CN110500939A - MISSILE LAUNCHING position and guidance axis angle error measuring means and detection method - Google Patents
MISSILE LAUNCHING position and guidance axis angle error measuring means and detection method Download PDFInfo
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- CN110500939A CN110500939A CN201910769807.4A CN201910769807A CN110500939A CN 110500939 A CN110500939 A CN 110500939A CN 201910769807 A CN201910769807 A CN 201910769807A CN 110500939 A CN110500939 A CN 110500939A
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- 238000001514 detection method Methods 0.000 title abstract description 23
- 125000006850 spacer group Chemical group 0.000 claims abstract description 7
- 230000003287 optical effect Effects 0.000 claims description 29
- 238000000034 method Methods 0.000 claims description 8
- 238000010304 firing Methods 0.000 claims description 4
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000011065 in-situ storage Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
- F42B35/02—Gauging, sorting, trimming or shortening cartridges or missiles
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/24—Measuring arrangements characterised by the use of mechanical techniques for measuring angles or tapers; for testing the alignment of axes
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Telescopes (AREA)
Abstract
The device and detection method of MISSILE LAUNCHING position and guidance axis angle separate-blas estimation belong to optics and integrate detection technique field, and in order to solve problems in the prior art, support frame is fixed on one end of plate；Object lens and graticle are arranged in shell, and graticle is arranged at the focal plane of object lens；Pedestal upper end is fixed on shell, and lower end is fixed on plate；Handwheel pressing ring is connected to ring flange one end, and ring flange is fixed in support frame；The ring flange other end is connect with main casing, and main casing upper side light hole is aligned with ring flange inner hole；The inside of main casing is arranged in roof prism, and roof prism is fixed on roof prism seat, and the axial end face of roof prism is compressed by roof prism pressing ring, and roof prism seat pressing ring is compressed in roof prism seat upper end；Right-angle prism is arranged in right-angled edge frame, is fixed as one by right-angle prism spacer ring and right-angle prism pressing ring, inside the whole lower end for being packed into main casing；The light hole of right-angled edge frame is aligned with the light hole of main casing.
Description
Technical field
The present invention relates to it is a kind of can to the device and detection method of MISSILE LAUNCHING position and guidance axis angle separate-blas estimation,
Belong to optics and integrates detection technique field.
Background technique
When missile weapon system MISSILE LAUNCHING position directly influences MISSILE LAUNCHING relative to the angle deviation of guidance axis
Play the initial position of axis and aiming.If the two meets theoretical angular position, guided missile can be made to be located within the scope of STT missile field, had
It is an important factor for influencing Hitting Accuracy of Missile conducive to launching guidance device to guided missile timely and effectively tracking and guidance.
Missile weapon system MISSILE LAUNCHING position directly influences bullet axis when MISSILE LAUNCHING relative to the angle of guidance axis
With the initial position of aiming, for the detection of angle, existing technology is that a preset lens are installed on MISSILE LAUNCHING guide rail, away from
The cross drone for meeting resolution requirement is placed at a distance from MISSILE LAUNCHING guidance 200-300m, by operating launching guidance device
Azimuth pitch mechanism, is directed at guidance axis with cross drone, then is observed by the preset lens eyepiece on shoe, cross drone
Relative to the position of preset lens graticle cross, the angle value of reading is that guided missile installation site is inclined relative to the angle of guidance axis
Difference.The shortcomings that detection method, is there are certain requirements to detecting distance, and to equipping our troops, place election causes difficulty.If cross target
Frame, which is set, to be closer, and not within the focal depth range of launching guidance device telescope objective and preposition endoscope objective lens, human eye can not
See clearly with crossline of sight target, influence detection accuracy.Therefore it needs a kind of in situ detection to set on launching guidance device
Standby and method.
