Zero calibration equipment for observing and aiming system of missile launcher

Abstract

The utility model provides a missile launcher sighting system zero calibration device, and belongs to the field of missile launcher calibration devices. The problems that a large site is needed for calibration of a missile launcher observing and aiming system, and observation is not easy due to mutual alignment of optical windows are solved. The device comprises a positioning support used for being connected with a tested missile launcher; the collimator is connected with the positioning bracket; an eyepiece and a light source part are arranged at the eyepiece end of the collimator; one end of the light guide arm is connected with the end side, far away from the eyepiece, of the collimator, and the other end of the light guide arm is aligned with a missile launcher observation window; the indicating assembly is detachably installed at the end, close to the sighting window of the missile launcher, of the light guide arm and used for indicating the sighting window of the missile launcher to be aligned with the axis of the collimator. The zero calibration device is mainly used for zero calibration of a missile launcher observing and aiming system.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of missile launcher calibration equipment, in particular, relate to a kind of missile launcher sighting system zero calibration equipment. BACKGROUND

[0002] Missile is accurately installed on the missile launcher positioning datum through positioning pin when missile is launched, and the target is observed and launched through missile launcher sighting system, and then launched. Therefore, the parallelism of the direction of the missile axis on the missile launcher and the missile launcher sighting system is an important factor affecting the hit rate of missile, and the zero calibration process of the missile launcher sighting system has a great impact on the hit rate of missile.

[0003] The traditional calibration method is to install a front mirror in front of the missile axis of the missile launcher, and to place a cross target satisfying resolution at a distance of 200-300m from the missile launcher. By adjusting the missile launcher sighting mirror, the central axis of the sighting system is aligned with the center of the cross target, and then the position of the cross target relative to the center cross of the front mirror scale plate in front of the missile axis is observed through the front mirror, to obtain the angle deviation of the missile axis and the missile launcher sighting system, i.e. the zero deviation of the missile launcher sighting system. However, this detection method has certain shortcomings, i.e. it has certain requirements for detection distance, and needs a relatively large site, which causes great difficulty in observation during detection, and because the site is large, the detection distance needs to be ensured to be relatively far, which is time-consuming and laborious during detection.

[0004] In view of the above, a missile launcher sighting system zero calibration equipment is proposed. SUMMARY

[0005] Therefore, the utility model aims at providing a missile launcher sighting system zero calibration equipment to solve the problems of large site required for calibration of missile launcher sighting system and difficulty in observing mutual alignment of optical windows.

[0006] To achieve the above-mentioned purpose, the utility model adopts the following technical solutions, and provides a missile launcher sighting system zero calibration equipment, comprising:

[0007] Positioning bracket, for connecting the measured missile launcher;

[0008] Parallel light tube, connected with the positioning bracket; the eyepiece end of the parallel light tube is provided with an eyepiece and a light source part;

[0009] Light guide arm, one end connected with the parallel light tube away from the eyepiece end side, and the other end aligned with the missile launcher sighting window;

[0010] Indication assembly, detachably installed on one end of the light guide arm close to the missile launcher sighting window, for indicating the alignment of the missile launcher sighting window and the axis of the parallel light tube.

[0011] Further, the positioning support comprises reinforced carbon fiber rods, and reference surface supports are arranged at two ends of the reinforced carbon fiber rods respectively, and positioning pin seats for connecting the measured missile launcher are arranged on the reference surface supports.

[0012] Further, the positioning pin seats are provided with through holes for connecting the measured missile launcher in the axial direction, and are provided with ball head plungers for positioning in the radial direction.

[0013] Further, reinforcing supports for maintaining the relative positions of the reinforced carbon fiber rods are arranged between the reinforced carbon fiber rods.

[0014] Further, the collimator comprises an eyepiece end and an objective end, and a collimator barrel connecting the eyepiece end and the objective end, the eyepiece end and the objective end are connected with the positioning support, the eyepiece end is connected with the eyepiece and the light source part, and the objective end is connected with the light guide arm.

