CN104089529A

CN104089529A - Method and equipment for calibrating fighter weapon system by fiber-optic gyroscope

Info

Publication number: CN104089529A
Application number: CN201410218270.XA
Authority: CN
Inventors: 焦锋利; 李平金; 陈远春
Original assignee: Individual
Current assignee: Individual
Priority date: 2014-05-22
Filing date: 2014-05-22
Publication date: 2014-10-08
Anticipated expiration: 2034-05-22
Also published as: CN104089529B

Abstract

The invention provides a method and equipment for calibrating a fighter weapon system by a fiber-optic gyroscope. The equipment comprises an azimuth and posture determining instrument and fighter vertical axis azimuth determining equipment, wherein the azimuth and posture determining instrument comprises an azimuth and posture regulator, a second fiber-optic gyroscope module is mounted on the azimuth and posture regulator, a computer for analyzing azimuth angle data is embedded into the second fiber-optic gyroscope module, an electronic optical aligner and a display are mounted on the second fiber-optic gyroscope module, both an integral solving module of the second fiber-optic gyroscope module and the display are connected with the computer through data transmission interfaces, the computer is connected with an integral solving module of a first fiber-optic gyroscope module through a data transmission interface, and the fighter vertical axis azimuth determining equipment can measure the current vertical axis direction of the fighter and indicate the direction through a cross line of sight, displayed in a level eyepiece. The method and the equipment have the advantages that steps in the process for calibrating fighter weapons can be effectively simplified, the calibrating efficiency can be effectively improved and the affect of natural factors can be prevented.

Description

The method and apparatus that uses fibre optic gyroscope to calibrate fighter plane armament systems

Technical field

The present invention relates to a kind of weapon calibration steps and equipment, specifically a kind of method and apparatus that uses fibre optic gyroscope to calibrate fighter plane armament systems.

Background technology

The armament systems that use in armed helicopter and fixed-wing opportunity of combat before use, change weapon after or pilot when its accuracy is thrown doubt upon, need to calibrate.Existing main calibration steps is for contracting is apart from target plate calibration method, before boresight, first want tens people to coordinate together the horizontal body attitude in top, take horizontal plane as reference, by bracing wire method, determine body orientation again, in whole weapon calibration process, body bearing measurement process and boresight process all exist step complexity loaded down with trivial details, efficiency is low, the shortcoming that needs a large amount of Collaboration work, cause each calibration at least to need 3 to 4 hours, cannot meet modernized war to the requirement of opportunity of combat rapid-action, in boresight process, be easily subject to landform, the impact of the multiple natural cause such as wind-force, the precision of boresight cannot guarantee, cannot meet in field environment the demand of boresight at any time.

Summary of the invention

The object of this invention is to provide a kind of method and apparatus that uses fibre optic gyroscope to calibrate fighter plane armament systems, it determines the azimuth deviation angle of weapon axis or the relative body axis system regulation of sight sight line by high accuracy three axis optical fibre gyro system, and by electron-optical aligner, the azimuth deviation angle of this regulation is calibrated on weapon axis or on sight line, make the angle of deviation of weapon axis or the relative body axis system of sight sight line correct.The method can effectively be simplified step, the lifting calibration efficiency of Fighter Weapons calibration process, do not need the horizontal body in top, do not need heavy huge target plate, only need a people just can complete the calibration of whole opportunity of combat armament systems, during calibration, be not subject to the impact of the natural causes such as landform, wind-force, in field environment, can to armament systems, calibrate whenever and wherever possible.

The present invention for achieving the above object, is achieved through the following technical solutions: a kind of fibre optic gyroscope that uses, to the flat aobvious method of calibrating of fighter plane, comprises the steps:

1. the first optical fibre gyro module is installed on fighter plane body, the first optical fibre gyro module comprises by three optical fibre gyros of three orthogonal space coordinates direction of principal axis of x, y, z setting and corresponding integration resolves module, and the angular velocity information that three optical fibre gyros are measured resolves module through integration to carry out integral operation and can draw three axial angle-datas of current the first optical fibre gyro module;

2. body longitudinal axis position determining device is placed on to body below, measures the orientation attitude of body, measured the cross hair direction showing in the spirit level eyepiece in rear body longitudinal axis position determining device and be body longitudinal axis;

3. orientation attitude is determined to instrument is positioned over body longitudinal axis position determining device anterior, the electron-optical aligner that orientation attitude is determined install on instrument is positioned at the dead ahead of spirit level, orientation attitude determines that the second optical fibre gyro module of installing on instrument comprises that three optical fibre gyros and the corresponding integration identical with the first optical fibre gyro modular structure resolve module, can measure when first three axial angle-data;

4. from the spirit level eyepiece of orientation attitude coordinate measuring apparatus, see and look into, can see that spirit level visual field and electron-optical aligner visual field mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of spirit level, another determines the cross hair of the electron-optical aligner of installing on instrument for orientation attitude, by regulating orientation attitude, determine that the orientation attitude adjuster of instrument is adjusted to the cross hair of electron-optical aligner with the cross hair of spirit level and overlaps, now the sighted direction of electron-optical aligner is parallel with the cross hair direction of spirit level, be body longitudinal axis,