Summary of the invention
The present invention there are certain requirements detecting distance to solve prior art detection method, influence asking for detection accuracy
Topic, proposes the device and detection method of a kind of MISSILE LAUNCHING position and guidance axis angle separate-blas estimation.This method can emit
The guidance device angle deviation in situ for fast and accurately detecting guided missile installation site and guidance axis, gets rid of the limit in detection place
System, improves detection efficiency, while ensure that detection accuracy.The detection method is suitable for all MISSILE LAUNCHING guide rails and guidance axis
Detection of the guided missile installation site relative to guidance axis angle deviation in the launching guidance device of one.
The technical scheme is that
MISSILE LAUNCHING position and guidance axis angle error measuring means, characterized in that it includes guide rail, parallel light tube and two
Parallel optical axis detector three parts；Guide rail includes plate and support frame；Parallel light tube includes object lens, graticle, shell and bracket；
Two parallel optical axis detectors mainly include handwheel pressing ring, ring flange, roof prism pressing ring, roof prism, roof prism seat, ridge
Prism table pressing ring, main casing, right-angled edge frame, right-angle prism, right-angle prism spacer ring and right-angle prism pressing ring；Support frame is fixed on
One end of plate；Object lens and graticle are arranged in shell, and graticle is arranged at the focal plane of object lens；Pedestal upper end is fixed on shell
On body, lower end is fixed on plate；Handwheel pressing ring is connected to ring flange one end, and ring flange is fixed in support frame；Ring flange
The other end is fixedly connected with main casing upper side, and main casing upper side light hole is aligned with ring flange inner hole；Roof prism
It is arranged in inside the upper end of main casing, roof prism is fixed on roof prism seat, and the axial end face of roof prism passes through ridge
Prism pressing ring compresses, and roof prism seat pressing ring is compressed in roof prism seat upper end；Right-angle prism is arranged in right-angled edge frame, leads to
It crosses right-angle prism spacer ring and right-angle prism pressing ring is fixed as one, inside the whole lower end for being packed into main casing；Right-angled edge frame
Light hole is aligned with the light hole of main casing.
Plate is the wedge structure that bottom surface datum level and upper plane have α angle；The α angle and MISSILE LAUNCHING angle phase
Together；The bottom surface of the parallel light tube optical axis and plate is at α angle, parallel with side.
The round groove of γ mark, object of the groove through parallel light tube are carved at the graticle center of axis parallel light tube
The object lens of mirror, two parallel optical axis detectors and launching guidance device telescope image on the graticle of telescope.
MISSILE LAUNCHING position and guidance axis angle deviation detecting method, characterized in that method includes the following steps:
Parallel light tube is screwed on the plate of guide rail by bracket, adjusts the graduation of parallel light tube by step 1
Plate keeps the bottom surface of the parallel light tube optical axis and plate at α angle with electro-optic theodolite observation, parallel with side；
Adjustment right-angled edge frame keeps right-angle prism parallel with roof prism emergent ray；
Step 2, by the Missile Body of the side of the four corners on the plate of guide rail and bottom surface datum level and tested guidance device
The orientation and pitching benchmark of frame, which cooperate, to be fixed；
The ring flange of two parallel optical axis detectors is inserted into support frame by step 3, rotates two parallel optical axis detectors
Make itself and the at angle β degree of vertical line, at this point, two parallel optical axis detector light-emitting windows are aligned with the guidance axis of tested guidance device, rotation
Change hands wheel pressing ring locking；
Whether step 4, the crosshair that graticle is observed by being detected guidance device eyepiece are located at the graticle of parallel light tube
Round groove in, and then judge whether angle MISSILE LAUNCHING position and guidance axis angle deviation meet the requirements.
