Nothing Special   »   [go: up one dir, main page]

You seem to have javascript disabled. Please note that many of the page functionalities won't work as expected without javascript enabled.
 
 
Sign in to use this feature.

Years

Between: -

Subjects

remove_circle_outline
remove_circle_outline
remove_circle_outline
remove_circle_outline
remove_circle_outline

Journals

Article Types

Countries / Regions

Search Results (43)

Search Parameters:
Keywords = aircraft infrared observability

Order results
Result details
Results per page
Select all
Export citation of selected articles as:
27 pages, 28409 KiB  
Article
Non-Dominated Sorting Genetic Algorithm II (NSGA2)-Based Parameter Optimization of the MSMGWB Model Used in Remote Infrared Sensing Prediction for Hot Combustion Gas Plume
by Yihan Li, Haiyang Hu and Qiang Wang
Remote Sens. 2024, 16(17), 3116; https://doi.org/10.3390/rs16173116 - 23 Aug 2024
Cited by 1 | Viewed by 683
Abstract
The Multi-Scale Multi-Group Wide-Band (MSMGWB) model was used to calculate radiative transfer in strongly non-isothermal and inhomogeneous media such as the remote infrared sensing of aircraft exhaust system and jet plume scenario. In this work, the reference temperature was introduced into the model [...] Read more.
The Multi-Scale Multi-Group Wide-Band (MSMGWB) model was used to calculate radiative transfer in strongly non-isothermal and inhomogeneous media such as the remote infrared sensing of aircraft exhaust system and jet plume scenario. In this work, the reference temperature was introduced into the model as an independent variable for each spectral subinterval group. Then, to deal with the exceedingly vast parameter sample space (i.e., the combination of spectral subinterval grouping results, reference temperatures and Gaussian quadrature schemes), an MSMGWB model’s parameter optimization process superior to the exhaustive approach employed in previous studies was established, which was consisted of the Non-dominated Sorting Genetic Algorithm II method (NSGA2) and an iterative scan method. Through a series of 0-D test cases and two real 3-D remote infrared imaging results of an aircraft exhaust system, it was observed that the MSMGWB model established and optimiazed in current work demonstrated notable improvements in both accuracy and computational efficiency. Full article
Show Figures

Graphical abstract

Graphical abstract
Full article ">Figure 1
<p>The relationship between <span class="html-italic">k</span> and <math display="inline"><semantics> <msub> <mi>g</mi> <mrow> <mi>n</mi> <mi>m</mi> </mrow> </msub> </semantics></math> of a group in different reference temperatures and thermodynamic states at 8~14 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band.</p>
Full article ">Figure 2
<p>Relationship between probability density of objective function value and three critical factors (Gaussian quadrature point quantity, reference temperature, and wavenumber subinterval grouping).</p>
Full article ">Figure 3
<p>Genotype and crossover process diagram.</p>
Full article ">Figure 4
<p>NSGA2 algorithm workflow diagram.</p>
Full article ">Figure 5
<p>Offspring generation workflow diagram.</p>
Full article ">Figure 6
<p>Convergence results of the NSGA2 method: (<b>a</b>) the foremost 10 Pareto front results, (<b>b</b>) convergence iteration process of 10 random grouping strategy combinations.</p>
Full article ">Figure 7
<p><math display="inline"><semantics> <msub> <mi>f</mi> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mn>0</mn> </mrow> </msub> </semantics></math> results between exhaustive search method and NSGA2 method.</p>
Full article ">Figure 8
<p>The <math display="inline"><semantics> <msub> <mi>f</mi> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mn>0</mn> </mrow> </msub> </semantics></math> results among 100 <math display="inline"><semantics> <mrow> <msub> <mi mathvariant="normal">H</mi> <mn>2</mn> </msub> <mi mathvariant="normal">O</mi> </mrow> </semantics></math> and 400 <math display="inline"><semantics> <msub> <mi>CO</mi> <mn>2</mn> </msub> </semantics></math> grouping strategy combinations.</p>
Full article ">Figure 9
<p>Diagram of 4 iterative scan method process plans.</p>
Full article ">Figure 10
<p>Convergence perfomance of 4 plans for scan iteration process.</p>
Full article ">Figure 11
<p>Ratio of the <math display="inline"><semantics> <msub> <mi>f</mi> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mn>0</mn> </mrow> </msub> </semantics></math> at the current sample population size to its corresponding baseline value.</p>
Full article ">Figure 12
<p><math display="inline"><semantics> <msub> <mi>f</mi> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mn>0</mn> </mrow> </msub> </semantics></math> results between the same grouping result combination in the NSGA2 model population sizes of 5000 and 40,000.</p>
Full article ">Figure 13
<p>Optimization results at 2~2.5 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band: (<b>a</b>) Pareto front, (<b>b</b>) <math display="inline"><semantics> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mi>o</mi> <msub> <mi>r</mi> <mrow> <mi>j</mi> <mo>,</mo> <mi>m</mi> <mi>a</mi> <mi>x</mi> </mrow> </msub> </mrow> </semantics></math> in 56 0-D cases.</p>
Full article ">Figure 14
<p>Optimization results at 3.7~4.8 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band: (<b>a</b>) Pareto front, (<b>b</b>) <math display="inline"><semantics> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mi>o</mi> <msub> <mi>r</mi> <mrow> <mi>j</mi> <mo>,</mo> <mi>m</mi> <mi>a</mi> <mi>x</mi> </mrow> </msub> </mrow> </semantics></math> in 56 0-D cases.</p>
Full article ">Figure 15
<p>Optimization results at 3~5 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band: (<b>a</b>) Pareto front, (<b>b</b>) <math display="inline"><semantics> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mi>o</mi> <msub> <mi>r</mi> <mrow> <mi>j</mi> <mo>,</mo> <mi>m</mi> <mi>a</mi> <mi>x</mi> </mrow> </msub> </mrow> </semantics></math> in 56 0-D cases.</p>
Full article ">Figure 16
<p>Optimization results at 7.7~9.7 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band: (<b>a</b>) Pareto front, (<b>b</b>) <math display="inline"><semantics> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mi>o</mi> <msub> <mi>r</mi> <mrow> <mi>j</mi> <mo>,</mo> <mi>m</mi> <mi>a</mi> <mi>x</mi> </mrow> </msub> </mrow> </semantics></math> in 56 0-D cases.</p>
Full article ">Figure 17
<p>Optimization results at 8~14 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band: (<b>a</b>) Pareto front, (<b>b</b>) <math display="inline"><semantics> <mrow> <mi>e</mi> <mi>r</mi> <mi>r</mi> <mi>o</mi> <msub> <mi>r</mi> <mrow> <mi>j</mi> <mo>,</mo> <mi>m</mi> <mi>a</mi> <mi>x</mi> </mrow> </msub> </mrow> </semantics></math> in 56 0-D cases.</p>
Full article ">Figure 18
<p>Aerosol spectral extinction coefficient at 0~7 km altitude and 2~14 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m: (<b>a</b>) large-sized case, (<b>b</b>) small-sized case.</p>
Full article ">Figure 19
<p>Diagram of the Large-sized exhaust system with a cooling structure.</p>
Full article ">Figure 20
<p>Distribution of temperature (<span class="html-italic">T</span>), pressure (<span class="html-italic">p</span>), carbon dioxide mass fraction (<math display="inline"><semantics> <msub> <mi>y</mi> <mrow> <mi>C</mi> <msub> <mi>O</mi> <mn>2</mn> </msub> </mrow> </msub> </semantics></math>), and Mach number (<math display="inline"><semantics> <mrow> <mi>M</mi> <mi>a</mi> </mrow> </semantics></math>) in the meridional and axial sections of the fluid field of the large-sized exhaust system with a cooling structure.</p>
Full article ">Figure 21
<p>Temperature (<span class="html-italic">T</span>) distribution of the solid part of the large-sized exhaust system with a cooling structure.</p>
Full article ">Figure 22
<p>Remote infrared imaging of the large-sized exhaust system with a cooling structure in different atmospheric window bands (<b>left</b>), and the distribution of calculation errors of the optimized MSMGWB model (<b>right</b>), (<b>a</b>,<b>b</b>) 2~2.5 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>c</b>,<b>d</b>) 3.7~4.8 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>e</b>,<b>f</b>) 3~5 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>g</b>,<b>h</b>) 7.7~9.7 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>i</b>,<b>j</b>) 8~14 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band.</p>
Full article ">Figure 23
<p>Diagram of the small-sized exhaust system without a cooling structure.</p>
Full article ">Figure 24
<p>Distribution of temperature (<span class="html-italic">T</span>), pressure (<span class="html-italic">p</span>), carbon dioxide mass fraction (<math display="inline"><semantics> <msub> <mi>y</mi> <mrow> <mi>C</mi> <msub> <mi>O</mi> <mn>2</mn> </msub> </mrow> </msub> </semantics></math>), and Mach number (<math display="inline"><semantics> <mrow> <mi>M</mi> <mi>a</mi> </mrow> </semantics></math>) in the meridional and axial sections of the fluid field of the small-sized exhaust system without a cooling structure.</p>
Full article ">Figure 25
<p>Temperature (<span class="html-italic">T</span>) distribution of the major components of the small-sized exhaust system without a cooling structure.</p>
Full article ">Figure 26
<p>Remote infrared imaging of the small-sized exhaust system without a cooling structure in different atmospheric window bands (<b>left</b>) and the distribution of calculation errors of the optimized MSMGWB model (<b>right</b>), (<b>a</b>,<b>b</b>) 2~2.5 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>c</b>,<b>d</b>) 3.7~4.8 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>e</b>,<b>f</b>) 3~5 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>g</b>,<b>h</b>) 7.7~9.7 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band, (<b>i</b>,<b>j</b>) 8~14 <math display="inline"><semantics> <mi mathvariant="sans-serif">μ</mi> </semantics></math>m band.</p>
Full article ">Figure A1
<p>Two types of radiative transfer paths, diagram of 56 0-D cases.</p>
Full article ">
23 pages, 8075 KiB  
Article
MATI: Multimodal Adaptive Tracking Integrator for Robust Visual Object Tracking
by Kai Li, Lihua Cai, Guangjian He and Xun Gong
Sensors 2024, 24(15), 4911; https://doi.org/10.3390/s24154911 - 29 Jul 2024
Viewed by 883
Abstract
Visual object tracking, pivotal for applications like earth observation and environmental monitoring, encounters challenges under adverse conditions such as low light and complex backgrounds. Traditional tracking technologies often falter, especially when tracking dynamic objects like aircraft amidst rapid movements and environmental disturbances. This [...] Read more.
Visual object tracking, pivotal for applications like earth observation and environmental monitoring, encounters challenges under adverse conditions such as low light and complex backgrounds. Traditional tracking technologies often falter, especially when tracking dynamic objects like aircraft amidst rapid movements and environmental disturbances. This study introduces an innovative adaptive multimodal image object-tracking model that harnesses the capabilities of multispectral image sensors, combining infrared and visible light imagery to significantly enhance tracking accuracy and robustness. By employing the advanced vision transformer architecture and integrating token spatial filtering (TSF) and crossmodal compensation (CMC), our model dynamically adjusts to diverse tracking scenarios. Comprehensive experiments conducted on a private dataset and various public datasets demonstrate the model’s superior performance under extreme conditions, affirming its adaptability to rapid environmental changes and sensor limitations. This research not only advances visual tracking technology but also offers extensive insights into multisource image fusion and adaptive tracking strategies, establishing a robust foundation for future enhancements in sensor-based tracking systems. Full article
(This article belongs to the Section Navigation and Positioning)
Show Figures