5. after the cross hair of electron-optical aligner and the cross hair of spirit level overlap, press orientation attitude and determine the SR of the second optical fibre gyro module on instrument, now the second optical fibre gyro module is confirmed as identical with the initial relative bearing of the first optical fibre gyro module, make zero in relative deviation azimuth, from then on constantly rise, the first optical fibre gyro module starts the record orientation attitude variation of relative universe coordinate system separately with the second optical fibre gyro module, computer is by calculating the relative attitude angle of deviation data between the first optical fibre gyro module and the second optical fibre gyro module to the first optical fibre gyro module and the orientation attitude variation separately of the second optical fibre gyro module, these relative attitude angle of deviation data are shown on display simultaneously,

6. orientation attitude is determined to instrument moves to flat aobvious dead astern, electron-optical aligner sighted direction is aimed to body dead ahead, by regulating orientation attitude adjuster to regulate the orientation attitude angle of the second optical fibre gyro module, until the predetermined angular between the flat aobvious sight line of the current type of relative attitude data fit showing on display device and the body longitudinal axis, the direction that at this moment direction of the cross hair indication in electron-optical aligner visual field need to be adjusted to for flat aobvious sight line;

7. from the form of electron-optical aligner, observe, can see that Yu Pingxian visual field, electron-optical aligner visual field mutually superposes in the visual field forming and has two cross hairs, one is flat aobvious cross hair, one is the cross hair of electron-optical aligner, by the flat adjusting device that shows self, flat aobvious cross hair is adjusted to the cross hair of electron-optical aligner and is overlapped, now can determine that flat aobvious cross hair direction meets the predetermined angular of the flat aobvious sight line of current type and the body longitudinal axis, completes flat aobvious calibration.

Complete after flat aobvious calibration, by following step, gun calibrated:

8. complete after flat aobvious calibration, gun tube front end at gun is installed borescope, orientation attitude is determined to instrument moves to gun the place ahead, the electron-optical aligner that orientation attitude is determined install on instrument is positioned at the dead ahead of borescope, electron-optical aligner sighted direction is aimed to body dead ahead, by regulating orientation attitude adjuster to regulate the orientation attitude angle of the second optical fibre gyro module, until the current type gun of the relative attitude data fit showing on display device and the predetermined angular between flat showing, at this moment the direction of the cross hair indication in electron-optical aligner visual field is the direction that gun need to be adjusted to,

9. from borescope, can see by borescope visual field and electron-optical aligner visual field and mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of borescope, another is the cross hair of electron-optical aligner, by regulating the angle of gun that the cross hair of borescope is adjusted to the cross hair of electron-optical aligner and is overlapped, the direction that now can determine gun meets current type gun and the predetermined angular between flat showing, and completes gun calibration.

The step of the orientation attitude of measurement body is as follows:

A, the first housing coordinate measuring apparatus in body longitudinal axis position determining device and second housing coordinate measuring apparatus are placed on respectively to organism bottom, the vertical lift masthead end of first housing coordinate measuring apparatus and second housing coordinate measuring apparatus contacts with former and later two longitudinal axis face gauge points of organism bottom respectively, guarantee that the direction that body longitudinal axis position determining device is measured is body longitudinal axis, the spirit level on the spirit level on first housing coordinate measuring apparatus and second housing coordinate measuring apparatus arranges in opposite directions;

B, by adjusting first housing coordinate measuring apparatus, make platform inclination angle and the platform inclination angle on second housing coordinate measuring apparatus on first housing coordinate measuring apparatus all consistent with the inclination angle of body with second housing coordinate measuring apparatus adjusting base separately;

C, the portable plate of spirit level on first housing coordinate measuring apparatus is gone to open mode, and the portable plate of spirit level on second housing coordinate measuring apparatus is gone to shielding status, from first housing coordinate measuring apparatus, in the eyepiece of spirit level, observe the scale position that cross hair aims at second housing coordinate measuring apparatus portable plate, then the portable plate of spirit level on second housing coordinate measuring apparatus is gone to open mode, and the portable plate of spirit level on first housing coordinate measuring apparatus is gone to shielding status, from second housing coordinate measuring apparatus, in the eyepiece of spirit level, observe the scale position that cross hair aims at first housing coordinate measuring apparatus portable plate, repeatedly adjust first housing coordinate measuring apparatus identical with the scale position that the sight line of spirit level on second housing coordinate measuring apparatus aims at the scale position that second housing coordinate measuring apparatus adjusting base separately aims at the sight line of spirit level on first housing coordinate measuring apparatus, determine that the spirit level of first housing coordinate measuring apparatus and the spirit level sighted direction of second housing coordinate measuring apparatus are parallel, platform inclination angle and the platform inclination angle on second housing coordinate measuring apparatus on first housing coordinate measuring apparatus is all consistent with the inclination angle of body simultaneously, the vertical lift masthead end of first housing coordinate measuring apparatus and second housing coordinate measuring apparatus contacts with former and later two longitudinal axis face gauge points of organism bottom respectively, now towards the sighted direction of the spirit level in body the place ahead, be the longitudinal axis of body.