The beneficial effects of the present invention are: MISSILE LAUNCHING position and guidance axis angle are inclined in MISSILE LAUNCHING guidance device of the present invention
Poor detection device.The apparatus structure is simple, only used parallel light tube, two parallel optical axis detectors (right-angle prism, ridge rib
Mirror) and guide rail, it is looked in the distance the detection of sem observation MISSILE LAUNCHING position and guidance axis angle deviation by launching guidance device.Two is parallel
The right angle roof prism that optical axis detector uses can make collimation telescope axis and guided missile installation site not in same upright position
When (at angle β with vertical direction shape), two plain shaft parallelism detectors are rotated, original target property is still kept, detection is not brought to miss
Difference.Plate uses the straight-line displacement guide rail structure of bottom surface and side as benchmark, realizes the quick and precisely connection with guided missile firing mount,
Collimator tube reticle is combined using cross with circle, and angle deviation can be quickly detected.By above scheme, transmitting is realized
Guidance device is looked in the distance the in situ detection of sem observation MISSILE LAUNCHING position and guidance axis angle deviation, is improved working efficiency, is realized letter
Just, practical, efficient and economic purpose.Scheme is suitable for different guided missile launchers and different guided missiles installs angle α, with
And the different angle β of telescopic central and the guided missile installation site line of centres and vertical direction, there is stronger versatility.The dress
It sets and is formed by type design, have developed model machine, and have passed through army and be applicable in, test effect is preferable.
Detailed description of the invention
Fig. 1 is MISSILE LAUNCHING position of the present invention and guidance axis angle error measuring means schematic diagram.
Fig. 2 is guide rail connection schematic diagram of the present invention.
Fig. 3 is guide rail of the present invention and axes measuring parallel light tube connection schematic diagram.
Fig. 4 is two parallel optical axis detector rotating state diagram of the present invention.
Fig. 5 is two parallel optical axis detector composition schematic diagram of the present invention.
Specific embodiment
As shown in Figure 1, MISSILE LAUNCHING position and guidance axis angle error measuring means comprising guide rail 1, parallel light tube 2
With two parallel optical axis detectors, 3 three parts.
As shown in Fig. 2, guide rail 1 includes plate 1-1 and support frame 1-2, support frame 1-2 is fixed on slotting using two M5 screws
On plate 1-1.
As shown in figure 3, parallel light tube 2 includes object lens 2-1, graticle 2-2, shell 2-3 and bracket 2-4.Object lens 2-1 and point
It draws plate 2-2 to be arranged in shell 2-3, graticle 2-2 is arranged at the focal plane of object lens 2-1.The upper end bracket 2-4 is fixed on shell 2-
On 3, lower end is fixed on plate 1-1.
Plate 1-1 is the wedge structure that bottom surface datum level and upper plane have α angle.The α angle and MISSILE LAUNCHING angle
It is identical.2 optical axis of parallel light tube and the bottom surface of plate 1-1 are at α angle, parallel with side.
The four corners of plate 1-1 are respectively provided with side and bottom surface datum level, and each datum level is connect with guided missile firing mount respectively
Orientation and pitching benchmark cooperation fix.
γ (scribing according to angular deviation specific requirement) mark is carved at the center graticle 2-2 of axis parallel light tube 2
Round groove, object lens 2-1 of the groove through parallel light tube 2, two parallel optical axis detectors 3 and launching guidance device telescope
Object lens image on the graticle 2-2 of telescope, human eye passes through telescope ocular and observes graticle 2-2 cross hairs center and circle
The positional relationship of circle, judges whether the angle deviation of launching guidance device guidance axis and guided missile installation site meets the requirements.If ten
Wordline center is located to be qualified in circle, is otherwise unqualified.
As shown in figure 4, mainly including handwheel pressing ring 3-1, ring flange 3-2, roof prism pressure for two parallel optical axis detectors 3
Enclose 3-3, roof prism 3-4, roof prism seat 3-5, roof prism seat pressing ring 3-6, main casing 3-7, right-angled edge frame 3-8, straight
Angle prism 3-9, right-angle prism spacer ring 3-10 and right-angle prism pressing ring 3-11.Handwheel pressing ring 3-1 is threadedly attached in ring flange
The one end 3-2, and ring flange 3-2 is fixed in support 1-2.The ring flange 3-2 other end and the fixed company of main casing 3-7 upper side
It connects, main casing 3-7 upper side light hole is aligned with ring flange 3-2 inner hole.The upper of main casing 3-7 is arranged in roof prism 3-4
End is internal, and roof prism 3-4 is fixed on roof prism seat 3-5, and the axial end face of roof prism 3-4 passes through roof prism pressing ring
3-3 is compressed, and roof prism seat pressing ring 3-6 is compressed in the roof prism upper end seat 3-5.
