CN110500939B - Device and method for detecting deviation of included angle between missile launching position and aiming axis - Google Patents
Device and method for detecting deviation of included angle between missile launching position and aiming axis Download PDFInfo
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- CN110500939B CN110500939B CN201910769807.4A CN201910769807A CN110500939B CN 110500939 B CN110500939 B CN 110500939B CN 201910769807 A CN201910769807 A CN 201910769807A CN 110500939 B CN110500939 B CN 110500939B
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- 238000000034 method Methods 0.000 title abstract description 9
- 230000003287 optical effect Effects 0.000 claims abstract description 27
- 238000001514 detection method Methods 0.000 claims abstract description 26
- 230000000007 visual effect Effects 0.000 claims description 5
- 210000004209 hair Anatomy 0.000 claims description 2
- 238000009434 installation Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 238000011065 in-situ storage Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Classifications
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- 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
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- 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)
- Telescopes (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The device and the method for detecting the deviation of the included angle between the missile launching position and the aiming axis belong to the technical field of optical integrated detection, and in order to solve the problems in the prior art, a support frame is fixed at one end of an inserting plate; the objective lens and the reticle are arranged in the shell, and the reticle is arranged at the focal plane of the objective lens; the upper end of the bracket is fixed on the shell, and the lower end of the bracket is fixed on the plugboard; the hand wheel pressing ring is connected to one end of the flange plate, and the flange plate is fixed in the support frame; the other end of the flange is connected with the main shell, and the light through hole on the side surface of the upper part of the main shell is aligned with the inner hole of the flange; the roof prism is arranged in the main shell, the roof prism is fixed on the roof prism seat, the axial end face of the roof prism is pressed by the roof prism pressing ring, and the roof prism seat pressing ring is pressed at the upper end of the roof prism seat; the right-angle prism is arranged in the right-angle prism frame, is fixed into a whole through the right-angle prism spacing ring and the right-angle prism pressing ring, and is integrally arranged in the lower end of the main shell; the light-passing holes of the right-angle prism frame are aligned with the light-passing holes of the main shell.
Description
Technical Field
The invention relates to a device and a method for detecting deviation of an included angle between a missile launching position and an aiming axis, and belongs to the technical field of optical integrated detection.
Background
The deviation of the included angle of the missile launching position of the missile weapon system relative to the aiming axis directly influences the initial positions of the missile launching axis and aiming. If the two are in a theoretical included angle position, the missile can be positioned in the range of a missile control field, so that the missile launching guidance device is beneficial to timely and effectively tracking and guiding the missile, and is an important factor affecting the missile hit rate.
The method comprises the steps that an included angle of a missile launching position of a missile weapon system relative to an aiming axis directly influences an initial position of the missile axis and aiming when the missile launches, and for detection of the included angle, a front mirror is arranged on a missile launching guide rail, a cross target meeting resolution requirements is placed at a distance of 200-300m away from the missile launching guide rail, the aiming axis is aligned with the cross target through operating a launching guide device azimuth pitching mechanism, then the front mirror eyepiece on the launching guide rail is used for observing, the cross target is relative to the cross position of a front mirror reticle, and the read angle value is the included angle deviation of the missile installation position relative to the aiming axis. The disadvantage of this detection method is that it has certain requirements on the detection distance, which makes the selection of the site of the army difficult. If the cross target is erected at a relatively short distance, the human eyes cannot see and aim at the cross target clearly without being in the focal depth range of the telescope objective lens of the emission guidance device and the front lens objective lens, and the detection accuracy is affected. There is therefore a need for an apparatus and method that enables in situ detection on an emission guidance device.
Disclosure of Invention
The invention provides a device and a method for detecting the deviation of the included angle between the launching position of a missile and an aiming axis, and aims to solve the problems that the detection accuracy is affected due to certain requirements on the detection distance in the detection method in the prior art. According to the method, the deviation of the included angle between the missile installation position and the aiming axis can be detected in situ rapidly and accurately, the limit of a detection field is eliminated, the detection efficiency is improved, and the detection precision is ensured. The detection method is suitable for detecting the deviation of the included angle of the missile installation position relative to the aiming axis in all missile launching guide rails and the aiming axis integrated launching guide devices.
