CN112896536A - Unmanned aerial vehicle nacelle structure - Google Patents
Unmanned aerial vehicle nacelle structure Download PDFInfo
- Publication number
- CN112896536A CN112896536A CN202110289307.8A CN202110289307A CN112896536A CN 112896536 A CN112896536 A CN 112896536A CN 202110289307 A CN202110289307 A CN 202110289307A CN 112896536 A CN112896536 A CN 112896536A
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- nacelle
- unmanned aerial
- aerial vehicle
- electronic equipment
- nacelle body
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- 210000001015 abdomen Anatomy 0.000 abstract description 8
- 238000009434 installation Methods 0.000 description 13
- 238000012423 maintenance Methods 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Support Of Aerials (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses an unmanned aerial vehicle pod structure, and belongs to the technical field of unmanned aerial vehicles. The invention can decouple the load of the unmanned aerial vehicle and the electronic equipment on the physical structure, and the antennas are symmetrically arranged at the left side and the right side in the nacelle and can be independently hung on the belly. The invention improves the safety distance between the knife-type antenna at the bottom of the nacelle and the ground, and greatly improves the independence and interchangeability of the nacelle.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle nacelle structure.
Background
The nacelle refers to a streamline nacelle which is provided with airborne equipment, electronic equipment or weapons and the like and is hung under an abdomen or wings. The unmanned aerial vehicle electronic pod can decouple the load of the unmanned aerial vehicle and the electronic equipment on the physical structure, so that the matching or the optional installation is realized, and the flexibility of the load of the unmanned aerial vehicle is greatly improved.
The existing large-scale unmanned aerial vehicle pod needs to be hung on an airplane through a hanging device, and the structure is often characterized by large mass and large size in the vertical direction. The multi-metal structure of the large unmanned aerial vehicle pod is the main one, and the special requirements of installing the antenna in the cabin cannot be met. In order to reduce the shielding of the body on a target, the pod is often required to be hung on the belly of the aircraft, but the common pod is usually provided with an antenna to influence the elevation angle of the aircraft during takeoff, so that the requirement of hanging the pod below the belly of the aircraft cannot be met. Therefore, generally, the unmanned aerial vehicle considers that electronic equipment is loaded on two wings of the unmanned aerial vehicle, and the wings are hung in one set respectively, so that redundancy is formed. Or the electronic equipment load is installed in a certain streamline antenna housing following the aircraft belly, and the method has the defects of difficult installation, large assembly gap, difficult maintenance and debugging due to the processing error of the aircraft skin. In order to solve the problem, a novel pod needs to be developed to meet the requirement of an unmanned aerial vehicle platform.
Disclosure of Invention
In view of the above, the present invention provides a pod structure for an unmanned aerial vehicle. This structure can realize dismantling fast to when fixed with unmanned aerial vehicle, have higher installation accuracy and installation effectiveness.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
an unmanned aerial vehicle nacelle structure comprises a nacelle body, wherein the nacelle body comprises an inner frame and a wave-transparent cover coated on the inner frame; fairings are arranged at the head and the tail of the nacelle body; the top of the nacelle body is provided with a lifting lug and an opening, and the opening is provided with a cover plate;
the bottom outside the nacelle body is also provided with a plurality of blade antennas, and the blade antennas are vertical to the bottom surface of the nacelle body; helical antennas are arranged on two sides inside the nacelle body; mounting electronic equipment at a middle position inside the nacelle body; the electronic equipment is arranged at the bottom of the nacelle body through an electronic equipment fixing frame positioned at the bottom of the electronic equipment; an electric connector of the electronic equipment is fixed at the outer top of the nacelle body, and the electronic equipment and the helical antenna are connected through equidistant radio frequency.
Further, the inner frame comprises a cross beam and a plurality of enclosing frames; the plurality of enclosure frames are in a straight line and parallel to each other and fixed through the cross beam.
Furthermore, enclose the frame and be isosceles trapezoid structure, enclose the quantity of frame and be 3 and be parallel to each other, crossbeam fixed connection is adjacent encloses the corresponding extreme point of frame.