A method of using fibre optic gyroscope to calibrate fighter plane Optic-electronic Stabilization Sight, comprises the steps:

1. the first optical fibre gyro module is installed on fighter plane body, the first optical fibre gyro module forms by resolving module by three optical fibre gyros of three orthogonal space coordinates direction of principal axis of x, y, z setting and corresponding integration, and the angular velocity information that three optical fibre gyros are measured resolves module through integration to carry out integral operation and can draw three axial angle-datas of current the first optical fibre gyro module;

6. orientation attitude is determined to instrument moves to Optic-electronic Stabilization Sight the place ahead, electron-optical aligner sighted direction is aimed to body dead ahead, by regulating orientation attitude adjuster to regulate the orientation attitude angle of the second optical fibre gyro module, until sight line during the current type Optic-electronic Stabilization Sight of the relative attitude data fit zero-bit showing on display device and the predetermined angular between the body longitudinal axis, at this moment the direction of the cross hair indication in electron-optical aligner visual field is the direction that Optic-electronic Stabilization Sight sight line need to be adjusted to;

7. Optic-electronic Stabilization Sight is adjusted to zero-bit, now in the Optic-electronic Stabilization Sight significant screen from driving cabin, observe, can see that electron-optical aligner visual field and Optic-electronic Stabilization Sight visual field mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of Optic-electronic Stabilization Sight, one is the cross hair of electron-optical aligner, adjusting device by Optic-electronic Stabilization Sight self is adjusted to the cross hair of Optic-electronic Stabilization Sight zero-bit with the cross hair of electron-optical aligner and overlaps, sight line when the cross hair direction that now can determine Optic-electronic Stabilization Sight zero-bit meets current type Optic-electronic Stabilization Sight zero-bit and the predetermined angular between the body longitudinal axis, complete Optic-electronic Stabilization Sight calibration.

The step of the orientation attitude of measurement body is as follows:

A method of using fibre optic gyroscope to calibrate fighter plane gun, comprises the steps:

2. orientation attitude is determined to instrument is positioned over flat aobvious dead astern, orientation attitude determines that the second optical fibre gyro module of installing on instrument comprises that three optical fibre gyros and the corresponding integration identical with the first optical fibre gyro modular structure resolve module, can measure when first three axial angle-data, from the eyepiece of electron-optical aligner, see and look into, can see that Yu Pingxian visual field, electron-optical aligner visual field mutually superposes in the visual field forming and has two cross hairs, one is the cross hair of electron-optical aligner, another is flat aobvious cross hair, by regulating orientation attitude, determine that the orientation attitude adjuster of instrument is adjusted to the cross hair of electron-optical aligner with flat aobvious cross hair and overlaps, now the sighted direction of electron-optical aligner is parallel with flat aobvious cross hair direction,

3. after the cross hair of electron-optical aligner overlaps with flat aobvious cross hair, press orientation attitude and determine the SR of the second optical fibre gyro module on instrument, now the second optical fibre gyro module is confirmed as identical with the initial relative bearing of the first optical fibre gyro module, make zero in relative deviation azimuth, from then on constantly rise, the first optical fibre gyro module starts the record orientation attitude variation of relative universe coordinate system separately with the second optical fibre gyro module, computer is by calculating the relative attitude angle of deviation data between the first optical fibre gyro module and the second optical fibre gyro module to the first optical fibre gyro module and the orientation attitude variation separately of the second optical fibre gyro module, these relative attitude angle of deviation data are shown on display simultaneously,

4. at the gun tube front end of gun, borescope is installed, orientation attitude is determined to instrument moves to gun the place ahead, the electron-optical aligner that orientation attitude is determined install on instrument is positioned at the dead ahead of borescope, electron-optical aligner sighted direction is aimed to body dead ahead, by regulating orientation attitude adjuster to regulate the orientation attitude angle of the second optical fibre gyro module, until the predetermined angular between the current type gun of the relative attitude data fit showing on display device and the body longitudinal axis, at this moment the direction of the cross hair indication in electron-optical aligner visual field is the direction that gun need to be adjusted to,

5. from borescope, can see by borescope visual field and electron-optical aligner visual field and mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of borescope, another is the cross hair of electron-optical aligner, by regulating the angle of gun that the cross hair of borescope is adjusted to the cross hair of electron-optical aligner and is overlapped, the direction that now can determine gun meets the predetermined angular between current type gun and the body longitudinal axis, completes gun calibration.

The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems, comprise that orientation attitude determines instrument and body longitudinal axis position determining device, orientation attitude determines that instrument comprises orientation attitude adjuster, the second optical fibre gyro module is installed on orientation attitude adjuster, the second optical fibre gyro module is built-in for analyzing the computer of orientation angles data, in the second optical fibre gyro module, electron-optical aligner and display are installed, the integration of the second optical fibre gyro module resolves module and all by data transmission interface, is connected with computer with display, computer resolves module by data transmission interface with the integration of the first optical fibre gyro module and is connected, orientation attitude adjuster can regulate the attitude angle of the second optical fibre gyro module, body longitudinal axis position determining device can be measured the current longitudinal axis of body, and indicate this direction by the cross hair showing in spirit level eyepiece.Described orientation attitude adjuster comprises an x shaft angle position platform, a y shaft angle position platform, a z axle turntable, a z axle lifting platform and an x axle translation stage, and an x shaft angle position platform, a y shaft angle position platform, a z axle turntable, a z axle lifting platform and an x axle translation stage are installed on regulator bracket.Body longitudinal axis position determining device comprises first housing longitudinal axis measurement instrument and second housing longitudinal axis measurement instrument, first housing longitudinal axis measurement instrument and second housing longitudinal axis measurement instrument include adjusting base, mounting platform on adjusting base, the vertical lift bar vertical with platform is installed on platform, inclinator and spirit level, vertical lift bar can be along the vertical direction lifting of platform, inclinator can display platform inclination angle, the axis of sighting of spirit level is parallel with platform, the spirit level of installing on the platform of the spirit level of installing on the platform of first housing longitudinal axis measurement instrument and second housing longitudinal axis measurement instrument arranges in opposite directions, first housing longitudinal axis measurement instrument and the axis of sighting of the spirit level of second housing longitudinal axis measurement instrument equate with the distance between vertical lift bar separately, object lens one end of each spirit level all arranges and spirit level objective end can be covered or unlimited portable plate, portable plate is provided with scale away from the one side of spirit level object lens.Described adjusting base comprises the 2nd x shaft angle position platform, the 2nd y shaft angle position platform, the 2nd z axle turntable, the 2nd z axle lifting platform and the 2nd x axle translation stage, and the 2nd x shaft angle position platform, the 2nd y shaft angle position platform, the 2nd z axle turntable, the 2nd z axle lifting platform and the 2nd x axle translation stage are installed on base.