Figure 1

Figure 1
<p>Schematic of the multimodal tracking network architecture. This diagram illustrates the comprehensive workflow of our tracking model, which processes both visible and optionally infrared image inputs. The visible and infrared images undergo initial patch embedding and subsequent position embedding. The data flow then progresses through a series of encoders, incorporating token spatial filtering. A key component, the crossmodal compensation module, is selectively engaged to integrate features from both image types, enhancing the system’s ability to handle diverse environmental inputs and improve target detection accuracy. This model architecture exemplifies our approach to adaptable, multimodal tracking by efficiently processing various input types and optimizing computational resources.</p>
Full article ">Figure 2
<p>Visualizations of attention weights in the search areas corresponding to different tracking targets after various ViT layers. Subfigures labeled ’<b>a(1)</b>’, ’<b>b(1)</b>’, ’<b>a(2)</b>’, ’<b>b(2)</b>’, ’<b>a(3)</b>’, and ’<b>b(3)</b>’ represent attention distributions before and after employing TSF modules for targets 1, 2, and 3, respectively. Layers 4, 7, and 10 are displayed to illustrate how the model estimates similarity across positions in the search area. The red rectangles mark the locations of the target objects in each search region image.</p>
Full article ">Figure 3
<p>Visualization of attention maps at different layers across three flight phases, with and without the use of CMC modules. Subfigures labeled with ’<b>a(1)</b>’, ’<b>a(2)</b>’, ’<b>a(3)</b>’ represent the attention distribution before employing CMC modules during the first, second, and third flight phases, respectively. Correspondingly, ’<b>b(1)</b>’, ’<b>b(2)</b>’, ’<b>b(3)</b>’ depict the attention distribution after employing CMC modules. The red rectangle marks the location of the target object.</p>
Full article ">Figure A1
<p>Visualizations of attention weights in the search areas corresponding to different tracking targets after various ViT layers. Subfigures labeled ’<b>a(1)</b>’, ’<b>b(1)</b>’, ’<b>a(2)</b>’, ’<b>b(2)</b>’, ’<b>a(3)</b>’, ’<b>b(3)</b>’, ’<b>a(4)</b>’, ’<b>b(4)</b>’, ’<b>a(5)</b>’, ’<b>b(5)</b>’, ’<b>a(6)</b>’, ’<b>b(6)</b>’, ’<b>a(7)</b>’, and ’<b>b(7)</b>’ represent attention distributions before and after employing TSF modules for targets 1, 2, 3, 4, 5, 6, and 7, respectively. Layers 4, 7, and 10 are displayed to illustrate how the model estimates similarity across positions in the search area. The red rectangles mark the locations of the target objects in each search region image.</p>
Full article ">Figure A1 Cont.
<p>Visualizations of attention weights in the search areas corresponding to different tracking targets after various ViT layers. Subfigures labeled ’<b>a(1)</b>’, ’<b>b(1)</b>’, ’<b>a(2)</b>’, ’<b>b(2)</b>’, ’<b>a(3)</b>’, ’<b>b(3)</b>’, ’<b>a(4)</b>’, ’<b>b(4)</b>’, ’<b>a(5)</b>’, ’<b>b(5)</b>’, ’<b>a(6)</b>’, ’<b>b(6)</b>’, ’<b>a(7)</b>’, and ’<b>b(7)</b>’ represent attention distributions before and after employing TSF modules for targets 1, 2, 3, 4, 5, 6, and 7, respectively. Layers 4, 7, and 10 are displayed to illustrate how the model estimates similarity across positions in the search area. The red rectangles mark the locations of the target objects in each search region image.</p>
Full article ">
17 pages, 10012 KiB  
Article
Arctic Sea Ice Albedo Estimation from Fengyun-3C/Visible and Infra-Red Radiometer
by Xiaohui Sun and Lei Guan
Remote Sens. 2024, 16(10), 1719; https://doi.org/10.3390/rs16101719 - 12 May 2024
Viewed by 1316
Abstract
The sea ice albedo can amplify global climate change and affect the surface energy in the Arctic. In this paper, the data from Visible and Infra-Red Radiometer (VIRR) onboard Fengyun-3C satellite are applied to derive the Arctic sea ice albedo. Two radiative transfer [...] Read more.
The sea ice albedo can amplify global climate change and affect the surface energy in the Arctic. In this paper, the data from Visible and Infra-Red Radiometer (VIRR) onboard Fengyun-3C satellite are applied to derive the Arctic sea ice albedo. Two radiative transfer models, namely, 6S and FluxNet, are used to simulate the reflectance and albedo in the shortwave band. Clear sky sea ice albedo in the Arctic region (60°~90°N) from 2016 to 2019 is derived through the physical process, including data preprocessing, narrowband to broadband conversion, anisotropy correction, and atmospheric correction. The results are compared with aircraft measurements and AVHRR Polar Pathfinder-Extended (APP-x) albedo product and OLCI MPF product. The bias and standard deviation of the difference between VIRR albedo and aircraft measurements are −0.040 and 0.071, respectively. Compared with APP-x product and OLCI MPF product, a good consistency of albedo is shown. And analyzed together with melt pond fraction, an obvious negative relationship can be seen. After processing the 4-year data, an obvious annual trend can be observed. Due to the influence of snow on the ice surface, the average surface albedo of the Arctic in March and April can reach more than 0.8. Starting in May, with the ice and snow melting and melt ponds forming, the albedo drops rapidly to 0.5–0.6. Into August, the melt ponds begin to freeze and the surface albedo increases. Full article
Show Figures

Figure 1

Figure 1
<p>The process flow of the retrieval algorithm.</p>
Full article ">Figure 2
<p>Cloud detection tree.</p>
Full article ">Figure 3
<p>Clear sky reflectance of channel 1 after cloud detection on 6 June 2017.</p>
Full article ">Figure 4
<p>Spectral reflectance curves processed from MOSAIC.</p>
Full article ">Figure 5
<p>Clear sky broadband reflectance at the top of atmosphere on 6 June 2017.</p>
Full article ">Figure 6
<p>Clear sky albedo at the top of atmosphere after anisotropy correction on 6 June 2017.</p>
Full article ">Figure 7
<p>Relationship between the top of atmospheric albedo and surface albedo varied with the total column ozone (<b>a</b>), aerosol optical depth (<b>b</b>), and total column water vapor (<b>c</b>) (original condition: the solar zenith angle is 60°, the aerosol optical depth is 0.25, the total column ozone is 6.96 g/m<sup>2</sup>, and the total column water vapor is 1.0 g/cm<sup>2</sup>).</p>
Full article ">Figure 8
<p>Clear sky sea ice albedo on 6 June 2017.</p>
Full article ">Figure 9
<p>Space distribution of aircraft measurement data matched up with VIRR albedo.</p>
Full article ">Figure 10
<p>Scatterplot (<b>a</b>) and frequency (<b>b</b>) distribution of the VIRR albedo and aircraft measurements.</p>
Full article ">Figure 11
<p>Daily average broadband albedo scatterplots of retrieval (blue lines) and APP-x product (orange lines) in 2016 (<b>a</b>), 2017 (<b>b</b>), 2018 (<b>c</b>), and 2019 (<b>d</b>).</p>
Full article ">Figure 12
<p>Daily average broadband albedo scatterplots of retrieval (blue lines) and OLCI albedo (orange lines) and melt pond fraction product (green lines) in 2017 (<b>a</b>), 2018 (<b>b</b>), and 2019 (<b>c</b>).</p>
Full article ">Figure 13
<p>Monthly average sea ice albedo map in (<b>a</b>) March, (<b>b</b>) April, (<b>c</b>) May, (<b>d</b>) June, (<b>e</b>) July, and (<b>f</b>) August, from 2016 to 2019.</p>
Full article ">
19 pages, 6697 KiB  
Article
Methane Retrieval from Hyperspectral Infrared Atmospheric Sounder on FY3D
by Xinxin Zhang, Ying Zhang, Fan Meng, Jinhua Tao, Hongmei Wang, Yapeng Wang and Liangfu Chen
Remote Sens. 2024, 16(8), 1414; https://doi.org/10.3390/rs16081414 - 16 Apr 2024
Viewed by 1001
Abstract
This study utilized an infrared spotlight Hyperspectral infrared Atmospheric Sounder (HIRAS) and the Medium Resolution Spectral Imager (MERSI) mounted on FY3D cloud products from the National Satellite Meteorological Center of China to obtain methane profile information. Methane inversion channels near 7.7 μm were [...] Read more.
This study utilized an infrared spotlight Hyperspectral infrared Atmospheric Sounder (HIRAS) and the Medium Resolution Spectral Imager (MERSI) mounted on FY3D cloud products from the National Satellite Meteorological Center of China to obtain methane profile information. Methane inversion channels near 7.7 μm were selected based on the different distribution of methane weighting functions across different seasons and latitudes, and the selected retrieval channels had a great sensitivity to methane but not to other parameters. The optimization method was employed to retrieve methane profiles using these channels. The ozone profiles, temperature, and water vapor of the European Centre for Medium-Range Weather Forecasts (ECMWF) fifth-generation reanalysis data (ERA5) were applied to the retrieval process. After validating the methane profile concentrations retrieved by HIRAS, the following conclusions were drawn: (1) compared with Civil Aircraft for the Regular Investigation of the Atmosphere Based on an Instrument Container (CARIBIC) flight data, the average correlation coefficient, relative difference, and root mean square error were 0.73, 0.0491, and 18.9 ppbv, respectively, with lower relative differences and root mean square errors in low-latitude regions than in mid-latitude regions. (2) The methane profiles retrieved from May 2019 to September 2021 showed an average error within 60 ppbv compared with the Fourier transform infrared spectrometer (FTIR) station observations of the Infrared Working Group (IRWG) of the Network for the Detection of Atmospheric Composition Change (NDACC). The errors between the a priori and retrieved values, as well as between the retrieved and smoothed values, were larger by around 400–500 hPa. Apart from Toronto and Alzomoni, which had larger peak values in autumn and spring respectively, the mean column averaging kernels typically has a larger peak in summer. Full article
(This article belongs to the Section Atmospheric Remote Sensing)
Show Figures