Furthermore, each lifting lug of the same pair is respectively positioned at two sides of the top of the same rectangular surrounding frame, and each surrounding frame is provided with a corresponding pair of lifting lugs.
Further, the height of the electronic equipment fixing frame is larger than 10 mm.
Further, the helical antenna comprises a large helical antenna and a small helical antenna; the wave-transparent cover is provided with mounting holes for mounting the spiral antennas, and the positions of the spiral antennas on two sides in the nacelle structure are mutually symmetrical.
Furthermore, the front end face and the rear end face of the nacelle body are provided with locking pins on opposite angles, and locking buckles are arranged on the fairing at positions corresponding to the locking pins.
Furthermore, a conductive plane for installing the knife antenna is arranged at the bottom of the wave-transmitting cover.
Furthermore, the electronic equipment mounting frame is fixed on the enclosing frame.
Furthermore, two side walls of the wave-transparent cover are symmetrically inclined, the included angle between the two side walls is 20 degrees, and the width of the top of the nacelle body is larger than that of the bottom of the nacelle body.
The invention adopts the technical scheme to produce the beneficial effects that:
1. according to the invention, the unmanned aerial vehicle and the electronic equipment load are decoupled on the physical structure through the unmanned aerial vehicle nacelle, so that matching or optional mounting is realized, and the flexibility of the unmanned aerial vehicle load is greatly improved. The nacelle passes through organism structure and lug interconnection, compares whole along with the type and attaches to the ventral, can improve installation effectiveness and installation accuracy greatly, and is little to unmanned aerial vehicle organism structure's dependence, and the nacelle has good interchangeability.
2. The antennas on the left side and the right side of the nacelle structure are symmetrically arranged, so that information acquisition on the left side and the right side of the flight direction is realized.
3. The lifting lug disclosed by the invention not only avoids the shielding of the nacelle information acquisition direction by the machine body, saves the redundancy of hanging the nacelle on the left side and the right side respectively, but also can save the height size of two stages of hanging racks in the standard unmanned aerial vehicle nacelle, greatly improves the safety distance between the knife-shaped antenna at the bottom of the nacelle and the ground, and solves the problem of elevation angle when the aircraft glides and takes off.
4. The pod of the invention, as an independent functional unit, can complete power-up, control and ground debugging only through the top electric connector thereof without disassembling any parts.
5. The fairing of the invention shields certain covering covers under the belly of the unmanned aerial vehicle, the whole pod does not need to be disassembled, the pod fairing can be rapidly disassembled as an independent part, and the influence of the pod on the ground maintenance of the unmanned aerial vehicle is greatly reduced.
6. The cabin structure of the invention can be flexibly adjusted according to the array requirement, the knife-shaped antenna is arranged at the bottom of the cabin body and can be arranged according to the antenna requirement, the large spiral antenna and the small spiral antenna are arranged by attaching the inner walls in the cabin, and the array can be rearranged and adjusted according to the antenna index requirement.
7. The nacelle has good maintainability, the cover is arranged at the upper part of the cabin body, and the accessibility of each antenna and module in the cabin is good, so that the maintenance time is effectively shortened.
8. The lateral wall of the nacelle can be designed and adjusted in inclination angle according to the target condition, the antenna efficiency is greatly improved compared with the vertical installation, and the problem of phase difference caused by the fact that the antenna housing is not parallel to the antenna receiving plane is solved.
Drawings
FIG. 1 is a schematic illustration of an installation of an embodiment of the present invention.
Fig. 2 is an external schematic view of an embodiment of the invention.
Fig. 3 is an internal schematic view of an embodiment of the present invention.
Fig. 4 is a schematic structural view of an inner frame according to an embodiment of the present invention.
In the figure, the nacelle body 1, the belly 2, the nacelle body 3, the fairing 4, the front opening cover 5, the rear opening cover 6, the wave-transparent cover 7, the electric connector 8, the lifting lug 9, the knife antenna 10, the large spiral antenna 11, the small spiral antenna 12, the electronic equipment 13, the cable bracket 14, the cross beam 15 and the enclosure frame are shown.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments.