The invention has the advantages that: the azimuth deviation angle of determining weapon axis or the relative body axis system regulation of sight sight line by high accuracy three axis optical fibre gyro system, and by electron-optical aligner, the azimuth deviation angle of this regulation is calibrated on weapon axis or on sight line, make the angle of deviation of weapon axis or the relative body axis system of sight sight line correct, the method can effectively be simplified the step of Fighter Weapons calibration process, promote calibration efficiency, do not need the horizontal body in top, do not need heavy huge target plate, only need a people just can complete the calibration of whole opportunity of combat armament systems, during calibration, be not subject to landform, the impact of the natural causes such as wind-force, in field environment, can to armament systems, calibrate whenever and wherever possible, also can realize on motion carrier armament systems are calibrated, be not subject to the own motion effects of carrier etc.

Accompanying drawing explanation

Fig. 1 is the method schematic diagram that use fibre optic gyroscope of the present invention is calibrated fighter plane armament systems; State while determining that for orientation attitude instrument is placed in position, flat aobvious dead astern shown in figure;

Fig. 2 is the method schematic diagram that use fibre optic gyroscope of the present invention is calibrated fighter plane armament systems; State while determining that for orientation attitude instrument is placed in Optic-electronic Stabilization Sight forward position shown in figure;

Fig. 3 is the method schematic diagram that use fibre optic gyroscope of the present invention is calibrated fighter plane armament systems; State while determining that for orientation attitude instrument is placed in gun forward position shown in figure;

Fig. 4 is structure and the annexation schematic diagram that in use fibre optic gyroscope of the present invention equipment that fighter plane armament systems are calibrated, orientation attitude is determined instrument and the first optical fibre gyro module;

Fig. 5 is that in use fibre optic gyroscope of the present invention equipment that fighter plane armament systems are calibrated, orientation attitude is determined the contour structures schematic diagram that instrument is connected with the first optical fibre gyro module;

Fig. 6 is the structural representation of body longitudinal axis position determining device of the present invention;

Fig. 7 is the use status architecture schematic diagram of the present invention while using body longitudinal axis position determining device to determine body longitudinal axis orientation.

The specific embodiment

Embodiment mono-:

In the time of need to be to flat aobvious calibration in fighter plane armament systems, adopt following method to calibrate:

A kind of fibre optic gyroscope that uses of the present invention, to the flat aobvious method of calibrating of fighter plane, comprises the steps:

1. the first optical fibre gyro module 1 is installed on fighter plane body 3, the first optical fibre gyro module 1 comprises by three optical fibre gyros of three orthogonal space coordinates direction of principal axis of x, y, z setting and corresponding integration resolves module, and the angular velocity information that three optical fibre gyros are measured resolves module through integration to carry out integral operation and can draw 1 three axial angle-datas of current the first optical fibre gyro module;

2. body longitudinal axis position determining device 2 is placed on to body 3 belows, measures the orientation attitude of body 3, measured the cross hair direction showing in spirit level 5 eyepieces in rear body longitudinal axis position determining device 2 and be body 3 longitudinal axis;

3. orientation attitude is determined to instrument is positioned over body longitudinal axis position determining device 2 the place aheads, the electron-optical aligner 4 that orientation attitude is determined install on instrument is positioned at the dead ahead of spirit level 5, orientation attitude determines that the second optical fibre gyro module 6 of installing on instrument comprises that three optical fibre gyros and the corresponding integration identical with the first optical fibre gyro module 1 structure resolve module, can measure when first three axial angle-data;

4. from spirit level 5 eyepieces of orientation attitude coordinate measuring apparatus, see and look into, can see that spirit level 5 visual fields and electron-optical aligner 4 visual fields mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of spirit level 5, another determines the cross hair of the electron-optical aligner 4 of installing on instrument for orientation attitude, by regulating orientation attitude, determine that the orientation attitude adjuster 7 of instrument is adjusted to the cross hair of electron-optical aligner 4 with the cross hair of spirit level 5 and overlaps, now the sighted direction of electron-optical aligner 4 is parallel with the cross hair direction of spirit level 5, be body 3 longitudinal axis,