Right-angle prism 3-9 is arranged in right-angled edge frame 3-8, passes through right-angle prism spacer ring 3-10 and right-angle prism pressing ring 3-
11 are fixed as one, inside the whole lower end for being packed into main casing 3-7.The light hole of right-angled edge frame 3-8 and leading to for main casing 3-7
Unthreaded hole alignment, is fixed by fastening screw.
As shown in figure 5, after two parallel optical axis detectors 3 are connect with the support frame 1-2 of guide rail 1, it can be by rotating angle of arrival
Spend β.Roof prism 3-4 can make in two parallel optical axis detectors 3 rotation β angular range on detection without influence.
The directional light that parallel light tube 2 issues is incident on roof prism 3-4, then is emitted by right-angle prism 3-9, emergent light warp
The object lens for crossing tested guidance device 4 are imaged on the graticle of object lens focal plane, are observed and are detected by eyepiece.
MISSILE LAUNCHING position and guidance axis angle deviation detecting method, comprising the following steps:
Parallel light tube 2 is screwed on the plate 1-1 of guide rail 1 by step 1 by bracket 2-4, adjusts directional light
The graticle 2-2 of pipe 2 keeps 2 optical axis of parallel light tube and the bottom surface of plate 1-1 at α angle with electro-optic theodolite observation, flat with side
Row.
Adjustment right-angled edge frame 3-8 keeps right-angle prism 3-9 parallel with roof prism 3-4 emergent ray.
Step 2, by the side of the four corners on the plate 1-1 of guide rail 1 and bottom surface datum level and tested guidance device 4
The orientation and pitching benchmark of guided missile firing mount, which cooperate, to be fixed.
The ring flange 3-2 of two parallel optical axis detectors 3 is inserted into support frame 1-2 by step 3, rotates two parallel optical axis
Detector 3 makes itself and the at angle β degree of vertical line, at this point, the aiming of two parallel optical axis detectors, 3 light-emitting window and tested guidance device 4
Axis alignment, rotation hand wheel pressing ring 3-1 locking.
Whether step 4, the crosshair that graticle is observed by being detected 4 eyepiece of guidance device are located at the graduation of parallel light tube 2
In the round groove of plate 2-2, and then judge whether angle MISSILE LAUNCHING position and guidance axis angle deviation meet the requirements.
Claims (4)
1. MISSILE LAUNCHING position and guidance axis angle error measuring means, characterized in that it includes guide rail (1), parallel light tube (2)
With two parallel optical axis detector (3) three parts；
Guide rail (1) includes plate (1-1) and support frame (1-2)；Parallel light tube (2) includes object lens (2-1), graticle (2-2), shell
Body (2-3) and bracket (2-4)；Two parallel optical axis detectors (3) mainly include handwheel pressing ring (3-1), ring flange (3-2), ridge
Prism pressing ring (3-3), roof prism (3-4), roof prism seat (3-5), roof prism seat pressing ring (3-6), main casing (3-7),
Right-angled edge frame (3-8), right-angle prism (3-9), right-angle prism spacer ring (3-10) and right-angle prism pressing ring (3-11)；
Support frame (1-2) is fixed on one end of plate (1-1)；
In shell (2-3), the focal plane in object lens (2-1) is arranged in graticle (2-2) for object lens (2-1) and graticle (2-2) setting
Place；The upper end bracket (2-4) is fixed on shell (2-3), and lower end is fixed on plate (1-1)；
Handwheel pressing ring (3-1) is connected to the one end ring flange (3-2), and ring flange (3-2) is fixed in support frame (1-2)；Flange
Disk (3-2) other end is fixedly connected with main casing (3-7) upper side, main casing (3-7) upper side light hole and ring flange
The alignment of (3-2) inner hole；Roof prism (3-4) is arranged inside the upper end of main casing (3-7), and roof prism (3-4) is fixed on room
On ridge prism table (3-5), the axial end face of roof prism (3-4) is compressed by roof prism pressing ring (3-3), roof prism seat pressure
(3-6) is enclosed to compress in the roof prism seat upper end (3-5)；
Right-angle prism (3-9) setting passes through right-angle prism spacer ring (3-10) and right-angle prism pressing ring in right-angled edge frame (3-8)
(3-11) is fixed as one, inside the whole lower end for being packed into main casing (3-7)；The light hole and main casing of right-angled edge frame (3-8)
The light hole of body (3-7) is aligned.