An unmanned aerial vehicle nacelle structure comprises a nacelle body, wherein the nacelle body comprises an inner frame and a wave-transparent cover coated on the inner frame; fairings are arranged at the head and the tail of the nacelle body; the top of the nacelle body is provided with a lifting lug and an opening, and the opening is provided with a cover plate;
the bottom outside the nacelle body is also provided with a plurality of blade antennas, and the blade antennas are vertical to the bottom surface of the nacelle body; helical antennas are arranged on two sides inside the nacelle body; mounting electronic equipment at a middle position inside the nacelle body; the electronic equipment is arranged at the bottom of the nacelle body through an electronic equipment fixing frame positioned at the bottom of the electronic equipment; an electric connector of the electronic equipment is fixed at the outer top of the nacelle body, and the electronic equipment and the helical antenna are connected through equidistant radio frequency.
Further, the inner frame comprises a cross beam and a plurality of enclosing frames; the plurality of enclosure frames are in a straight line and parallel to each other and fixed through the cross beam.
Furthermore, enclose the frame and be isosceles trapezoid structure, enclose the quantity of frame and be 3 and be parallel to each other, crossbeam fixed connection is adjacent encloses the corresponding extreme point of frame.
Furthermore, each lifting lug of the same pair is respectively positioned at two sides of the top of the same rectangular surrounding frame, and each surrounding frame is provided with a corresponding pair of lifting lugs.
Further, the height of the electronic equipment fixing frame is larger than 10 mm.
Further, the helical antenna comprises a large helical antenna and a small helical antenna; the wave-transparent cover is provided with mounting holes for mounting the spiral antennas, and the positions of the spiral antennas on two sides in the nacelle structure are mutually symmetrical.
Furthermore, the front end face and the rear end face of the nacelle body are provided with locking pins on opposite angles, and locking buckles are arranged on the fairing at positions corresponding to the locking pins.
Furthermore, a conductive plane for installing the knife antenna is arranged at the bottom of the wave-transmitting cover.
Furthermore, the electronic equipment mounting frame is fixed on the enclosing frame.
Furthermore, two side walls of the wave-transparent cover are symmetrically inclined, the included angle between the two side walls is 20 degrees, and the width of the top of the nacelle body is larger than that of the bottom of the nacelle body.
The following is a more specific example:
referring to fig. 1 to 3, in the embodiment, the nacelle lifting lug 8 is connected with the fuselage reinforcing frame of the unmanned aerial vehicle belly 1 through a structural member, and the nacelles are symmetrically installed along the plane where the central axis of the aircraft course is located. The connecting structural member of the nacelle and the airframe is designed according to the actual state of the aircraft reinforcing frame and can bear larger load.
The nacelle structure comprises a nacelle body 2, a blade antenna 9, a large spiral antenna 10, a small spiral antenna 11, electronic equipment 12 and a cable support 13; the nacelle body 2 comprises a fairing 3, a front opening cover 4, a rear opening cover 5, a wave-transparent cover 6, an electric connector 7 and a lifting lug 8.
The bottom of a nacelle body 2 is provided with 5 blade antennas 9 through flanges pre-buried in a wave-transparent cover 6 to form an array, the two sides of the inner wall of the nacelle are symmetrically provided with 4 large spiral antennas 10 and 4 small spiral antennas 11 to form an array, all the antennas are electrically connected with electronic equipment 12 arranged at the bottom in the nacelle through isometric radio-frequency cables, and two cable supports 13 are longitudinally arranged in the nacelle to facilitate the binding of all the cables; a power supply connector 7 and a control connector are arranged in the middle of the upper part of the nacelle to realize data interconnection inside and outside the nacelle;
the pod is in a trapezoidal structure, and mounting planes on two sides of the pod wave-transparent cover 6 are required to be inclined downwards by 10 degrees according to the angle of a target; the large helical antenna 10 and the small helical antenna 11 on the two sides are attached to the inner side of the wave-transparent cover.