[0015] Further, the eyepiece end is provided with a target, and the objective end is provided with an optical coupling system.

[0016] Further, the optical coupling system is sequentially provided with a lens one, a lens two, a lens three and a spacer between adjacent lenses in a direction away from the collimator barrel.

[0017] Further, the light guide arm comprises two mirrors and a shell supporting the two mirrors, and the shell is connected with the collimator.

[0018] Further, the two mirrors are arranged at an angle of 90 degrees.

[0019] Further, the shell and the collimator are connected through a quick clamp.

[0020] Beneficial effects:

[0021] The device is fixed on the measured missile launcher through the positioning support, the position of the collimator and the observation window of the measured missile launcher can be observed and adjusted more easily through the indicating assembly, and the missile launcher observation system can be calibrated within a limited range of field through the collimator. BRIEF DESCRIPTION OF DRAWINGS

[0022] The drawings constituting a part of this utility model are used to provide a further understanding of the utility model, and the illustrative embodiments of the utility model and the description thereof are used to explain the utility model, and do not constitute an improper limitation on the utility model. In the drawings:

[0023] Figure 1 It is a whole structure schematic view of the missile launcher observation system zero position calibration device.

[0024] Figure 2 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0025] Figure 3 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0026] Figure 4 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0027] Figure 5 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0028] Figure 6 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0029] Figure 7 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model; Figure 6 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0030] Figure 8 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model; Figure 6 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0031] Figure 9 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0032] Figure 10 The positioning support of the zero position calibration equipment for a missile launcher observation and sighting system is the positioning support shown in the utility model;

[0033] In the figure: positioning support 1; eyepiece and light source part 2; collimator 3; light guide arm 4; indication assembly 5; positioning pin seat 6; left reference surface support 7; reinforced carbon fiber rod 8; carbon fiber rod locking support 9; reinforcing support 10; right reference surface support 11; target pressing ring 12; target 13; eyepiece end light pipe connecting support 14; light pipe barrel 15; light guide end light pipe connecting support 16; lens one 17; spacer one 18; lens two 19; spacer two 20; lens three 21; lens pressing ring 22; quick clamp 23; thin mirror one pressing block 24; shell 25; thin mirror two pressing block 26; thin mirror one 27; thin mirror two 28; ball head plunger 29; missile launcher observation window 30. DETAILED DESCRIPTION

[0034] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present application, but not all the embodiments.

[0035] It should be noted that the descriptions of "left", "right", "left side", "right side", "upper part", "lower part", "top", "bottom" and the like in the present application are all defined based on the position or relationship of the drawings shown, and are only for the convenience of describing the present application and simplifying the description, and are not intended to indicate or imply that the described structure must be constructed and operated in a particular orientation, therefore, it cannot be understood as a limitation on the present application. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0036] In the description of the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection" and "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium, or the communication inside two elements. For ordinary skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0037] With reference to the drawings of the embodiments, a zero calibration device for missile launcher sighting system is provided, comprising:

[0038] A positioning bracket 1 is used to connect the missile launcher to be measured;

[0039] A collimator 3 is connected to the positioning bracket 1; the eyepiece end of the collimator 3 is provided with an eyepiece and a light source part 2;

[0040] A light guide arm 4 is connected to the collimator 3 at one end away from the eyepiece end side, and the other end is aligned with the missile launcher sighting window 30;

[0041] An indicating assembly 5 is detachably mounted on the light guide arm 4 near the end of the missile launcher sighting window 30, and is used to indicate that the missile launcher sighting window 30 is aligned with the axis of the collimator.

[0042] Positioning support 1 is the connection between the axis detection device and the measured equipment through the positioning pin hole, which plays a role in ensuring the repeated installation accuracy of the axis detection device. Eyepiece and light source part 2 can be used for autocollimation detection of collimator 3 and provide light source for collimator 3, and eyepiece is used for observation and alignment. Collimator 3 outputs cross target image of detection reference to the small field optical system of the measured sighting scope, and light guide arm 4 reflects the cross target image emitted by collimator 3 to the small field optical system of the sighting scope through two plane mirrors. Indication assembly 5 can output coaxial red light beam through collimator 1 through the eyepiece, which plays an indicating role when the output image of collimator 1 is aligned with the axis of the measured sighting system. After alignment, indication assembly 5 is removed, and calibration work begins. Indication assembly 5 is a laser indication assembly.