Figure 1

Figure 1
<p>Data from four flights of the Civil Aircraft for the Regular Investigation of the Atmosphere Based on an Instrument Container (CARIBIC). The light blue line is flight 569 (1 May 2019), the light green line is flight 575 (14 August 2019), the red line is flight 586 (9 January 2020), and the light pink line is flight 587 (10 January 2020).</p>
Full article ">Figure 2
<p>Sensitivities of HIRAS channels located in 1200−1750 cm<sup>−1</sup> to variations of 1 K temperature (blue), 10% H<sub>2</sub>O (grey), 1% CO<sub>2</sub> (yellow),10% CH<sub>4</sub> (red), 10% N<sub>2</sub>O (pink), 10% O<sub>3</sub> (dark red) and 10% CO (light blue).</p>
Full article ">Figure 3
<p>CH<sub>4</sub> Jacobians (K/ppmv) from 1210 to 1400 cm<sup>−1</sup> with a spectral resolution of 0.625 cm<sup>−1</sup> for (<b>a</b>) high latitude between 90°S–30°S and 30–90°N in spring and summer (HS), (<b>b</b>) high latitude between 90°S–30°S and 30–90°N in spring and summer (HS), (<b>c</b>) low latitude (30°S–30°N) in spring and summer (LS) and (<b>d</b>) low latitude (30°S–30°N) in autumn and winter (LW). The different colors of the lines in the figure represent different channels (1210 to 1400 cm<sup>−1</sup>).</p>
Full article ">Figure 4
<p>CH<sub>4</sub> retrieval channels in (<b>a</b>) HS, (<b>b</b>) HW (light blue line), (<b>c</b>) LS and (<b>d</b>) LW.</p>
Full article ">Figure 5
<p>CH<sub>4</sub> comparison between HIRAS retrievals and smoothed CARIBIC with a 0.5° × 0.5° spatial resolution. (<b>a</b>) Flight no. 569, (<b>b</b>) flight no. 575, (<b>c</b>) flight no. 586, and (<b>d</b>) flight no. 587.</p>
Full article ">Figure 6
<p>CH<sub>4</sub> profile comparisons between a priori (pink line), smoothing Fourier transform infrared spectrometer (FTIR) (light green line) observation products, and HIRAS retrieval (light blue line), in FTIR sites.</p>
Full article ">Figure 7
<p>The mean column averaging kernels of CH<sub>4</sub> retrievals in FTIR stations. The blue, green, red, and black lines refer to spring, summer, autumn, and winter, respectively.</p>
Full article ">Figure 8
<p>Means of variations of CH<sub>4</sub> induced by variations of T (1–10 hPa: 2 K; 10–1000 hPa: 0.2 K) and H<sub>2</sub>O (5%) in Altzomoni and Rikubetsu.</p>
Full article ">Figure 9
<p>Comparison of Altzomoni and Rikubetsu observations with inversion results (<b>a</b>) and inversion results using changed channels. (<b>a</b>) Channels in opposite seasons in Altzomoni and (<b>b</b>) channels in high latitudes in Rikubetsu.</p>
Full article ">
20 pages, 1786 KiB  
Review
Anthropogenic Impacts in the Lower Stratosphere: Scale Invariant Analysis
by Adrian F. Tuck
Atmosphere 2024, 15(4), 465; https://doi.org/10.3390/atmos15040465 - 9 Apr 2024
Viewed by 1232
Abstract
Aircraft and rockets entered the lower stratosphere on a regular basis during World War II and have done so in increasing numbers to the present. Atmospheric testing of nuclear weapons saw radioactive isotopes in the stratosphere. Rocket launches of orbiters are projected to [...] Read more.
Aircraft and rockets entered the lower stratosphere on a regular basis during World War II and have done so in increasing numbers to the present. Atmospheric testing of nuclear weapons saw radioactive isotopes in the stratosphere. Rocket launches of orbiters are projected to increase substantially in the near future. The burnup of orbiters has left signatures in the aerosol. There are proposals to attenuate incoming solar radiation by deliberate injection of artificial aerosols into the stratosphere to “geoengineer” cooling trends in surface temperature, with the aim of countering the heating effects of infrared active gases. These gases are mainly carbon dioxide from fossil burning, with additional contributions from methane, chlorofluorocarbons, nitrous oxide and the accompanying positive feedback from increasing water vapor. Residence times as a function of altitude above the tropopause are critical. The analysis of in situ data is performed using statistical multifractal techniques and combined with remotely sensed and modeled results to examine the classical radiation–photochemistry–fluid mechanics interaction that determines the composition and dynamics of the lower stratosphere. It is critical in assessing anthropogenic effects. It is argued that progress in predictive ability is driven by the continued generation of new and quantitative observations in the laboratory and the atmosphere. Full article
(This article belongs to the Section Upper Atmosphere)
Show Figures

Figure 1

Figure 1
<p>Average water vapor profiles in the tropics and in northern midlatitudes during the late winter/spring period when the tropical tropopause is coldest. The data are from ER-2 take-offs and landings 1987–1996 at Darwin and Panama (tropics), and from Moffett Field; Bangor, Maine and Wallops Island (midlatitudes). It is apparent that the air in the lowest 5 km above the tropopause has not been dried exclusively in the tropics. After Ref. [<a href="#B19-atmosphere-15-00465" class="html-bibr">19</a>].</p>
Full article ">Figure 2
<p>(<b>a</b>) Typical temperature profile. (<b>b</b>) Typical ozone number density profile. (<b>c</b>) Typical mixing ratio profile. The contrast between (<b>b</b>,<b>c</b>) shows why the greatest contributions to the total overhead ozone column arise from altitudes below 25 km, depending on latitude; the number density profile shows where the greatest contribution to the overhead column amount is located. The maxima in the profiles in (<b>b</b>,<b>c</b>) slope downwards from the tropics toward the poles. Profiles of DU (Dobson Units) per km are in Figure 4 of Ref. [<a href="#B20-atmosphere-15-00465" class="html-bibr">20</a>].</p>
Full article ">Figure 3
<p>(<b>1</b>) is the logarithmic density profile. (<b>2</b>) is the solar flux and (<b>3</b>) is the resulting absorption rate to produce ozone. The result is a mixing ratio profile peaking at about 30 km, while the number density profile peaks lower down at about 20–25 km in midlatitudes, see <a href="#atmosphere-15-00465-f002" class="html-fig">Figure 2</a>. After Ref. [<a href="#B21-atmosphere-15-00465" class="html-bibr">21</a>].</p>
Full article ">Figure 4
<p>Data from ER-2 observations during POLARIS [<a href="#B133-atmosphere-15-00465" class="html-bibr">133</a>,<a href="#B134-atmosphere-15-00465" class="html-bibr">134</a>] and SOLVE [<a href="#B137-atmosphere-15-00465" class="html-bibr">137</a>]. The abscissa in both diagrams is the intermittency of temperature. The ordinate in the left diagram is the ozone photodissociation rate averaged over the flight segment. The ordinate in the right diagram is the temperature averaged over the flight segment. Error bars are standard deviations. The correlations indicate incomplete thermalization of photofragment energy at 55 mbar.</p>
Full article ">Figure 5
<p>Change in temperature with altitude (the lapse rate). The dry adiabatic lapse rate (DALR) is 9.8 K/km and is marked by the vertical dashed line. The data are from Winter Storms 2004 [<a href="#B159-atmosphere-15-00465" class="html-bibr">159</a>,<a href="#B160-atmosphere-15-00465" class="html-bibr">160</a>] and were calculated for (<b>a</b>) a vertical interval of 15 m and (<b>b</b>) a vertical interval of 100 m. In (<b>a</b>), about 1% of the cases exceed the dry adiabatic lapse rate, whereas in (<b>b</b>), none do. The tropopause is discernible at vertical resolutions above 30 m using this criterion, but not below it. The 50% exceedance of the DALR is, by extrapolation, at 93 cm. Note that fluid flow emerges from a simulated molecular dynamics population of Maxwellian billiards in an asymmetric environment on very short time and space scales [<a href="#B165-atmosphere-15-00465" class="html-bibr">165</a>,<a href="#B166-atmosphere-15-00465" class="html-bibr">166</a>].</p>
Full article ">
15 pages, 2695 KiB  
Article
Electric Field-Driven Jetting and Water-Assisted Transfer Printing for High-Resolution Electronics on Complex Curved Surfaces
by Wenzheng Sun, Zhenghao Li, Xiaoyang Zhu, Houchao Zhang, Hongke Li, Rui Wang, Wensong Ge, Huangyu Chen, Xinyi Du, Chaohong Liu, Fan Zhang, Fei Wang, Guangming Zhang and Hongbo Lan
Electronics 2024, 13(7), 1182; https://doi.org/10.3390/electronics13071182 - 23 Mar 2024
Viewed by 1057
Abstract
High-resolution electronics on complex curved surfaces have wide applications in fields such as biometric health monitoring, intelligent aircraft skins, conformal displays, and biomimetics. However, current manufacturing processes can only adapt to limited curvature, posing a significant challenge for achieving high-resolution fabrication of electronics [...] Read more.
High-resolution electronics on complex curved surfaces have wide applications in fields such as biometric health monitoring, intelligent aircraft skins, conformal displays, and biomimetics. However, current manufacturing processes can only adapt to limited curvature, posing a significant challenge for achieving high-resolution fabrication of electronics on complex curved surfaces. In this study, we propose a novel fabrication strategy that combines electric field-driven jetting and water-assisted transfer printing techniques to achieve the fabrication of high-resolution electronics on complex curved surfaces. The electric field-driven jetting enables the fabrication of high-resolution 2D electronics on sacrificial layer substrates. After dissolving the sacrificial layer, it is observed that the 2D electronics form a self-supporting structure with a certain rigidity and flexibility. During the water-assisted transfer printing process, this self-supporting structure undergoes stretching deformation with excellent conformity of the electronics to curved surfaces while effectively minimizing wrinkles. Finally, we successfully demonstrate the manufacture of 25 μm high-resolution electronics on highly curved surfaces (nautilus shell) and complex (scallop shell, stone) surfaces. The integrity of transferred circuit patterns and consistency of conductors are verified through infrared thermography analysis, confirming the feasibility of this manufacturing strategy. In addition, a protective film with strong adhesive properties is sprayed onto the transferred curved circuits to enhance their adhesion and resistance to extreme environments such as acids and alkalis. Our proposed technique provides a simple and effective new strategy for the fabrication of high-resolution electronics on complex curved surfaces. Full article
Show Figures