The technical scheme of the invention is as follows:
The missile launching position and aiming axis included angle deviation detection device is characterized by comprising a guide rail, a collimator and two parallel optical axis detectors; the guide rail comprises a plugboard and a support frame; the collimator comprises an objective lens, a reticle, a shell and a bracket; the two parallel optical axis detectors mainly comprise a hand wheel pressing ring, a flange plate, a roof prism pressing ring, a roof prism seat pressing ring, a main shell, a right-angle prism frame, a right-angle prism spacing ring and a right-angle prism pressing ring; the support frame is fixed at one end of the plugboard; the objective lens and the reticle are arranged in the shell, and the reticle is arranged at the focal plane of the objective lens; the upper end of the bracket is fixed on the shell, and the lower end of the bracket is fixed on the plugboard; the hand wheel pressing ring is connected to one end of the flange plate, and the flange plate is fixed in the support frame; the other end of the flange is fixedly connected with the side surface of the upper part of the main shell, and the light through hole of the side surface of the upper part of the main shell is aligned with the inner hole of the flange; the roof prism is arranged in the upper end of the main shell, the roof prism is fixed on a roof prism seat, the axial end face of the roof prism is pressed by a roof prism pressing ring, and the roof prism seat pressing ring is pressed at the upper end of the roof prism seat; the right-angle prism is arranged in the right-angle prism frame, is fixed into a whole through the right-angle prism spacing ring and the right-angle prism pressing ring, and is integrally arranged in the lower end of the main shell; the light-passing holes of the right-angle prism frame are aligned with the light-passing holes of the main shell.
The plugboard is a wedge-shaped structure with an alpha angle between a bottom surface datum plane and an upper plane; the alpha angle is the same as the missile launching angle; the collimator visual axis forms an angle alpha with the bottom surface of the plugboard and is parallel to the side surface.
A circular dividing line with gamma mark is carved on the center of the dividing plate of the axis collimator, and the dividing line is imaged on the dividing plate of the telescope through the objective lens of the collimator, the two parallel optical axis detectors and the objective lens of the emission guidance device telescope.
The method for detecting the deviation of the included angle between the missile launching position and the aiming axis is characterized by comprising the following steps:
Fixing a collimator on a plugboard of a guide rail through a bracket by using a screw, adjusting a reticle of the collimator, and observing by using a photoelectric theodolite to enable a visual axis of the collimator to form an alpha angle with the bottom surface of the plugboard and to be parallel to the side surface;
Adjusting the right-angle prism frame to enable the right-angle prism to be parallel to emergent rays of the roof prism;
step two, the side surface and bottom surface datum surfaces at four corners on the plugboard of the guide rail are matched and fixed with the azimuth and pitching datum of the missile launcher of the guided device to be detected;
Step three, inserting the flange plates of the two parallel optical axis detectors into the supporting frame, rotating the two parallel optical axis detectors to form a beta angle with a vertical line, aligning the light outlets of the two parallel optical axis detectors with the aiming axis of the guided device to be detected, and rotating the hand wheel pressing ring to lock;
And fourthly, observing whether the cross wire of the reticle is positioned in the circular scribing line of the reticle of the collimator through the eyepiece of the inspected guidance device, and further judging whether the deviation of the included angle between the launching position of the angle missile and the aiming axis meets the requirement.
The beneficial effects of the invention are as follows: the invention relates to a missile launching position and aiming axis included angle deviation detection device in a missile launching guidance device. The device has a simple structure, only uses a collimator, two parallel optical axis detectors (a right-angle prism and a roof prism) and a guide rail, and observes the detection of the deviation of the included angle between the missile launching position and the aiming axis through the launching guidance device telescope. The right-angle roof prism used by the two parallel optical axis detectors can ensure that when the telescope aiming axis and the missile installation position are not in the same vertical position (form a beta angle with the vertical direction), the two optical axis parallelism detectors are rotated, the original target characteristic is still maintained, and no detection error is caused. The flashboard adopts a linear displacement guide rail structure with the bottom surface and the side surface as the reference, so that the quick and accurate connection with the missile launcher is realized, and the collimator reticle adopts the combination of a cross and a circle, so that the included angle deviation can be quickly detected. Through the scheme, the in-situ detection of the deviation of the included angle between the missile launching position and the aiming axis observed by the launching guidance device telescope is realized, the working efficiency is improved, and the purposes of simplicity, practicality, high efficiency and economy are realized. The scheme is suitable for different missile launching devices, different missile installation included angles alpha and different included angles beta between the connecting line of the center of the telescope and the center of the missile installation position and the vertical direction, and has stronger universality. The device is designed and shaped according to the model, a prototype is developed, the device is suitable for troops, and the test effect is good.
Drawings
FIG. 1 is a schematic diagram of a device for detecting deviation of an included angle between a missile launching position and an aiming axis.
Fig. 2 is a schematic view of the rail connection according to the present invention.
Fig. 3 is a schematic diagram showing connection between a guide rail and an axis detection collimator according to the present invention.
Fig. 4 is a schematic diagram showing a rotation state of two parallel optical axis detectors according to the present invention.
FIG. 5 is a schematic diagram showing the composition of two parallel optical axis detectors according to the present invention.
Detailed Description
As shown in figure 1, the missile launching position and aiming axis included angle deviation detection device comprises a guide rail 1, a collimator 2 and two parallel optical axis detectors 3.