[0043] In the embodiment, positioning support 1 includes reinforced carbon fiber rods 8, and reference surface supports are arranged at both ends of the reinforced carbon fiber rods 8, respectively. The reference surface supports are provided with positioning pin seats 6 for connecting the measured missile launcher.

[0044] The reference surface supports include left reference surface support 7 and right reference surface support 11. The contact surfaces of the left reference surface support 7 and the right reference surface support 11 are provided with adjustable pads, which are used for adjusting the parallelism between the image optical axis output by the collimator and the missile axis formed by the installation reference surface and the positioning pin on the measured missile launcher, observing the sighting window of the measured product, adjusting the installation angle of the sighting system of the measured product, and achieving zero calibration of the sighting system of the missile launcher until the cross target image is located at the cross center of the sighting system of the measured product.

[0045] In the embodiment, positioning pin seats 6 are provided with through holes for connecting the measured missile launcher in the axial direction, and are provided with ball plunger 29 for positioning in the radial direction.

[0046] Ball plunger 29 is provided with two ball plungers 29 in the same radial plane, and the two ball plungers 29 are arranged at an angle of 90°, which is beneficial to the connection with the positioning pin on the measured missile launcher and ensures the repeated positioning accuracy of the equipment.

[0047] In the embodiment, reinforcing supports 10 are arranged between the reinforced carbon fiber rods 8 for maintaining the relative positions of the reinforced carbon fiber rods 8.

[0048] Preferably, three reinforced carbon fiber rods 8 are arranged, and reinforcing support 10 is arranged between the three reinforced carbon fiber rods 8. Reinforcing support 10 is fixed on reinforced carbon fiber rods 8 through carbon fiber rod locking support 9, which reduces the shaking caused by the excessive length of reinforced carbon fiber rods 8 and increases the stability of positioning support 1.

[0049] In the embodiment, the collimator 3 comprises an eyepiece end and an objective end, and a collimator barrel 15 connecting the two ends, the eyepiece end and the objective end are connected with the positioning support 1, the eyepiece end is connected with the eyepiece and light source part 2, and the objective end is connected with the light guide arm 4.

[0050] The eyepiece and light source part 2 provides a viewing port and a light source for the collimator 3. The eyepiece end is fixed with the reinforced carbon fiber rod 8 through the eyepiece end light pipe connecting support 14, and the objective end is fixed with the reinforced carbon fiber rod 8 through the light guide end light pipe connecting support 16.

[0051] In the embodiment, the eyepiece end is provided with a target 13, and the objective end is provided with an optical coupling system.

[0052] The target 13 is a crosshair target, and the target pressing ring 12 fixes the target 13 on the collimator barrel 15. The crosshair target image output by the collimator covers the small field of view optical system of the sighting telescope to be measured, so that the optical axis detection and calibration of the small field of view optical system of the sighting telescope are realized.

[0053] In the embodiment, the optical coupling system is sequentially provided with a lens one 17, a lens two 19, a lens three 21 and a spacer ring between adjacent lenses in a direction away from the collimator barrel 15.

[0054] The spacer ring one 18 is arranged between the lens one 17 and the lens two 19 to adjust the distance between the lens one 17 and the lens two 19, the spacer ring two 20 is arranged between the lens two 19 and the lens three 21 to adjust the distance between the lens two 19 and the lens three 21, and the lens pressing ring 22 is arranged between the lens three 21 and the collimator barrel 15 to fix the lens three 21.

[0055] In the embodiment, the light guide arm 4 comprises two reflectors and a shell 25 supporting the two reflectors, and the shell 25 is connected with the collimator 3.