Figure 1

Figure 1
<p>Schematic of the process flow for the preparation of high-resolution electronics on complex curved surfaces by combining electric field-driven jetting and water-assisted transfer printing techniques: (<b>a</b>) Spin-coating the sacrificial layer; (<b>b</b>) Printing the 2D electronics on the planar surface; (<b>c</b>) Electric field-driven jetting principle; (<b>d</b>) 2D electronics falling off; (<b>e</b>) Moving the 2D electronics above the complex curved surfaces; (<b>f</b>) Holding out the curved surface from the water; (<b>g</b>) Macro image of a 2D electronics; (<b>h</b>,<b>i</b>) SEM images of (<b>g</b>) local enlargements; (<b>j</b>) Macro image of the high-resolution electronics on the complex curved surfaces; (<b>k</b>,<b>l</b>) SEM images of (<b>j</b>) and local enlargements.</p>
Full article ">Figure 2
<p>Two-dimensional electronics printing parameter laws: (<b>a</b>) Print air pressure and electronics resolution relationship; (<b>b</b>) Print height and electronics resolution relationship and microstructure; (<b>c</b>) Print speed and electronics resolution relationship; (<b>d</b>) Print voltage and electronics resolution relationship and microstructure.</p>
Full article ">Figure 3
<p>Macro- and microstructures of high-resolution electronics on typical complex curved surfaces: (<b>a</b>–<b>c</b>) Macro- and microstructures of high-resolution electronics on shell substrate; (<b>d</b>–<b>f</b>) Macro- and microstructures of high-resolution electronics on hot-melt adhesive substrates; (<b>g</b>–<b>i</b>) Macro- and microstructures of high-resolution electronics on plastic plug base; (<b>j</b>–<b>l</b>) Macro- and microstructures of high-resolution electronics on resin sphere substrate; (<b>m</b>–<b>o</b>) Macro- and microstructures of high-resolution electronics on pipette bases.</p>
Full article ">Figure 4
<p>Macroscopic imaging and thermal imaging testing of high-resolution electronics on large-curvature and arbitrarily complex surface substrates: (<b>a</b>) Macroscopic image of high-resolution electronics on glass pane substrate; (<b>b</b>) Thermal imaging testing of the high-resolution electronics on glass pane substrate; (<b>c</b>) Macroscopic image of high-resolution electronics on scallop shell substrate; (<b>d</b>) Thermal imaging testing of the high-resolution electronics on scallop shell substrate; (<b>e</b>) Macroscopic image of high-resolution electronics on stone substrate; (<b>f</b>) Thermal imaging testing of high-resolution electronics on scallop substrate; (<b>g</b>) Macroscopic image of high-resolution electronics on conch shell substrate; (<b>h</b>) Thermal imaging tests of high-resolution electronics on conch shell substrates.</p>
Full article ">Figure 5
<p>Characterization of the properties of acrylic dome conformal circuits; (<b>a</b>) Transmittance of circuits before transfer; (<b>b</b>) Transmittance of circuits after transfer; (<b>c</b>) Resistance relations for circuits with different cycles; (<b>d</b>) Effect of heating temperature and heating time on circuit resistance; (<b>e</b>) Chemical stability test; (<b>f</b>) Adhesion test.</p>
Full article ">Figure 6
<p>Characterization of micro-morphology and performance of curved transparent electric heaters: (<b>a</b>) Macro image of a conformal circuit with acrylic dome cover; (<b>b</b>,<b>c</b>) SEM images of (<b>a</b>) as well as local enlargements; (<b>d</b>–<b>h</b>) Maximum temperatures corresponding to curved transparent heater with different voltages; (<b>i</b>) Temperature rise curve of curved transparent heater with different voltages; (<b>j</b>) Curved transparent electric heater 100 times thermal cycle curve.</p>
Full article ">
20 pages, 7586 KiB  
Article
CenterADNet: Infrared Video Target Detection Based on Central Point Regression
by Jiaqi Sun, Ming Wei, Jiarong Wang, Ming Zhu, Huilan Lin, Haitao Nie and Xiaotong Deng
Sensors 2024, 24(6), 1778; https://doi.org/10.3390/s24061778 - 9 Mar 2024
Cited by 1 | Viewed by 1224
Abstract
Infrared video target detection is a fundamental technology within infrared warning and tracking systems. In long-distance infrared remote sensing images, targets often manifest as circular spots or even single points. Due to the weak and similar characteristics of the target to the background [...] Read more.
Infrared video target detection is a fundamental technology within infrared warning and tracking systems. In long-distance infrared remote sensing images, targets often manifest as circular spots or even single points. Due to the weak and similar characteristics of the target to the background noise, the intelligent detection of these targets is extremely complex. Existing deep learning-based methods are affected by the downsampling of image features by convolutional neural networks, causing the features of small targets to almost disappear. So, we propose a new infrared video weak-target detection network based on central point regression. We focus on suppressing the image background by fusing the different features between consecutive frames with the original image features to eliminate the background’s influence. We also employ high-resolution feature preservation and incorporate a spatial–temporal attention module into the network to capture as many target features as possible and improve detection accuracy. Our method achieves superior results on the infrared image weak aircraft target detection dataset proposed by the National University of Defense Technology, as well as on the simulated dataset generated based on real-world observation. This demonstrates the efficiency of our approach for detecting weak point targets in infrared continuous images. Full article
Show Figures

Figure 1

Figure 1
<p>Illustration of consecutive frames in remote infrared long-range infrared remote sensing imaging (dim targets are marked with red boxes in the figure).</p>
Full article ">Figure 2
<p>Targets and noise (the upper portion represents noise, while the lower portion represents the target).</p>
Full article ">Figure 3
<p>Network-specific flowchart (multiple frames are differentially computed and fed into the network, incorporating attention modules, and ultimately outputting keypoint predictions).</p>
Full article ">Figure 4
<p>Matrix representation illustrating the results of differential computations across multiple frames.</p>
Full article ">Figure 5
<p>Components of the feature extraction network.</p>
Full article ">Figure 6
<p>The specific structure of stackable high-resolution network in this paper.</p>
Full article ">Figure 7
<p>Structural schematic diagram of the spatial–temporal attention module.</p>
Full article ">Figure 8
<p>Flowchart of implementation steps of simulation dataset MIRPT.</p>
Full article ">Figure 9
<p>Visualization of a subset of the simulated dataset MIRPT.</p>
Full article ">Figure 10
<p>Mask image of MIRST (first line) and mask image of infrared-weak aircraft dataset (second line).</p>
Full article ">Figure 11
<p>The annotation box of SIRST dataset is partially modified.</p>
Full article ">Figure 12
<p>Visualization results of detection keypoints of CenterNet and CenterADNet.</p>
Full article ">Figure 13
<p>Performance curves of CenterNet and CenterADNet: (<b>a</b>) AP performance curve; (<b>b</b>) AR performance curve.</p>
Full article ">Figure 14
<p>Effect demonstration on another dataset.</p>
Full article ">
14 pages, 4324 KiB  
Article
Receptivity and Stability Theory Analysis of a Transonic Swept Wing Experiment
by Yuanqiang Liu, Yan Liu, Zubi Ji, Yutian Wang and Jiakuan Xu
Aerospace 2023, 10(10), 903; https://doi.org/10.3390/aerospace10100903 - 23 Oct 2023
Viewed by 1516
Abstract
Surface suction provides an efficient way to delay boundary layer transitions. In order to verify the suction effects and determine the mechanism of suction control in transonic swept wing boundary layers, wind tunnel transition measurements in a hybrid laminar flow control (HLFC) wind [...] Read more.
Surface suction provides an efficient way to delay boundary layer transitions. In order to verify the suction effects and determine the mechanism of suction control in transonic swept wing boundary layers, wind tunnel transition measurements in a hybrid laminar flow control (HLFC) wind tunnel model uses an infrared thermography technique in the Aircraft Research Association (ARA) 2.74 m × 2.44 m low turbulence level transonic wind tunnel. Based on the experimental data of stationary crossflow dominant transitions without and with surface suction in transonic swept wing boundary layers, in this paper, the effects on the receptivity and linear and nonlinear evolution of stationary crossflow vortices have been analyzed with the consideration of curvature. Theoretical analysis agreed with the experimental observations in regard to the transition delay caused by boundary layer suction near the leading-edge region. Full article
(This article belongs to the Section Aeronautics)
Show Figures