The wave-transparent cover 6 is pre-embedded according to the flight envelope of the unmanned aerial vehicle and the vibration impact load, loads such as an antenna and a module are transmitted to the enclosure frame 15, the enclosure frame is a main force-bearing component of the nacelle body 2, wherein the force-bearing main component is divided into the cross beam 14, the enclosure frame 15 and an antenna mounting seat, in order to improve the rigidity of a structural component pre-embedded into the wave-transparent cover, four cross beams 14 and three enclosure frames 15 are rigidly connected by riveting and threaded connection, the cross beam 14 and the enclosure frame 15 form a space force-bearing structure, the section and the strength of the space force-bearing structure can be selected according to the length of the nacelle and the vibration condition of an airplane platform, the cross beam 14 adopts an L-shaped aluminum profile, the enclosure frame 15 adopts a square-shaped aluminum frame, the section has certain rigidity, and the torsional strength and the rigidity of the.
The design of the wave-transparent cover 6 is that firstly, the position of the enclosure frame 15 on the cabin body is determined according to the installation interface of the aircraft platform, and the upper part of the enclosure frame 15 is directly provided with the lifting lug 8 and can be rigidly connected with the unmanned aerial vehicle platform; in order to ensure the installation accuracy of the lifting lugs 8 and the enclosure frame 15, the tool is designed in the embodiment, and the interchangeability of similar nacelles is ensured.
The lifting lugs 8, the lifting lugs 8 and the cabin body are designed in a split mode and are machined through an aluminum ingot machine, and the specific size of each lifting lug 8 can be modified according to the adaptability of an airplane platform interface. The lifting lug 8 is structurally simple and rigidly connected, has light weight and small vertical size, and is an important stressed part for the load of the nacelle body 2. The lug 8 can be interconnected with each cabin section bulkhead frame of unmanned aerial vehicle organism through the structure, has good adaptability to the installation of the nonstandard cabin under the unmanned aerial vehicle ventral.
A front opening cover 4 and a rear opening cover 5 are reserved on the upper plane of the wave-transmitting cover 6, so that the installation, maintenance and debugging of an indoor antenna, electronic equipment 12, a cable and the like are facilitated; a boss is designed at the position of the mounting opening cover of the wave-permeable cover 6, and a waterproof rubber pad is arranged between the opening covers, so that the waterproof requirement of the nacelle is met.
The stainless steel mesh is embedded in the bottom surface of the wave-transmitting cover 6, so that the electric conductivity of the wave-transmitting cover is improved, the stainless steel mesh and the antenna mounting flange are equal electric potential bodies, the grounding of the blade antenna 9 is realized, and meanwhile, the bottom surface of the nacelle is also used as an antenna reflection plate.
The positions of the large helical antenna 10 and the small helical antenna 11 are wave-transmitting planes, through holes are reserved in the wave-transmitting cover 6, transition installation parts are not needed, and the large helical antenna 10 and the small helical antenna 11 can be directly and rigidly fixed outside the cabin by using bolts.
The electronic equipment 12 is arranged at the bottom of the cabin, and when the electronic equipment 12 is arranged, the electronic equipment 12 is erected above the bottom plate of the cabin by more than 10mm through the mounting bracket so as to prevent the electronic equipment module 12 from being soaked in water and facilitate the wiring of the lower part of the electronic equipment 12; in the embodiment, the arrangement length of the helical antenna occupies the length of all the wave-transparent cover 6, and in order to reduce the distance difference between the similar antennas in the cabin and the electronic equipment 12, the electronic equipment module 12 is installed in the middle of the wave-transparent cover of the nacelle, and the length of the radio-frequency cable of the similar antenna is the minimum.
The position of the electric connector 7 needs to be determined according to the unmanned aerial vehicle platform, after pod debugging is completed, the electric connection with the unmanned aerial vehicle platform only needs to be achieved through the aviation plug connector, and ground debugging of the pod can also be achieved through the aviation plug.