5. after the cross hair of electron-optical aligner 4 overlaps with the cross hair of spirit level 5, press orientation attitude and determine the SR of the second optical fibre gyro module 6 on instrument, now the second optical fibre gyro module 6 is confirmed as identical with the initial relative bearing of the first optical fibre gyro module 1, make zero in relative deviation azimuth, from then on constantly rise, the first optical fibre gyro module 1 starts the record orientation attitude variation of relative universe coordinate system separately with the second optical fibre gyro module 6, computer is by calculating the relative attitude angle of deviation data between the first optical fibre gyro module 1 and the second optical fibre gyro module 6 to the first optical fibre gyro module 1 and the orientation attitude variation separately of the second optical fibre gyro module 6, these relative attitude angle of deviation data are shown on display 32 simultaneously,

6. orientation attitude is determined to instrument moves to flat aobvious 8 dead asterns, electron-optical aligner 4 sighted directions are aimed to body 3 dead aheads, by regulating orientation attitude adjuster 7 to regulate the orientation attitude angle of the second optical fibre gyro module 6, until the predetermined angular between the flat aobvious sight line of the current type of relative attitude data fit showing on display device 32 and the body longitudinal axis, the direction that at this moment direction of the cross hair indication in electron-optical aligner 4 visual fields need to be adjusted to for flat aobvious sight line;

7. from the form of electron-optical aligner 4, observe, can see that electron-optical aligner 4 visual fields and flat aobvious 8 visual fields mutually superpose in the visual field forming and have two cross hairs, one is flat aobvious 8 cross hair, one is the cross hair of electron-optical aligner 4, by flat aobvious 8 self adjusting devices, flat aobvious 8 cross hair is adjusted to the cross hair of electron-optical aligner 4 and is overlapped, now can determine that flat aobvious 8 cross hair direction meets the predetermined angular of the flat aobvious sight line of current type and the body longitudinal axis, completes flat aobvious 8 calibrations.

Complete after flat aobvious calibration, can to gun, calibrate by following step:

8. complete after flat aobvious calibration, gun tube front end at gun 10 is installed borescope 29, orientation attitude is determined to instrument moves to gun 10 the place aheads, the electron-optical aligner 4 that orientation attitude is determined install on instrument is positioned at the dead ahead of borescope 29, electron-optical aligner 4 sighted directions are aimed to body 3 dead aheads, by regulating orientation attitude adjuster 7 to regulate the orientation attitude angle of the second optical fibre gyro module 6, until the current type gun of relative attitude data fit showing on display device 32 and the predetermined angular between flat showing, at this moment the direction of the cross hair indication in electron-optical aligner 4 visual fields is the direction that gun need to be adjusted to,

9. from borescope 29, can see by borescope 29 visual fields and electron-optical aligner 4 visual fields and mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of borescope 29, another is the cross hair of electron-optical aligner 4, by regulating the angle of gun 10 that the cross hair of borescope 29 is adjusted to the cross hair of electron-optical aligner 4 and is overlapped, the direction that now can determine gun 10 meets current type gun and the predetermined angular between flat showing, and completes gun 10 calibrations.

The borescope 29 that the present invention adopted in the experimental stage is straight-9WA borescope, in actual use, can select supporting borescope to use according to type.

The present invention, when measuring body 3 orientation attitude, is to improve to measure efficiency, specialized designs body longitudinal axis position determining device 2, use the step of orientation attitude of this device measuring body as follows:

A, the first housing coordinate measuring apparatus 11 in body longitudinal axis position determining device 2 and second housing coordinate measuring apparatus 12 are placed on respectively to body 3 bottoms, vertical lift bar 13 tops of first housing coordinate measuring apparatus 11 and second housing coordinate measuring apparatus 12 contact with former and later two longitudinal axis face gauge points of body 3 bottoms respectively, guarantee that the direction that body longitudinal axis position determining device 2 is measured is body 3 longitudinal axis, the spirit level 5 on first housing coordinate measuring apparatus 11 arranges in opposite directions with the spirit level 5 on second housing coordinate measuring apparatus 12;

B, by adjusting first housing coordinate measuring apparatus 11, make platform 15 inclination angles and platform 15 inclination angles on second housing coordinate measuring apparatus 12 on first housing coordinate measuring apparatus 11 all consistent with the inclination angle of body 3 with second housing coordinate measuring apparatus 12 adjusting base 14 separately;

C, the portable plate 16 of spirit level 5 on first housing coordinate measuring apparatus 11 is gone to open mode, and the portable plate 16 of spirit level 5 on second housing coordinate measuring apparatus 12 is gone to shielding status, from first housing coordinate measuring apparatus 11, in the eyepiece of spirit level 5, observe the scale position that cross hair aims at second housing coordinate measuring apparatus 12 portable plates 16, then the portable plate 16 of spirit level 5 on second housing coordinate measuring apparatus 12 is gone to open mode, and the portable plate 16 of spirit level 5 on first housing coordinate measuring apparatus 11 is gone to shielding status, from second housing coordinate measuring apparatus 12, in the eyepiece of spirit level 5, observe the scale position that cross hair aims at first housing coordinate measuring apparatus 11 portable plates 16, repeatedly adjust first housing coordinate measuring apparatus 11 identical with the scale position that the sight line of spirit level 5 on second housing coordinate measuring apparatus 12 aims at the scale position that second housing coordinate measuring apparatus 12 adjusting base 14 separately aims at the sight line of spirit level 5 on first housing coordinate measuring apparatus 11, determine that the spirit level 5 of first housing coordinate measuring apparatus 11 and spirit level 5 sighted directions of second housing coordinate measuring apparatus 12 are parallel, platform 15 inclination angles and platform 15 inclination angles on second housing coordinate measuring apparatus 12 on first housing coordinate measuring apparatus 11 are all consistent with the inclination angle of body 3 simultaneously, vertical lift bar 13 tops of first housing coordinate measuring apparatus 11 and second housing coordinate measuring apparatus 12 contact with former and later two longitudinal axis face gauge points of body 3 bottoms respectively, now towards the sighted direction of the spirit level 5 in body 3 the place aheads, be the longitudinal axis of body 3.