Figure 1

Figure 1
<p>Wind tunnel setup of HFLC model (copied from Ref. [<a href="#B26-aerospace-10-00903" class="html-bibr">26</a>]). The gray area represents the surface suction region, the pink area is the experimental measurement region, and the orange area has hot films installed.</p>
Full article ">Figure 2
<p>Transition experimental data with surface suction. (<b>a</b>) Case 1, (<b>b</b>) Case 2.</p>
Full article ">Figure 3
<p>Comparison of pressure coefficient between computational results and experimental data.</p>
Full article ">Figure 4
<p>Comparison of velocity profiles before and after suction: (<b>a</b>) streamwise velocity; (<b>b</b>) crosswise velocity (arrows indicate the direction of flow from front to back).</p>
Full article ">Figure 5
<p>Comparison of <span class="html-italic">N</span> factor among various stationary crossflow waves before and after suction using LST: (<b>a</b>) no suction; (<b>b</b>) with suction.</p>
Full article ">Figure 6
<p>Comparison of <span class="html-italic">N</span> factor among various stationary crossflow waves before and after suction using LPSE: (<b>a</b>) no suction; (<b>b</b>) with suction.</p>
Full article ">Figure 7
<p>The critical <span class="html-italic">N</span> factors from LST and LPSE with and without suction.</p>
Full article ">Figure 8
<p>Computed receptivity coefficient of the most unstable crossflow vortices under no control and control states (Green circles indicate the starting point of the neutral curve).</p>
Full article ">Figure 9
<p>Computed peak disturbance amplitudes for (<b>a</b>) no suction and (<b>b</b>) suction cases.</p>
Full article ">Figure 10
<p>The comparison of saturated crossflow vortices before transition between the (<b>a</b>) no suction and (<b>b</b>) suction cases.</p>
Full article ">Figure 11
<p>Integrated amplification factor of the primary (0,1) mode under no control and control states through the NPSE.</p>
Full article ">
12 pages, 17484 KiB  
Technical Note
Validation of Landsat-9 and Landsat-8 Surface Temperature and Reflectance during the Underfly Event
by Rehman Eon, Aaron Gerace, Lucy Falcon, Ethan Poole, Tania Kleynhans, Nina Raqueño and Timothy Bauch
Remote Sens. 2023, 15(13), 3370; https://doi.org/10.3390/rs15133370 - 30 Jun 2023
Cited by 9 | Viewed by 2499
Abstract
With the launch of Landsat-9 on 27 September 2021, Landsat continues its fifty-year continuity mission of providing users with calibrated Earth observations. It has become a requirement that an underflight experiment be performed during commissioning to support sensor cross-calibration. In this most recent [...] Read more.
With the launch of Landsat-9 on 27 September 2021, Landsat continues its fifty-year continuity mission of providing users with calibrated Earth observations. It has become a requirement that an underflight experiment be performed during commissioning to support sensor cross-calibration. In this most recent experiment, Landsat-9 flew under Landsat-8 for nearly three days with over 50% ground overlap, from 13 to 15 November 2021. To address the scarcity of reference data that are available to support calibration and validation early-on in the mission, a ground campaign was planned and executed by the Rochester Institute of Technology (RIT) on 14 November 2021 to provide full spectrum measurements for early mission comparisons. The primary experiment was conducted in the Outer Banks, North Carolina at Jockey’s Ridge Sand Dunes. Full-spectrum ground-based measurements were acquired with calibrated reference equipment, while a novel Unmanned Aircraft System (UAS)-based platforms acquired hyperspectral visible and near-infrared (VNIR)/Short-wave infrared (SWIR) imagery data and coincident broadband cooled thermal infrared (TIR) imagery. Results of satellite/UAS/ground comparisons were an indicator, during the commissioning phase, that Landsat-9 is behaving consistently with Landsat-8, ground reference, and UAS measurements. In the thermal infrared, all measurements agree to be within 1 K over water and to within 2 K over sand, which represents the most challenging material for estimating surface temperature. For the surface reflectance product(s), Landsat-8 and -9 are in good agreement and only deviate slightly from ground reference in the SWIR bands; a deviation of 2% in the VNIR and 5–8% in the SWIR regime. Subsequent longer-term studies indicate that Landsat 9 continues to perform as expected. The behavior of Thermal Infrared Sensor-2 (TIRS-2) against reference is also shown for the first year of the mission to illustrate its consistent performance. Full article
Show Figures

Figure 1

Figure 1
<p>The Jockey’s Ridge Sand Dune System. This site was chosen to support thermal calibration and validation due to its 1.73 km<math display="inline"><semantics><msup><mrow/><mn>2</mn></msup></semantics></math> area and material endpoints, i.e., water and sand. RIT’s MX-2 UAS-platform is equipped with full-spectrum sensors including a cooled thermal.</p>
Full article ">Figure 2
<p>The four different experiment regions during the underflight; Western New York, Phoenix Arizona, the Atlantic Coast, including the primary ground campaign site in the Outer Banks, North Carolina.</p>
Full article ">Figure 3
<p>(<b>a</b>) Image of the <math display="inline"><semantics><mi>μ</mi></semantics></math>FTIR, (<b>b</b>) the measured downwell and sample radiance from the <math display="inline"><semantics><mi>μ</mi></semantics></math>FTIR, and (<b>c</b>) the derived emissivity spectra using the temperature/emissivity separation algorithm. The placement of the two TIRS thermal bands is highlighted.</p>
Full article ">Figure 4
<p>(<b>a</b>) The measured NE<math display="inline"><semantics><mo>Δ</mo></semantics></math>T and (<b>b</b>) absolute radiometric uncertainty of the <math display="inline"><semantics><mi>μ</mi></semantics></math>FTIR between 8 and 14 <math display="inline"><semantics><mi mathvariant="sans-serif">μ</mi></semantics></math>m at three different temperatures (288 K, 303 K, and 318 K). These data illustrate the high fidelity of the <math display="inline"><semantics><mi>μ</mi></semantics></math>FTIR in measuring radiance.</p>
Full article ">Figure 5
<p>The bulk temperature of Canyon Lake, Arizona measured by the TidBit datalogger.</p>
Full article ">Figure 6
<p>BRDF measurements of the (<b>a</b>) 5% and (<b>b</b>) 50% Permaflect<span class="html-italic">®</span> panels using GRIT-T for Landsat band 4 (640–670 nm).</p>
Full article ">Figure 7
<p>The Permaflect<span class="html-italic">®</span> panels used during the underfly campaign to calibrate the UAS data to surface reflectance, and the spectra of the panels measured by the SVC spectroradiometer.</p>
Full article ">Figure 8
<p>The MX-2 multi-modal UAS payload consisting of five different imaging sensors on-board a DJI Wind 8 Octocopter, while the SWIR HSI in on-board a DJI Matrice 600.</p>
Full article ">Figure 9
<p>The NE<math display="inline"><semantics><mo>Δ</mo></semantics></math>T of the FLIR at three different temperatures.</p>
Full article ">Figure 10
<p>The absolute radiometric uncertainty of the FLIR at three different temperatures.</p>
Full article ">Figure 11
<p>The surface temperature map of the four different lakes derived from Landsat-9 using SW. TidBit dataloggers were deployed in each lake to monitor surface temperature for validating the ST product from L8/L9.</p>
Full article ">Figure 12
<p>The derived SW surface temperature for (<b>a</b>) Landsat-9 and (<b>b</b>) Landsat-8 versus the measured surface temperature using the TidBit dataloggers for water sites during the underfly event.</p>
Full article ">Figure 13
<p>(<b>a</b>) The derived SW surface temperature for Landsat-9 over the primary experiment site during the underfly event. (<b>b</b>) The measured emissivity spectra from the <math display="inline"><semantics><mi>μ</mi></semantics></math>FTIR of the dunes, and (<b>c</b>) the mosaic ST map of the dune from the FLIR and the corresponding RGB map of the dunes captured by the same UAS payload.</p>
Full article ">Figure 14
<p>The spectrally sampled image, to the Landsat VNIR/SWIR bands, of the Jockey’s Ridge experiment site collected from the VNIR/SWIR sensors on-board the UAS platform.</p>
Full article ">Figure 15
<p>The measured mean surface reflectance from L8, L9, and the UAS imagery acquired over the dune experiment site.</p>
Full article ">Figure 16
<p>The derived SW surface temperature for Landsat-9 versus the measured surface temperature using 26 NOAA buoys across the near-shore coastline of CONUS over the current mission life of Landsat-9.</p>
Full article ">
27 pages, 55934 KiB  
Article
Linear Contrails Detection, Tracking and Matching with Aircraft Using Geostationary Satellite and Air Traffic Data
by Rémi Chevallier, Marc Shapiro, Zebediah Engberg, Manuel Soler and Daniel Delahaye
Aerospace 2023, 10(7), 578; https://doi.org/10.3390/aerospace10070578 - 21 Jun 2023
Cited by 8 | Viewed by 4606
Abstract
Climate impact models of the non-CO2 emissions of aviation are still subject to significant uncertainties. Condensation trails, or contrails, are one of these non-CO2 effects. In order to validate the contrail simulation models, a dataset of observations covering the [...] Read more.
Climate impact models of the non-CO2 emissions of aviation are still subject to significant uncertainties. Condensation trails, or contrails, are one of these non-CO2 effects. In order to validate the contrail simulation models, a dataset of observations covering the entire lifetime of the contrails will be required, as well as the characteristics of the aircraft which produced them. This study carries on the work on contrail observation from geostationary satellite by proposing a new way to track contrails and identify the flight that produced it using geostationary satellite infrared images, weather data as well as air traffic data. It solves the tracking and the identification problem as one, each process leveraging information from the other to achieve a better overall result. This study is a new step towards a consistent contrail dataset that could be used to validate contrail models. Full article
(This article belongs to the Collection Air Transportation—Operations and Management)
Show Figures