Claims (10)
1. An unmanned aerial vehicle nacelle structure comprises a nacelle body and is characterized in that the nacelle body comprises an inner frame and a wave-transparent cover coated on the inner frame; fairings are arranged at the head and the tail of the nacelle body; the top of the nacelle body is provided with a lifting lug and an opening, and the opening is provided with a cover plate;
the bottom outside the nacelle body is also provided with a plurality of blade antennas, and the blade antennas are vertical to the bottom surface of the nacelle body; helical antennas are arranged on two sides inside the nacelle body; mounting electronic equipment at a middle position inside the nacelle body; the electronic equipment is arranged at the bottom of the nacelle body through an electronic equipment fixing frame positioned at the bottom of the electronic equipment; an electric connector of the electronic equipment is fixed at the outer top of the nacelle body, and the electronic equipment and the helical antenna are connected through equidistant radio frequency.
2. The unmanned aerial vehicle pod structure of claim 1, wherein the inner frame comprises a cross beam and a plurality of enclosure frames; the plurality of enclosure frames are in a straight line and parallel to each other and fixed through the cross beam.
3. The unmanned aerial vehicle nacelle structure of claim 1, wherein the enclosure frames are isosceles trapezoid-shaped, the number of the enclosure frames is 3, the enclosure frames are parallel to each other, and the cross beams are fixedly connected with corresponding end points of adjacent enclosure frames.
4. The unmanned aerial vehicle pod structure of claim 2, wherein each lifting lug of a same pair is located on each side of the top of a same rectangular enclosure frame, and each enclosure frame has a corresponding pair of lifting lugs.
5. The unmanned aerial vehicle pod structure of claim 1, wherein the height of the electronics mount is greater than 10 mm.
6. The unmanned aerial vehicle pod structure of claim 1, wherein the helical antenna comprises a large helical antenna and a small helical antenna; the wave-transparent cover is provided with mounting holes for mounting the spiral antennas, and the positions of the spiral antennas on two sides in the nacelle structure are mutually symmetrical.
7. The unmanned aerial vehicle nacelle structure of claim 1, wherein the nacelle body has locking pins at opposite corners on both the front and rear end faces, and locking buckles are provided on the cowling at positions corresponding to the locking pins.
8. The unmanned aerial vehicle pod structure of claim 1, wherein a bottom of the wave-transparent cover is provided with a conductive plane for mounting a blade antenna.
9. The unmanned aerial vehicle pod structure of claim 2, wherein the electronics mount is secured to the enclosure.
10. The unmanned aerial vehicle nacelle structure of claim 1, wherein two side walls of the wave-transparent cover are symmetrically inclined, an included angle between the two side walls is 20 degrees, and the width of the top of the nacelle body is larger than that of the bottom of the nacelle body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110289307.8A CN112896536A (en) | 2021-03-18 | 2021-03-18 | Unmanned aerial vehicle nacelle structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110289307.8A CN112896536A (en) | 2021-03-18 | 2021-03-18 | Unmanned aerial vehicle nacelle structure |
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| Publication Number | Publication Date |
|---|---|
| CN112896536A true CN112896536A (en) | 2021-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110289307.8A Pending CN112896536A (en) | 2021-03-18 | 2021-03-18 | Unmanned aerial vehicle nacelle structure |
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| CN (1) | CN112896536A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116544654A (en) * | 2023-07-05 | 2023-08-04 | 中国电子科技集团公司第二十九研究所 | Integrated flap of airborne nacelle |
| CN116534266A (en) * | 2023-07-06 | 2023-08-04 | 中国电子科技集团公司第二十九研究所 | Airborne high-rigidity and lightweight electronic nacelle body and assembly method |
-
2021
- 2021-03-18 CN CN202110289307.8A patent/CN112896536A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116544654A (en) * | 2023-07-05 | 2023-08-04 | 中国电子科技集团公司第二十九研究所 | Integrated flap of airborne nacelle |
| CN116544654B (en) * | 2023-07-05 | 2023-09-26 | 中国电子科技集团公司第二十九研究所 | Integrated flap of airborne nacelle |
| CN116534266A (en) * | 2023-07-06 | 2023-08-04 | 中国电子科技集团公司第二十九研究所 | Airborne high-rigidity and lightweight electronic nacelle body and assembly method |
| CN116534266B (en) * | 2023-07-06 | 2024-01-05 | 中国电子科技集团公司第二十九研究所 | Airborne high-rigidity and lightweight electronic nacelle body and assembly method |
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