[0056] The two reflectors are a thin reflector one 27 and a thin reflector two 28, the thin reflector one 27 is fixed at one end of the shell 25 through the thin reflector one pressing block 24, and the thin reflector two 28 is fixed at the other end of the shell 25 through the thin reflector two pressing block 26.

[0057] In the embodiment, the two reflectors are arranged at an angle of 90 degrees.

[0058] In the embodiment, the shell 25 is connected with the collimator 3 through the quick clamp 23.

[0059] The light path is as follows: the target 13 is installed on the collimator, the visible light source irradiates the target 13, the target 13 outputs a target image through the collimator 3, the light path direction is changed through the two reflectors of the light guide arm 4, and finally the light is output from the light guide arm outlet.

[0060] Alignment test: install the indication assembly 5 on the light guide arm, emit the indication laser, and the laser spot is irradiated on the lens of the device to be tested, so that the device has been aligned with the device to be tested, remove the laser indication assembly after alignment, and test.

[0061] Principle of indication assembly 5: the indication assembly 5 is composed of a laser, a power supply, a switch, a shell and the like, the power supply supplies power for the laser indication assembly, and the laser emits the indication laser.

[0062] The above disclosed embodiments of the utility model are only used for helping to set forth the utility model. The embodiments do not describe all the details, and also do not limit the utility model to be only the specific implementation mode. According to the content of the specification, many modifications and changes can be made. The specification selects and specifically describes these embodiments, in order to better explain the principle and practical application of the utility model, so that the technical personnel in the art can well understand and utilize the utility model.

Claims

1. A zero calibration apparatus for a missile launcher collimating system, comprising: The utility model relates to a kind of missile collimating sight, including: Positioning bracket (1) for connecting the missile launcher to be measured; Collimating tube (3) connected with the positioning bracket (1);The eyepiece end of the collimating tube (3) is provided with eyepiece and light source part (2); Light guide arm (4), one end is connected with the collimating tube (3) away from the eyepiece end side, the other end is aligned with the missile launcher observation window (30); Indication assembly (5) is detachably installed in light guide arm (4) near the missile launcher observation window (30) one end, for indicating the missile launcher observation window (30) and collimating tube axis alignment.

2. The zero calibration device for a missile launcher collimating system according to claim 1, characterized in that: The positioning bracket (1) includes reinforced carbon fiber rod (8) and is provided with reference surface support at both ends, respectively, the reference surface support is provided with positioning pin seat (6) for connecting the missile launcher to be measured.

3. The zero calibration device for a missile launcher collimating system according to claim 2, characterized in that: The positioning pin seat (6) is provided with through hole for connecting the missile launcher to be measured along the axial direction, and is provided with ball plunger (29) for positioning along the radial direction.

4. The zero calibration device for a missile launcher collimating system according to claim 2, characterized in that: Several reinforced carbon fiber rods (8) are provided with reinforced support (10) for maintaining their relative position.

5. The zero calibration device for a missile launcher collimating system according to claim 1, wherein: The collimating tube (3) includes eyepiece end and objective end and light tube barrel (15) connected therewith, the eyepiece end and objective end are connected with the positioning bracket (1), the eyepiece end is connected with the eyepiece and light source part (2), and the objective end is connected with the light guide arm (4).

6. The zero calibration device for a missile launcher collimating system according to claim 5, characterized in that: The eyepiece end is provided with target (13), and the objective end is provided with optical coupling system.

7. The zero calibration device for a missile launcher collimating system according to claim 6, characterized in that: The optical coupling system is provided with lens one (17), lens two (19), lens three (21) and spacer between adjacent lenses in sequence along the direction away from the light tube barrel (15).

8. The zero calibration device for a missile launcher collimating system according to claim 1, wherein: The light guide arm (4) includes two mirrors and shell (25) supporting them, and the shell (25) is connected with the collimating tube (3).

9. The zero calibration device for a missile launcher collimating system according to claim 8, characterized in that: Two mirrors are arranged at 90 degrees.

10. The zero calibration apparatus for a missile launcher collimating system according to claim 9, wherein: The shell (25) is connected with the collimating tube (3) by quick clamp (23).

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