Figure 1

Figure 1
<p>The Methodology developed in this study.</p>
Full article ">Figure 2
<p>Reprojection of the satellite images: Orthographic projection centered on continental US allowing to minimize distortion. (<b>a</b>) Geostationary image centered on the US, corresponding to Goes CONUS product. (<b>b</b>) Reprojected image: the orthographic projection minimizing distortion over the US.</p>
Full article ">Figure 3
<p>The principle of the method proposed by Appendix A12 of Schumann [<a href="#B2-aerospace-10-00578" class="html-bibr">2</a>]. It allows to compute the contribution of each pixel to the optical depth of the simulated contrail according to the distance between the center of the pixel and the contrail central axis.</p>
Full article ">Figure 4
<p>Description of the method used to study the difference in color between the contrail and the background.</p>
Full article ">Figure 5
<p>Comparison of the distributions of the color change induced by the contrail per channel (red, green blue) between the hand labelled contrails and our synthetic contrail generation method.</p>
Full article ">Figure 6
<p>Description of the method used to turn a simulated contrail mask into a synthetic contrail.</p>
Full article ">Figure 7
<p>CoCiP simulated contrails turned into a realistic synthetic satellite image. (<b>a</b>) Simulated contrails from CoCip turned into a set of polygons. (<b>b</b>) Polygons added in a GOES tile free of real contrails.</p>
Full article ">Figure 8
<p>The bounding boxes are overlapping: if not tuned correctly, non maximum suppression might delete the object with the lowest confidence score even if two different contrails were actually detected in the first place.</p>
Full article ">Figure 9
<p>This image contains linear shapes that look like condensation trails but are not.</p>
Full article ">Figure 10
<p>Result of contrail detection on real contrails. (<b>a</b>) Example of an unmodified GOES tile. (<b>b</b>) Detected contrails on this tile.</p>
Full article ">Figure 11
<p>Advection of the Flight Track with the wind. These lines correspond to the position at which a potential contrail would be located at the indicated time.</p>
Full article ">Figure 12
<p>Checking the quality of the matching between a detected contrail and two different flight tracks: advected flight track at timestep 6 needs to match the position of the polygon detected at timestamp 6. (<b>a</b>) Simulated contrail position matches the position of the contrail detected at timestamp 6. (<b>b</b>) Simulated contrail position doesn’t match the position of the contrail detected at timestamp 6.</p>
Full article ">Figure 13
<p>Selection of the portion of the flight that most probably produced the contrail.</p>
Full article ">Figure 14
<p>Contrail in the first situation must have a better score than in the second situation. (<b>a</b>) Contrail parallel to the track. (<b>b</b>) Contrail not parallel to the track.</p>
Full article ">Figure 15
<p>Selection of the successors of the detected contrail on the next frame.</p>
Full article ">Figure 16
<p>Examples of matching including tracking: the flight on the left picture gives a better match for the first polygon of the chain (on the left), but the evolution of the advected flight track does not match the evolution of the tracked contrail. (<b>a</b>) The contrail matches the advected flight track over the whole experiment. (<b>b</b>) The contrail drifts away from the advected flight track even if the first match is better.</p>
Full article ">Figure 17
<p>The situation at the beginning of the illustration example. Several polygons are detected on successive frames, and four flights flew in the area moments before the first polygons were detected.</p>
Full article ">Figure 18
<p>Chains generated from the situation presented in <a href="#aerospace-10-00578-f017" class="html-fig">Figure 17</a>. (<b>a</b>) Chain 1 from flight AAL944 and polygon 2790. (<b>b</b>) Chain 2 from flight DAL2057 and polygon 3106. (<b>c</b>) Chain 3 from flight DAL2057 and polygon 3627. (<b>d</b>) Chain 4 from flight RPA4727 and polygon 2824. (<b>e</b>) Chain 5 from flight SWA2163 and polygon 2790. (<b>f</b>) Chain 6 from flight SWA2163 and polygon 3118.</p>
Full article ">Figure 19
<p>Final set of selected chains after the optimization process.</p>
Full article ">Figure 20
<p>Distribution of the time of persistence of the tracked contrails.</p>
Full article ">Figure 21
<p>A long lasting contrail in the test case.</p>
Full article ">Figure 22
<p>Matching and tracking two contrails close and almost parallel: difficult without wind and traffic data.</p>
Full article ">
42 pages, 38264 KiB  
Review
A Review on Unmanned Aerial Vehicle Remote Sensing: Platforms, Sensors, Data Processing Methods, and Applications
by Zhengxin Zhang and Lixue Zhu
Drones 2023, 7(6), 398; https://doi.org/10.3390/drones7060398 - 15 Jun 2023
Cited by 86 | Viewed by 24446
Abstract
In recent years, UAV remote sensing has gradually attracted the attention of scientific researchers and industry, due to its broad application prospects. It has been widely used in agriculture, forestry, mining, and other industries. UAVs can be flexibly equipped with various sensors, such [...] Read more.
In recent years, UAV remote sensing has gradually attracted the attention of scientific researchers and industry, due to its broad application prospects. It has been widely used in agriculture, forestry, mining, and other industries. UAVs can be flexibly equipped with various sensors, such as optical, infrared, and LIDAR, and become an essential remote sensing observation platform. Based on UAV remote sensing, researchers can obtain many high-resolution images, with each pixel being a centimeter or millimeter. The purpose of this paper is to investigate the current applications of UAV remote sensing, as well as the aircraft platforms, data types, and elements used in each application category; the data processing methods, etc.; and to study the advantages of the current application of UAV remote sensing technology, the limitations, and promising directions that still lack applications. By reviewing the papers published in this field in recent years, we found that the current application research of UAV remote sensing research can be classified into four categories according to the application field: (1) Precision agriculture, including crop disease observation, crop yield estimation, and crop environmental observation; (2) Forestry remote sensing, including forest disease identification, forest disaster observation, etc.; (3) Remote sensing of power systems; (4) Artificial facilities and the natural environment. We found that in the papers published in recent years, image data (RGB, multi-spectral, hyper-spectral) processing mainly used neural network methods; in crop disease monitoring, multi-spectral data are the most studied type of data; for LIDAR data, current applications still lack an end-to-end neural network processing method; this review examines UAV platforms, sensors, and data processing methods, and according to the development process of certain application fields and current implementation limitations, some predictions are made about possible future development directions. Full article
Show Figures

Figure 1

Figure 1
<p>Article organization and content diagram.</p>
Full article ">Figure 2
<p>UAV platforms and sensors.</p>
Full article ">Figure 3
<p>UAV platforms: (<b>a</b>) Multi-rotor UAV, (<b>b</b>) Fixed-wing UAV, (<b>c</b>) Unmanned Helicopter, (<b>d</b>) VTOL UAV.</p>
Full article ">Figure 4
<p>Sensors carried by UAVs: (<b>a</b>) RGB Camera, (<b>b</b>) Multi-spectral Camera, (<b>c</b>) Hyper-spectral Camera, (<b>d</b>) LIDAR.</p>
Full article ">Figure 5
<p>LIDAR: (<b>a</b>) Mechanical Scanning LIDAR, (<b>b</b>) Solid-state LIDAR.</p>
Full article ">Figure 6
<p>UAV remote sensing applications.</p>
Full article ">Figure 7
<p>UAV remote sensing research in forestry.</p>
Full article ">Figure 8
<p>Symptoms of pine wilt disease.</p>
Full article ">Figure 9
<p>UAV remote sensing research in precision agriculture.</p>
Full article ">Figure 10
<p>Symptoms of huanglongbing (HLB), also known as citrus green disease.</p>
Full article ">Figure 11
<p>Symptoms of grape disease.</p>
Full article ">Figure 12
<p>Symptoms of wheat yellow rust disease.</p>
Full article ">Figure 13
<p>UAV remote sensing research of power lines and accessories.</p>
Full article ">Figure 14
<p>Power lines and tower.</p>
Full article ">Figure 15
<p>Insulators on power lines.</p>
Full article ">Figure 16
<p>Shock absorbers on power lines.</p>
Full article ">Figure 17
<p>UAV remote sensing research on artificial facilities and natural environments.</p>
Full article ">
18 pages, 6639 KiB  
Article
Morphological and Compositional Analysis on Thermal Deposition of Supercritical Aviation Kerosene in Micro Channels
by Ao Sun, Cui Ye, Chenyang Yao, Lifeng Zhang, Ji Mi and Wenjun Fang
Molecules 2023, 28(11), 4508; https://doi.org/10.3390/molecules28114508 - 1 Jun 2023
Cited by 1 | Viewed by 1523
Abstract
The integration of active cooling systems in super or hypersonic aircraft using endothermic hydrocarbon fuels is considered an effective way to relieve the thermal management issues caused by overheating. When the temperature of aviation kerosene exceeds 150 °C, the oxidation reaction of fuel [...] Read more.
The integration of active cooling systems in super or hypersonic aircraft using endothermic hydrocarbon fuels is considered an effective way to relieve the thermal management issues caused by overheating. When the temperature of aviation kerosene exceeds 150 °C, the oxidation reaction of fuel is accelerated, forming insoluble deposits that could cause safety hazards. This work investigates the deposition characteristic as well as the morphology of the deposits formed by thermal-stressed Chinese RP-3 aviation kerosene. A microchannel heat transfer simulation device is used to simulate the heat transfer process of aviation kerosene under various conditions. The temperature distribution of the reaction tube was monitored by an infrared thermal camera. The properties and morphology of the deposition were analyzed by scanning electron microscopy and Raman spectroscopy. The mass of the deposits was measured using the temperature-programmed oxidation method. It is observed that the deposition of RP-3 is highly related to dissolved oxygen content (DOC) and temperature. When the outlet temperature increased to 527 °C, the fuel underwent violent cracking reactions, and the structure and morphology of deposition were significantly different from those caused by oxidation. Specifically, this study reveals that the structure of the deposits caused by short-to-medium term oxidation are dense, which is different from long-term oxidative deposits. Full article
(This article belongs to the Special Issue Advances in the Applications of Surface Enhanced Raman Scattering)
Show Figures