As shown in fig. 2, the guide rail 1 comprises a plugboard 1-1 and a supporting frame 1-2, wherein the supporting frame 1-2 is fixed on the plugboard 1-1 by two M5 screws.
As shown in fig. 3, the collimator 2 includes an objective lens 2-1, a reticle 2-2, a housing 2-3, and a holder 2-4. The objective lens 2-1 and the reticle 2-2 are arranged in the housing 2-3, the reticle 2-2 being arranged at the focal plane of the objective lens 2-1. The upper end of the bracket 2-4 is fixed on the shell 2-3, and the lower end is fixed on the plugboard 1-1.
The plugboard 1-1 is a wedge-shaped structure with an alpha angle between a bottom surface datum plane and an upper plane. The alpha angle is the same as the missile launch angle. The visual axis of the collimator 2 forms an angle alpha with the bottom surface of the plugboard 1-1 and is parallel to the side surface.
Four corners of the plugboard 1-1 are respectively provided with a side surface datum surface and a bottom surface datum surface, and each datum surface is respectively matched and fixed with the azimuth and pitching datum of the missile launcher connection.
A circular dividing line marked by gamma (which is carved according to specific requirements of angle deviation) is carved in the center of a dividing plate 2-2 of an axis collimator 2, and the dividing line is imaged on the dividing plate 2-2 of the telescope through an objective lens 2-1 of the collimator 2, two parallel optical axis detectors 3 and an objective lens of a transmitting guidance device telescope, and human eyes observe the position relation between the center of the dividing plate 2-2 cross line and a circle through an eyepiece of the telescope, so that whether the deviation of an included angle between an aiming axis of the transmitting guidance device and the installation position of a missile meets the requirements is judged. If the center of the cross line is positioned in the circle, the cross line is qualified, otherwise, the cross line is unqualified.
As shown in fig. 4, the two parallel optical axis detectors 3 mainly include a hand wheel pressing ring 3-1, a flange 3-2, a roof prism pressing ring 3-3, a roof prism 3-4, a roof prism seat 3-5, a roof prism seat pressing ring 3-6, a main housing 3-7, a right angle prism frame 3-8, a right angle prism 3-9, a right angle prism spacer ring 3-10 and a right angle prism pressing ring 3-11. The hand wheel pressing ring 3-1 is connected with one end of the flange plate 3-2 through threads, and the flange plate 3-2 is fixed in the bracket 1-2. The other end of the flange plate 3-2 is fixedly connected with the side surface of the upper part of the main shell 3-7, and the light through hole of the side surface of the upper part of the main shell 3-7 is aligned with the inner hole of the flange plate 3-2. The roof prism 3-4 is arranged in the upper end of the main shell 3-7, the roof prism 3-4 is fixed on the roof prism seat 3-5, the axial end face of the roof prism 3-4 is tightly pressed by the roof prism pressing ring 3-3, and the roof prism seat pressing ring 3-6 is tightly pressed at the upper end of the roof prism seat 3-5.
The right-angle prism 3-9 is arranged in the right-angle prism frame 3-8, is fixed into a whole through the right-angle prism spacing ring 3-10 and the right-angle prism pressing ring 3-11, and is integrally arranged in the lower end of the main shell 3-7. The light-passing holes of the right-angle prism frame 3-8 are aligned with the light-passing holes of the main shell 3-7 and are fixed by fastening screws.
As shown in fig. 5, after the two parallel optical axis detectors 3 are connected to the support frames 1-2 of the guide rail 1, they can be rotated to reach an angle β. The roof prism 3-4 will rotate the two parallel optical axis detectors 3 by an angle beta without affecting the detection.
The parallel light emitted by the collimator 2 is incident on the roof prism 3-4, then is emitted by the right-angle prism 3-9, and the emitted light is imaged on a reticle of the focal plane of the objective lens through the objective lens of the inspected guidance device 4, and is observed and detected through an eyepiece.
The missile launching position and aiming axis included angle deviation detection method comprises the following steps:
The collimator 2 is fixed on the plugboard 1-1 of the guide rail 1 through the support 2-4 by using screws, the reticle 2-2 of the collimator 2 is adjusted, and the viewing axis of the collimator 2 and the bottom surface of the plugboard 1-1 form an alpha angle and are parallel to the side surface by using a photoelectric theodolite for observation.
The right-angle prism frame 3-8 is adjusted to enable the right-angle prism 3-9 to be parallel to the emergent light of the roof prism 3-4.
And step two, the side surface and bottom surface datum surfaces at four corners on the plugboard 1-1 of the guide rail 1 are matched and fixed with the azimuth and pitching datum of the missile carrier of the guided device 4 to be detected.