The method of the orientation attitude of above-mentioned measurement body 3 does not need to push up in advance flat body attitude, after opportunity of combat is landed, body 3 tilts and arbitrarily angledly all can measure, be applicable to various field environments, measuring process has had significantly compared with the conventional method to be simplified, and single can completing, and is conducive to improve measurement efficiency, this measuring method is not subject to natural environment influence simultaneously, and accuracy is high.

Embodiment bis-:

In the time of need to calibrating the Optic-electronic Stabilization Sight in fighter plane armament systems, adopt following method to calibrate:

A kind of method of using fibre optic gyroscope to calibrate fighter plane Optic-electronic Stabilization Sight of the present invention, comprises the steps:

1. the first optical fibre gyro module 1 is installed on fighter plane body 3, the first optical fibre gyro module 1 forms by resolving module by three optical fibre gyros of three orthogonal space coordinates direction of principal axis of x, y, z setting and corresponding integration, and the angular velocity information that three optical fibre gyros are measured resolves module through integration to carry out integral operation and can draw 1 three axial angle-datas of current the first optical fibre gyro module;

6. orientation attitude is determined to instrument moves to Optic-electronic Stabilization Sight 9 the place aheads, electron-optical aligner 4 sighted directions are aimed to body 3 dead aheads, by regulating orientation attitude adjuster 7 to regulate the orientation attitude angle of the second optical fibre gyro module 6, until sight line during the current type Optic-electronic Stabilization Sight of the relative attitude data fit zero-bit showing on display device 32 and the predetermined angular between the body longitudinal axis, at this moment the direction of the cross hair indication in electron-optical aligner 4 visual fields is the direction that Optic-electronic Stabilization Sight sight line need to be adjusted to;

7. Optic-electronic Stabilization Sight 9 is adjusted to zero-bit, now in the Optic-electronic Stabilization Sight significant screen from driving cabin, observe, can see that electron-optical aligner 4 visual fields and Optic-electronic Stabilization Sight 9 visual fields mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of Optic-electronic Stabilization Sight 9, one is the cross hair of electron-optical aligner 4, adjusting device by Optic-electronic Stabilization Sight 9 self is adjusted to the cross hair of Optic-electronic Stabilization Sight 9 zero-bits with the cross hair of electron-optical aligner 4 and overlaps, sight line when the cross hair direction that now can determine Optic-electronic Stabilization Sight 9 zero-bits meets current type Optic-electronic Stabilization Sight zero-bit and the predetermined angular between the body longitudinal axis, complete Optic-electronic Stabilization Sight 9 calibrations.

Complete after Optic-electronic Stabilization Sight calibration, can to other weapons such as guns, calibrate according to the cross hair of Optic-electronic Stabilization Sight, calibration steps is identical with embodiment mono-.

The present invention, when measuring body 3 orientation attitude, is to improve to measure efficiency, specialized designs body longitudinal axis position determining device 2, use the step of orientation attitude of this device measuring body 3 as follows:

Embodiment tri-:

Determining under the errorless state of flat aobvious boresight direction, in the time of need to calibrating the gun in fighter plane armament systems, adopting following method to calibrate:

A kind of method of using fibre optic gyroscope to calibrate fighter plane gun of the present invention, comprises the steps:

2. orientation attitude is determined to instrument is positioned over flat aobvious 8 dead asterns, orientation attitude determines that the second optical fibre gyro module 6 of installing on instrument comprises that three optical fibre gyros and the corresponding integration identical with the first optical fibre gyro module 1 structure resolve module, can measure when first three axial angle-data, from the eyepiece of electron-optical aligner 4, see and look into, can see that electron-optical aligner 4 visual fields and flat aobvious 8 visual fields mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of electron-optical aligner 4, another is flat aobvious 8 cross hair, by regulating orientation attitude, determine that the orientation attitude adjuster 7 of instrument is adjusted to the cross hair of electron-optical aligner 4 with flat aobvious 8 cross hair and overlaps, now the sighted direction of electron-optical aligner 4 is parallel with flat aobvious 8 cross hair direction,

3. after the cross hair of electron-optical aligner 4 overlaps with flat aobvious 8 cross hair, press orientation attitude and determine the SR of the second optical fibre gyro module 6 on instrument, now the second optical fibre gyro module 6 is confirmed as identical with the initial relative bearing of the first optical fibre gyro module 1, make zero in relative deviation azimuth, from then on constantly rise, the first optical fibre gyro module 1 starts the record orientation attitude variation of relative universe coordinate system separately with the second optical fibre gyro module 6, computer is by calculating the relative attitude angle of deviation data between the first optical fibre gyro module 1 and the second optical fibre gyro module 6 to the first optical fibre gyro module 1 and the orientation attitude variation separately of the second optical fibre gyro module 6, these relative attitude angle of deviation data are shown on display 32 simultaneously,