2. MISSILE LAUNCHING position and guidance axis angle error measuring means according to claim 1, which is characterized in that plate
(1-1) is the wedge structure that bottom surface datum level and upper plane have α angle；The α angle is identical as MISSILE LAUNCHING angle；Directional light
It manages (2) optical axis and the bottom surface of plate (1-1) is at α angle, it is parallel with side.
3. MISSILE LAUNCHING position and guidance axis angle error measuring means according to claim 1, which is characterized in that in axis
It is carved with the round groove of γ mark, object lens (2- of the groove through parallel light tube (2) in center graticle (2-2) of parallel light tube (2)
1), the object lens of two parallel optical axis detectors (3) and launching guidance device telescope image on the graticle of telescope.
4. MISSILE LAUNCHING position and guidance axis angle deviation detecting method, characterized in that method includes the following steps:
Parallel light tube (2) are screwed on the plate (1-1) of guide rail (1) by step 1 by bracket (2-4), and adjustment is flat
The graticle (2-2) of row light pipe (2) makes the bottom surface of parallel light tube (2) optical axis and plate (1-1) at α with electro-optic theodolite observation
Angle, it is parallel with side；
Adjustment right-angled edge frame (3-8) keeps right-angle prism (3-9) parallel with roof prism (3-4) emergent ray；
Step 2, by the side of the four corners on the plate (1-1) of guide rail (1) and bottom surface datum level and tested guidance device (4)
Guided missile firing mount orientation and pitching benchmark cooperation fix；
The ring flange (3-2) of two parallel optical axis detectors (3) is inserted into support frame (1-2) by step 3, rotates two directional lights
Axis detector (3) makes itself and the at angle β degree of vertical line, at this point, two parallel optical axis detector (3) light-emitting windows and tested guidance device
(4) guidance axis alignment, rotation hand wheel pressing ring (3-1) locking；
Whether step 4, the crosshair that graticle is observed by being detected guidance device (4) eyepiece are located at the graduation of parallel light tube (2)
In the round groove of plate (2-2), and then judge whether angle MISSILE LAUNCHING position and guidance axis angle deviation meet the requirements.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910769807.4A CN110500939B (en) | 2019-08-20 | 2019-08-20 | Device and method for detecting deviation of included angle between missile launching position and aiming axis |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910769807.4A CN110500939B (en) | 2019-08-20 | 2019-08-20 | Device and method for detecting deviation of included angle between missile launching position and aiming axis |
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| CN110500939B CN110500939B (en) | 2024-05-24 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113686549A (en) * | 2021-08-04 | 2021-11-23 | 孝感华中精密仪器有限公司 | Binocular microscope detection device and method |
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| CN2314345Y (en) * | 1997-11-12 | 1999-04-14 | 谭自成 | Full functional instrument for surveying plotting instrument |
| CN103759923A (en) * | 2014-01-20 | 2014-04-30 | 湖北航天技术研究院总体设计所 | Collimator parallel optical axis orientation included angle calibration device |
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| CN110500939B (en) | 2024-05-24 |
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