Figure 1

Figure 1
<p>BSED images of the internal surface of the reaction tube after heat transfer of aviation kerosene with a dissolved oxygen content (DOC) of 41.2 ppm. The number “①” to ”⑩” in the figures represent a reaction tube with an average of 10 sections, with directions from “①” to ”⑩” representing the direction of fuel flow in the experiment.</p>
Full article ">Figure 2
<p>ETD images of the internal surface of the reaction tube after heat transfer of aviation kerosene with a DOC of 41.2 ppm. The number “①” to ”⑩” in the figures represent a reaction tube with an average of 10 sections, with directions from “①” to ”⑩” representing the direction of fuel flow in the experiment.</p>
Full article ">Figure 3
<p>BSED image of the internal surface of the reaction tube after heat transfer of aviation kerosene with a DOC of 2.7 ppm. The number “①” to ”⑩” in the figures represent a reaction tube with an average of 10 sections, with directions from “①” to ”⑩” representing the direction of fuel flow in the experiment.</p>
Full article ">Figure 4
<p>ETD images of the internal surface of the reaction tube after heat transfer of aviation kerosene with a DOC of 2.7 ppm. The number “①” to ”⑩” in the figures represent a reaction tube with an average of 10 sections, with directions from “①” to ”⑩” representing the direction of fuel flow in the experiment.</p>
Full article ">Figure 5
<p>Morphology of the internal surfaces of reaction tubes ⑤ and ⑦, and elemental analysis of the selected corresponding area (marked with red “+” in the images).</p>
Full article ">Figure 6
<p>Raman spectra of tube surface after heat transfer by RP-3 with different DOCs.</p>
Full article ">Figure 7
<p>Mass of carbon deposited across the reaction tube after heat transfer by RP-3 with different DOCs.</p>
Full article ">Figure 8
<p>Release rate of CO<sub>2</sub> in different tube sections during temperature-programmed oxidation.</p>
Full article ">Figure 9
<p>Raman spectra of the tube surface at an outlet fuel temperature of 527 °C (flow rate = 0.2 g/s, pressure = 4.0 MPa, running time = 100 min).</p>
Full article ">Figure 10
<p>Mass of carbon deposited at different outlet fuel temperatures (flow rate = 0.2 g/s, pressure = 4.0 MPa, running time = 100 min).</p>
Full article ">Figure 11
<p>Infrared thermographic image of the reaction tube during heat transfer of aviation kerosene at different outlet fuel temperatures (flow rate = 0.2 g/s, pressure = 4.0 MPa).</p>
Full article ">Figure 12
<p>Temperature distribution of the reaction tube monitored by thermal camera.</p>
Full article ">Figure 13
<p>Release rate of CO<sub>2</sub> in different tube sections during temperature-programmed oxidation.</p>
Full article ">Figure 14
<p>Morphology of the reaction tube surface in the oxidation deposition area and elemental analysis of the selected corresponding area (marked with red “+” in images) (outlet fuel temperature = 527 °C, flow rate = 0.2 g/s, pressure = 4.0 MPa, running time = 100 min). (<b>1</b>) Enlarged image of the area marked “1” in the right image. (<b>2</b>) Enlarged image of the area marked “2” in the right image.</p>
Full article ">Figure 15
<p>Morphology of the reaction tube surface in the cracking deposition area and elemental analysis of the selected corresponding area (marked with red “+” in images) (outlet fuel temperature = 527 °C, flow rate = 0.2 g/s, pressure = 4.0 MPa, running time = 100 min).</p>
Full article ">Figure 16
<p>Schematic diagram of the flow heat transfer simulation device: (1) fuel storage tank; (2) high-pressure constant-flow pump; (3) inlet pressure sensor; (4) DC-electric heater; (5) K-type thermocouple; (6) outlet pressure sensor; (7) heat transfer reaction tube; (8) infrared thermometer; (9 and 10) condenser tubes; (11) back-pressure valve; and (12) gas–liquid separator.</p>
Full article ">
20 pages, 10206 KiB  
Article
Region Expansion of a Hyperspectral-Based Mineral Map Using Random Forest Classification with Multispectral Data
by Hideki Tsubomatsu and Hideyuki Tonooka
Minerals 2023, 13(6), 754; https://doi.org/10.3390/min13060754 - 31 May 2023
Cited by 1 | Viewed by 1773
Abstract
Observation images from hyperspectral (HS) sensors on satellites and aircraft can be used to map minerals in greater detail than those from multispectral (MS) sensors. However, the coverage of HS images is much less than that of MS images, so there are often [...] Read more.
Observation images from hyperspectral (HS) sensors on satellites and aircraft can be used to map minerals in greater detail than those from multispectral (MS) sensors. However, the coverage of HS images is much less than that of MS images, so there are often cases where MS images cover the entire area of interest while HS images cover only a part of it. In this study, we propose a new method to more reasonably expand the mineral map of an HS image with an MS image in such cases. The method uses various mineral indices from the MS image and MS sensor’s band values as the input and HS image-based mineral classes as the output. Random forest (RF) two-class classification is then applied iteratively to determine the distribution of each mineral in turn, starting with the minerals that are most consistent with the HS image-based mineral map. The method also involves the correction of misalignment between HS and MS images and the selection of input variables by RF multiclass classification. The method was evaluated in comparison with other methods in the Cuprite area, Nevada, using the Airborne Visible/Infrared Imaging Spectrometer (AVIRIS) and Hyperspectral Imager Suite (HISUI) as HS sensors and the Advanced Spaceborne Thermal Emission and Reflection Radiometer (ASTER) as MS sensors. As a result, all of the evaluated region-expansion methods with an HS–MS image pair, including the proposed method, showed better performance than the method using only an MS image. The proposed method had the highest performance, and the inter-mineral averages of the F1-scores for the overlap and non-overlap areas were 85.98% and 46.46% for the AVIRIS–ASTER image pair and 82.78% and 42.60% for the HISUI–ASTER image pair, respectively. Although the performance in the non-overlap region was lower than in the overlap region, the method showed high precision and high accuracy for almost all minerals, including minerals with only a few pixels. Misalignment between the HS–MS images is a factor that degrades accuracy and requires precise alignment, but the misalignment correction in the proposed method could suppress the effect of misalignment. Validation studies using different regions and different sensors will be carried out in the future. Full article
Show Figures

Figure 1

Figure 1
<p>Processing flow of the proposed method.</p>
Full article ">Figure 2
<p>Cuprite area, Nevada, USA, used as the study area.</p>
Full article ">Figure 3
<p>Comparison of mineral maps obtained from a single AVIRIS image and mineral maps from each of the extension methods using ASTER images: (<b>a</b>) AVIRIS-based map and the extended maps by (<b>b</b>) proposed method, (<b>c</b>) method A, (<b>d</b>) method B, (<b>e</b>) improved HT method, and (<b>f</b>) MS-based method. The white dotted box in (<b>a</b>) indicates the overlap region.</p>
Full article ">Figure 4
<p>Comparison of mineral maps obtained from a single HISUI image and mineral maps from each of the extension methods using ASTER images: (<b>a</b>) HISUI-based map and the extended maps by (<b>b</b>) proposed method, (<b>c</b>) method A, (<b>d</b>) method B, (<b>e</b>) improved HT method, and (<b>f</b>) MS-based method. The white dotted box in (<b>a</b>) indicates the overlap region.</p>
Full article ">Figure 5
<p>Mineral maps for the case of misalignment between AVIRIS and ASTER images: (<b>a</b>) AVIRIS-based map and the extended maps by (<b>b</b>) proposed method, (<b>c</b>) method A, (<b>d</b>) method B, and (<b>e</b>) improved HT method. The white dotted box in (<b>a</b>) indicates the overlap region.</p>
Full article ">
14 pages, 4585 KiB  
Article
A Lightweight Remote Sensing Payload for Wildfire Detection and Fire Radiative Power Measurements
by Troy D. Thornberry, Ru-Shan Gao, Steven J. Ciciora, Laurel A. Watts, Richard J. McLaughlin, Angelina Leonardi, Karen H. Rosenlof, Brian M. Argrow, Jack S. Elston, Maciej Stachura, Joshua Fromm, W. Alan Brewer, Paul Schroeder and Michael Zucker
Sensors 2023, 23(7), 3514; https://doi.org/10.3390/s23073514 - 27 Mar 2023
Cited by 1 | Viewed by 3153
Abstract
Small uncrewed aerial systems (sUASs) have the potential to serve as ideal platforms for high spatial and temporal resolution wildfire measurements to complement aircraft and satellite observations, but typically have very limited payload capacity. Recognizing the need for improved data from wildfire management [...] Read more.
Small uncrewed aerial systems (sUASs) have the potential to serve as ideal platforms for high spatial and temporal resolution wildfire measurements to complement aircraft and satellite observations, but typically have very limited payload capacity. Recognizing the need for improved data from wildfire management and smoke forecasting communities and the potential advantages of sUAS platforms, the Nighttime Fire Observations eXperiment (NightFOX) project was funded by the US National Oceanic and Atmospheric Administration (NOAA) to develop a suite of miniaturized, relatively low-cost scientific instruments for wildfire-related measurements that would satisfy the size, weight and power constraints of a sUAS payload. Here we report on a remote sensing system developed under the NightFOX project that consists of three optical instruments with five individual sensors for wildfire mapping and fire radiative power measurement and a GPS-aided inertial navigation system module for aircraft position and attitude determination. The first instrument consists of two scanning telescopes with infrared (IR) channels using narrow wavelength bands near 1.6 and 4 µm to make fire radiative power measurements with a blackbody equivalent temperature range of 320–1500 °C. The second instrument is a broadband shortwave (0.95–1.7 µm) IR imager for high spatial resolution fire mapping. Both instruments are custom built. The third instrument is a commercial off-the-shelf visible/thermal IR dual camera. The entire system weighs about 1500 g and consumes approximately 15 W of power. The system has been successfully operated for fire observations using a Black Swift Technologies S2 small, fixed-wing UAS for flights over a prescribed grassland burn in Colorado and onboard an NOAA Twin Otter crewed aircraft over several western US wildfires during the 2019 Fire Influence on Regional to Global Environments and Air Quality (FIREX-AQ) field mission. Full article
(This article belongs to the Special Issue Unmanned Aerial Systems and Remote Sensing)
Show Figures