4. at the gun tube front end of gun 10, borescope 29 is installed, orientation attitude is determined to instrument moves to gun 10 the place aheads, the electron-optical aligner 4 that orientation attitude is determined install on instrument is positioned at the dead ahead of borescope 29, electron-optical aligner 4 sighted directions are aimed to body 3 dead aheads, by regulating orientation attitude adjuster 7 to regulate the orientation attitude angle of the second optical fibre gyro module 6, until the current type gun of relative attitude data fit showing on display device 32 and the predetermined angular between the body longitudinal axis, at this moment the direction of the cross hair indication in electron-optical aligner 4 visual fields is the direction that gun need to be adjusted to,

5. from borescope 29, can see by borescope 29 visual fields and electron-optical aligner 4 visual fields and mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of borescope 29, another is the cross hair of electron-optical aligner 4, by regulating the angle of gun 10 that the cross hair of borescope 29 is adjusted to the cross hair of electron-optical aligner 4 and is overlapped, the direction that now can determine gun 10 meets the predetermined angular between current type gun and the body longitudinal axis, completes gun 10 calibrations.

This embodiment is determining under the errorless state of flat aobvious boresight direction, the method for gun 10 being calibrated according to flat aobvious 8 cross hair.In addition, determining under the errorless state of flat aobvious boresight direction, also can to other air weapon equipment such as Optic-electronic Stabilization Sight 9 grades, calibrate according to flat aobvious 8 cross hair, in like manner, cross hair in the time of also can be according to Optic-electronic Stabilization Sight 9 zero-bit under the errorless state of boresight direction when determining Optic-electronic Stabilization Sight zero-bit to gun 10, flat aobvious 8 and other air weapon equipment calibrate, calibration steps is identical with this embodiment principle.

The calibration steps of other weapons such as the rocket launcher carrying in opportunity of combat, boat rifle, guided missile hanger is identical with the gun calibration steps in the various embodiments described above, and in addition, the method also can be calibrated the various weapon equipment such as warship canon on naval vessels.

The present invention adopts the first optical fibre gyro module 1 and the second optical fibre gyro module 6 to do relative bearing attitude measurement scheme, can realize on motion carrier and measuring, be not subject to the motion effects of carrier own, such as calibrating various weapon equipment (opportunity of combat, warship canon etc.) on naval vessel under sail, not affected by ship motion.

The order of sight calibration or weapon calibration is exactly will be sight line or weapon boresighting on the misalignment angle of relative body longitudinal axis a certain regulation on body orientation attitude frame of reference.The misalignment of axe angle of weapon is to calculate according to trajectory shooting feature and weapon installation site on body, and this is the given value that can calculate out.Every kind of type has fixing housing construction, every kind of weapon or sight to have fixing installation site, so the weapon of every kind of type body axis system relative to sight has the fixed axis angle of deviation separately, if weapon installation position is equipped with change, also can recalculates and revise weapon misalignment of axe angle.There is explanation housing construction feature and sight, weapon installation site in the resume file of type and opportunity of combat, are given value.

Because orientation attitude is determined instrument and is operated need to move to equipment to be calibrated after obtaining body longitudinal axis near, and orientation attitude is determined instrument time and space in moving process variation has all been occurred, orientation attitude determines that instrument moves to after device location to be calibrated, body 3 has departed from former direction under the effect of earth rotation, therefore the present invention determines that by the first optical fibre gyro module 1 and the second optical fibre gyro module 6 orientation attitude determines the deviation rotation amount of instrument body 3 longitudinal axis in moving process, its principle is as follows: in body 3 and orientation attitude, determine that on instrument, respectively connecting firmly a coordinate system is respectively { C} and { Q}, X, Y, Z axis optical fibre gyro module, that is: the first optical fibre gyro module 1 and the second optical fibre gyro module 6, the X of the first optical fibre gyro module 1 and the second optical fibre gyro module 6, Y, z axis vertically represents respectively coordinate system San Ge unit main shaft mutually, at synchronization X, Y, coordinate system { C} and { the Spindle rotation angle rate signal of unit separately of Q} of three fibre optic gyroscope outputs on Z axis, through integration, resolve resume module, draw coordinate system { C} and the { spin matrix of the relative universe of Q} coordinate system ^u _cr, ^u _q(pre-super U represents universe coordinate system to R, lower left corner C represents the first optical fibre gyro module 1 coordinate system, lower left corner Q represents the second optical fibre gyro module 6 coordinate systems), coordinate system { C}, { take coordinate system { U} be reference, and { { spin matrix of C} is Q} relative coordinate system coordinate system by Q} ^c _qr, by ^u _qr= ^u _cr ^c _qr releases ^c _qr= ^u _cr ^-1. ^u _qr spin matrix is orthogonal matrix, so ^c _qr= ^u _cr ^t. ^u _qr, ^u _ur ^twith ^u _qr is optical fibre gyro module and resolve the instant given value that module draws, so ^c _qr is also a given value, be that { { C} is at the relative spin matrix of synchronization, and this matrix represents that orientation attitude determines the deviation rotation amount of relative the first optical fibre gyro module 1 of the second optical fibre gyro module 6 on instrument for relative the first optical fibre gyro module 1 coordinate system of Q} for the second optical fibre gyro module 6 coordinate systems.The relative local Coordinate System X of the first optical fibre gyro module 1 _c, Y _c, Z _ceach main shaft, resolves with Z-Y-X Euler horn cupping, and rotation amount is α successively _c, β _c, γ _c; The relative local Coordinate System X of the second optical fibre gyro module 6 _q, Y _q, Z _qeach main shaft, resolves with Z-Y-X Euler horn cupping, and rotation amount is α successively _q, β _q, γ _q.As next, have:

γ, β, α are that orientation attitude is determined the orientation attitude corner of instrument phase shift to the first optical fibre gyro module 1, and spin matrix is as follows relatively:

。

The present invention, when determining the roll angle of body 3 and the angle of pitch, measures the inclination data that opportunity of combat inclination angle obtains body 3 on the level platform that can arrange in opportunity of combat by inclinator.