Step three, the flange plates 3-2 of the two parallel optical axis detectors 3 are inserted into the supporting frame 1-2, the two parallel optical axis detectors 3 are rotated to form a beta angle with a vertical line, at the moment, the light outlets of the two parallel optical axis detectors 3 are aligned with the aiming axis of the guided device 4 to be detected, and the hand wheel pressing ring 3-1 is rotated to be locked.
And fourthly, observing whether the cross hairs of the reticle are positioned in the circular scribing line of the reticle 2-2 of the collimator 2 through the ocular of the inspected guiding device 4, and further judging whether the deviation of the included angle between the launching position of the angle missile and the aiming axis meets the requirement.
Claims (2)
1. The missile launching position and aiming axis included angle deviation detection device is characterized by comprising a guide rail (1), a collimator (2) and two parallel optical axis detectors (3);
The guide rail (1) comprises an inserting plate (1-1) and a supporting frame (1-2); the collimator (2) comprises an objective lens (2-1), a reticle (2-2), a shell (2-3) and a bracket (2-4); the two parallel optical axis detectors (3) mainly comprise a hand wheel pressing ring (3-1), a flange plate (3-2), a roof prism pressing ring (3-3), a roof prism (3-4), a roof prism seat (3-5), a roof prism seat pressing ring (3-6), a main shell (3-7), a right angle prism frame (3-8), a right angle prism (3-9), a right angle prism spacing ring (3-10) and a right angle prism pressing ring (3-11);
The support frame (1-2) is fixed at one end of the plugboard (1-1);
the objective lens (2-1) and the reticle (2-2) are arranged in the shell (2-3), and the reticle (2-2) is arranged at the focal plane of the objective lens (2-1); the upper end of the bracket (2-4) is fixed on the shell (2-3), and the lower end is fixed on the plugboard (1-1);
The hand wheel pressing ring (3-1) is connected to one end of the flange plate (3-2), and the flange plate (3-2) is fixed in the support frame (1-2); the other end of the flange plate (3-2) is fixedly connected with the side surface of the upper part of the main shell (3-7), and the light through hole of the side surface of the upper part of the main shell (3-7) is aligned with the inner hole of the flange plate (3-2); the roof prism (3-4) is arranged in the upper end of the main shell (3-7), the roof prism (3-4) is fixed on a roof prism seat (3-5), the axial end face of the roof prism (3-4) is tightly pressed by a roof prism pressing ring (3-3), and the roof prism seat pressing ring (3-6) is tightly pressed at the upper end of the roof prism seat (3-5);
the right-angle prism (3-9) is arranged in the right-angle prism frame (3-8), is fixed into a whole through the right-angle prism spacing ring (3-10) and the right-angle prism pressing ring (3-11), and is integrally arranged in the lower end of the main shell (3-7); the light-passing holes of the right-angle prism frame (3-8) are aligned with the light-passing holes of the main shell (3-7);
the plugboard (1-1) is a wedge-shaped structure with an alpha angle between a bottom surface datum plane and an upper plane; the alpha angle is the same as the missile launching angle; the visual axis of the collimator (2) forms an alpha angle with the bottom surface of the plugboard (1-1) and is parallel to the side surface;
A circular scribing line with a gamma mark is carved at the center of a reticle (2-2) of an axis collimator (2), and the scribing line is imaged on the reticle of the telescope through an objective lens (2-1) of the collimator (2), two parallel optical axis detectors (3) and an objective lens of a transmitting guidance device telescope.
2. The detection method based on the missile launching position and aiming axis included angle deviation detection device as claimed in claim 1, characterized by comprising the following steps:
Fixing a collimator (2) on a plugboard (1-1) of a guide rail (1) through a bracket (2-4) by using a screw, adjusting a reticle (2-2) of the collimator (2), and observing by using a photoelectric theodolite to enable a visual axis of the collimator (2) and the bottom surface of the plugboard (1-1) to form an alpha angle which is parallel to the side surface;
the right-angle prism frame (3-8) is adjusted to enable the right-angle prism (3-9) to be parallel to emergent rays of the roof prism (3-4);
step two, the side surface and bottom surface datum surfaces at four corners on the plugboard (1-1) of the guide rail (1) are matched and fixed with the azimuth and pitching datum of the missile carrier of the guided device (4) to be detected;
Step three, inserting the flange plates (3-2) of the two parallel optical axis detectors (3) into the supporting frame (1-2), rotating the two parallel optical axis detectors (3) to form a beta angle with a vertical line, aligning the light outlets of the two parallel optical axis detectors (3) with the aiming axis of the guided device (4) to be detected, and rotating the hand wheel pressing ring (3-1) to lock;
and fourthly, observing whether the cross hair of the reticle is positioned in a circular scribing line of the reticle (2-2) of the collimator (2) through an eyepiece of the guided device (4) to be inspected, and further judging whether the deviation of the included angle between the launching position of the angle missile and the aiming axis meets the requirement.
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| 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 true CN110500939B (en) | 2024-05-24 |
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