Graphical abstract

Graphical abstract
Full article ">Figure 1
<p>The AWSM two-channel infrared scanner. The sensor telescopes are scanned back and forth across the aircraft flight path, driven by a servo motor (<b>right</b> side). An angular encoder (<b>left</b> side) measures the telescope pointing angle relative to aircraft nadir.</p>
Full article ">Figure 2
<p>Ray-tracing model of the light path through the scanner telescopes (SWIR lens is shown). The vertical line at the lens focal plane represents either the MWIR sensor or the aperture in the SWIR channel. The far-right vertical line represents the SWIR sensor. Blue lines trace the path of incident light rays that are parallel to the lens axis. Red lines trace the path of light arriving from 0.5° off-axis. As shown, the 0.5° off-axis rays either miss the MWIR sensor or are blocked by the SWIR aperture (inset).</p>
Full article ">Figure 3
<p>The AWSM custom-built SWIR camera.</p>
Full article ">Figure 4
<p>Ray-tracing model of the light path through the SWIR camera. The sensor array surface is represented by the thin vertical line on the right side. The red, yellow, green, teal and blue lines represent light incident on the lens surface at −13°, −6.5°, 0°, 6.5° and 13°, respectively. As shown, these rays are sharply focused on the sensor array surface except at the edges, with a linear image aberration less than 1.5%.</p>
Full article ">Figure 5
<p>The AWSM sensors integrated into an S2 UAS payload frame. Top (<b>A</b>) and bottom (<b>B</b>) views of the AWSM system showing the arrangement of the individual sensors and components. Panel (<b>C</b>) shows the system inside the S2 nose cone with the hatch open. The hatch is closed before landing to protect the optics from debris.</p>
Full article ">Figure 6
<p>An S2 UAS carrying an AWSM payload ready for launch, Rabbit Mountain prescribed burn, Boulder County, Colorado, 31 July 2019.</p>
Full article ">Figure 7
<p>AWSM images and scanner data from an S2 UAS flight over a prescribed grassland burn during the active flaming period. The FLIR DUO visible wavelength camera (<b>A</b>) shows diffuse smoke across the area from multiple active fires. The yellow rectangle in (<b>A</b>) defines the area of the corresponding FLIR DUO thermal IR image shown in (<b>B</b>), where numerous fire spots are clearly visible across a burned area with elevated surface temperatures. The grey square in (<b>B</b>) defines the area of the approximately coincident SWIR camera image shown in (<b>C</b>). The blue dots in (<b>B</b>) are an overlay showing the location of fire pixels from the 4 um scanner channel. The 1.6 µm scanner channel measurement is shown in (<b>D</b>) and the sparse scanning resulting from the low altitude is apparent. The blue dotted line in (<b>D</b>) shows the flight track of the S2.</p>
Full article ">Figure 8
<p>The same area of the prescribed grassland fire as shown in <a href="#sensors-23-03514-f007" class="html-fig">Figure 7</a>, but in the post-active fire phase. No significant smoke is seen in the FLIR visible image (<b>A</b>), but the FLIR thermal camera (<b>B</b>) and custom SWIR camera (<b>C</b>) show distinct evidence of residual hot spots in the burned region. The yellow rectangle in (<b>A</b>) defines the area of the corresponding FLIR DUO thermal IR image (<b>B</b>), and the grey square in (<b>B</b>) defines the area of the approximately coincident SWIR camera image (<b>C</b>). The shift in the position of the SWIR camera image relative to the FLIR duo images from <a href="#sensors-23-03514-f007" class="html-fig">Figure 7</a> to <a href="#sensors-23-03514-f008" class="html-fig">Figure 8</a> is due to differences in the timing of image acquisition between the two cameras. The 1.6 µm scanner data are not shown because the lower temperatures were not distinguishable from the background created by scattered sunlight.</p>
Full article ">Figure 9
<p>For integration on an NOAA Twin Otter aircraft, the AWSM instrument suite was split into two parts (<b>A</b>) and installed to use two 11 cm diameter ports (<b>B</b>) in the aft payload bay.</p>
Full article ">Figure 10
<p>Images and scanner data of the Barren Hill wildfire in Idaho on 29 July 2019 observed from the NOAA-Met Twin Otter. (<b>A</b>) Images from the FLIR visible (<b>top</b>) and thermal (<b>middle</b>) cameras and SWIR camera (<b>bottom</b>). (<b>B</b>) The SWIR camera image is the same as shown in Panel A. Corresponding time series of the telescope scanner data (green = 1.6 µm, cyan = 4 µm) are also shown. The scanner time (vertical) axis is scaled to match the camera image.</p>
Full article ">Figure 11
<p>Maps of the Milepost 97 fire in Oregon on 27 July 2019 produced using the (<b>A</b>) SWIR camera, (<b>B</b>) 1.6 µm scanner channel and (<b>C</b>,<b>D</b>) 4 µm scanner channel. The flight took place during daytime, so terrain is clearly visible in the both of the SWIR sensor (<b>A</b>,<b>B</b>) maps. In panel (<b>A</b>), fire containing pixels are shown in red superimposed on a greyscale map. (<b>A</b>) color scale is used in (<b>B</b>) to highlight the contrast in the terrain-reflected sunlight. Detected fire locations appear as blue pixels. The 4 µm sensor (<b>C</b>,<b>D</b>) is blind to reflected sunlight, so non-fire pixels have a uniform background signal intensity (light grey), while fire pixels are clearly visible and the apparent temperature of the fire pixels is represented by the color scale.</p>
Full article ">
24 pages, 9038 KiB  
Article
Analysis of Space-Based Observed Infrared Characteristics of Aircraft in the Air
by Jiyuan Li, Huijie Zhao, Xingfa Gu, Lifeng Yang, Bin Bai, Guorui Jia and Zengren Li
Remote Sens. 2023, 15(2), 535; https://doi.org/10.3390/rs15020535 - 16 Jan 2023
Cited by 9 | Viewed by 3193
Abstract
The space-based infrared observatory of aircraft in the air has the advantages of wide-area, full-time, and passive detection. The optical design parameters for space-based infrared sensors strongly rely on target observed radiation, but there is still a lack of insight into the causes [...] Read more.
The space-based infrared observatory of aircraft in the air has the advantages of wide-area, full-time, and passive detection. The optical design parameters for space-based infrared sensors strongly rely on target observed radiation, but there is still a lack of insight into the causes of aircraft observation properties and the impact of instrument performance. A simulation model of space-based observed aircraft infrared characteristics was constructed for this provision, coupling the aircraft radiance with background radiance and instrument performance effects. It was validated by comparing the model predictions to data from both space-based and ground-based measurements. The validation results reveal the alignment between measurements and model predictions and the dependence of overall model accuracy on the background. Based on simulations, the radiance contributions of aircraft and background are quantitatively evaluated, and the detection spectral window for flying aircraft and its causes are discussed in association with instrumental performance effects. The analysis results indicate that the target-background (T-B) contrast is higher in the spectral ranges where aircraft radiation makes an important contribution. The background radiance plays a significant role overall, while the observed radiance at 2.5–3μm is mainly from skin reflection and plume radiance. The skin-reflected radiation absence affects the model reliability, and its reduction at nighttime reduces the T-B contrast. The difference in T-B self-radiation and the stronger atmospheric attenuation for background contribute to the higher contrast at 2.7 μm compared to the other spectral bands. Full article
(This article belongs to the Special Issue Advances in Thermal Infrared Remote Sensing)
Show Figures

Figure 1

Figure 1
<p>Diagrammatic sketch of aircraft infrared observation using space-based sensors. Schematic CO<sub>2</sub> and H<sub>2</sub>O column density diagrams with altitude are in the upper left corner.</p>
Full article ">Figure 2
<p>The flow chart of evaluation and analysis in this study.</p>
Full article ">Figure 3
<p>Observation line of sight uniform division schematic. <math display="inline"><semantics> <mrow> <mo>Δ</mo> <mi>l</mi> </mrow> </semantics></math> is the length of a slab; <math display="inline"><semantics> <mi>N</mi> </semantics></math> is the total number of sight lines intersecting with the plume; <math display="inline"><semantics> <mi>μ</mi> </semantics></math> and <math display="inline"><semantics> <mi>ν</mi> </semantics></math> are the elevation and azimuth angles relative to the aircraft; P, T and X represent the gas pressure, temperature and species content respectively; <math display="inline"><semantics> <mi>n</mi> </semantics></math> represents the number of stratified layers; <math display="inline"><semantics> <mrow> <mo>Δ</mo> <mi>d</mi> </mrow> </semantics></math> is the spatial sampling interval of LOS; <math display="inline"><semantics> <mrow> <msubsup> <mi>L</mi> <mrow> <mi>B</mi> <mi>B</mi> </mrow> <mi>n</mi> </msubsup> </mrow> </semantics></math> is the blackbody radiance of the n-th slab; <math display="inline"><semantics> <mrow> <msub> <mi>τ</mi> <mi>n</mi> </msub> </mrow> </semantics></math> denotes the transmissivity of the n-th slab.</p>
Full article ">Figure 4
<p>Auxiliary data for simulation, (<b>a</b>) aircraft position (red circle), the green box is selected cloud background area; (<b>b</b>) spectral response functions of B7–B12 and sea surface reflectance; (<b>c</b>) aircraft position and pixel aggregation information for B7–12 images.</p>
Full article ">Figure 4 Cont.
<p>Auxiliary data for simulation, (<b>a</b>) aircraft position (red circle), the green box is selected cloud background area; (<b>b</b>) spectral response functions of B7–B12 and sea surface reflectance; (<b>c</b>) aircraft position and pixel aggregation information for B7–12 images.</p>
Full article ">Figure 5
<p>The comparison of the background and aircraft radiance spectra, (<b>a</b>,<b>b</b>) is the comparison of simulated and measured restored radiance, and (<b>c</b>,<b>d</b>) is the comparison of target and background radiance curves.</p>
Full article ">Figure 6
<p>Comparison of plume measurement and simulation and atmospheric transmittance at 20 m horizontal path.</p>
Full article ">Figure 7
<p>Relative contributions for the body-leaving radiance at 2.5–13 μm. (<b>a</b>–<b>c</b>) are the contribution plots of three spatial resolutions in the daytime; (<b>d</b>–<b>f</b>) are the contribution plots in the nighttime; the blue, red, yellow, and purple areas represent the relative contribution of the background radiance, plume radiance, skin reflected radiance and skin emission radiance, respectively.</p>
Full article ">Figure 8
<p>Relative contributions for the TOA radiance at 2.5–13 μm. (<b>a</b>–<b>c</b>) are the contribution plots of three spatial resolutions in the daytime; (<b>d</b>–<b>f</b>) are the contributions plots in the nighttime; the blue, red, yellow, purple, and green areas represent the relative contribution of the background radiance, plume radiance, skin reflected radiance, skin emission radiance, and atmosphere path radiance respectively.</p>
Full article ">Figure 9
<p>B7–12 radiance comparison of aircraft and background simulated without the skin reflected radiance. The left axis is the radiance, and the right axis is the contrast, where the negative number means that the target radiance is lower than the background radiance.</p>
Full article ">Figure 10
<p>Comparison of target-background contrast ratio in daytime and nighttime.</p>
Full article ">Figure 11
<p>Spectral contrast of target and background at different GSDs of 70–400 m.</p>
Full article ">Figure 12
<p>Spectral contrast of target and background at different MTFs of 0.1–0.3.</p>
Full article ">Figure 13
<p>Target-background contrast and the spectral response functions of VIMS B7–12 at the GSD of 120 m.</p>
Full article ">Figure 14
<p>Contrast and its variation range with different center wavelengths and FWHMs.</p>
Full article ">Figure 15
<p>Comparison of noise equivalent radiance and radiance difference between target and background.</p>
Full article ">Figure 16
<p>The variation range of target background contrast and its standard deviation curve, considering the influence of noise.</p>
Full article ">Figure 17
<p>Atmospheric transmittance from different altitudes to the top of the atmosphere and atmospheric profile of CO<sub>2</sub>, H<sub>2</sub>O, derived from output files of the MODTRAN.</p>
Full article ">
Back to TopTop