The equipment that use fibre optic gyroscope of the present invention is calibrated fighter plane armament systems comprises that orientation attitude determines instrument and body longitudinal axis position determining device 2, orientation attitude determines that instrument comprises orientation attitude adjuster 7, the second optical fibre gyro module 6 is installed on orientation attitude adjuster 7, the second optical fibre gyro module 6 is built-in for analyzing the computer of orientation angles data, electron-optical aligner 4 and display 32 are installed in the second optical fibre gyro module 6, the integration of the second optical fibre gyro module 6 resolves module and all by data transmission interface, is connected with computer with display 32, computer resolves module by data transmission interface with the integration of the first optical fibre gyro module 1 and is connected, orientation attitude adjuster 7 can regulate the attitude angle of the second optical fibre gyro module 6, body longitudinal axis position determining device 2 can be measured the current longitudinal axis of body 3, and indicate this direction by the cross hair showing in spirit level 5 eyepieces.Electron-optical aligner 4 of the present invention can adopt the multiple optical aligners such as holographic aiming device, reflective sight, flat aobvious sight, parallel light tube.The present invention adopts optical fibre gyro as orientation attitude measurement parts, optical fibre gyro has all solid state, parts and friction means without spin, life-span is long, dynamic range is large, can instantaneous starting, simple in structure, size is little, the advantage such as lightweight, apply after the method and apparatus that fighter plane armament systems are calibrated of the present invention, singlely to opportunity of combat armo(u)ry system calibration operation, can in 30 minutes, complete, as 2 people's co-operatings, can in 20 minutes, can complete the calibration operation of opportunity of combat armo(u)ry system, body attitude is determined and boresight process all completes by optical instrument, be not subject to landform, the impact of the natural causes such as wind-force, in field environment, can to armament systems, calibrate whenever and wherever possible, be conducive to opportunity of combat and in modernized war, realize fast reaction, precision strike.

There is slight deflection in the present invention's second optical fibre gyro module when avoiding operating, can make the second optical fibre gyro module be connected with the supervisory keyboard 33 that the action buttons such as SR are installed by soft wire.For ease of viewing angle data, also orientation attitude can be determined to the display 32 of instrument is arranged on supervisory keyboard 33.

Attitude adjuster of the present invention is for regulating the attitude angle of the second optical fibre gyro module, for realizing this function, the present invention preferably adopts following structure: described orientation attitude adjuster 7 comprises that an x shaft angle position platform 17, a y shaft angle position platform 18, a z axle turntable 19, a z axle lifting platform 20 and x axle translation stage 21, the one x shaft angle position platforms 17, a y shaft angle position platform 18, a z axle turntable 19, a z axle lifting platform 20 and an x axle translation stage 21 are installed on regulator bracket 22.This structure has advantages of that adjusting operation is convenient, accuracy is high.Wherein an x shaft angle position platform 17 and a y shaft angle position platform 18 are for regulating the horizontal and vertical level inclination of the second optical fibre gyro module 6, the one z axle turntable 19 is for regulating the vertical direction of the second optical fibre gyro module 6, the one z axle lifting platform 20 and an x axle translation stage 21 are for regulating level height and the lateral attitude of the second optical fibre gyro module 6, for ease of operation, the one y axle translation stage 38, the one y axle translation stages 38 also can be installed on regulator bracket 22 for regulating the distance of electron-optical aligner 4 and equipment to be calibrated.Except preferred structure, attitude adjuster 7 of the present invention also can adopt universal turning bench to coordinate other various structures such as lifting platform, but these structures are compared adjusting operation with preferred structure relative loaded down with trivial details, and accuracy is relatively low simultaneously.

Body longitudinal axis position determining device of the present invention is for determining the orientation angles of the body longitudinal axis, its structure is: body longitudinal axis position determining device 2 comprises first housing longitudinal axis measurement instrument 11 and second housing longitudinal axis measurement instrument 12, first housing longitudinal axis measurement instrument 11 and second housing longitudinal axis measurement instrument 12 include adjusting base 14, on adjusting base 14, mounting platform 15, the vertical lift bar 13 vertical with platform 15 is installed on platform 15, inclinator 31 and spirit level 5, vertical lift bar 13 can be along the vertical direction lifting of platform 15, inclinator 31 can display platform 15 inclination angle, the axis of sighting of spirit level 5 is parallel with platform 15, the spirit level 5 of installing on the spirit level 5 of installing on the platform 15 of first housing longitudinal axis measurement instrument 11 and the platform 15 of second housing longitudinal axis measurement instrument 12 arranges in opposite directions, first housing longitudinal axis measurement instrument 11 and the axis of sighting of the spirit level 5 of second housing longitudinal axis measurement instrument 12 equate with the distance between vertical lift bar 13 separately, object lens one end of each spirit level 5 all arranges and spirit level 5 objective end can be covered or unlimited portable plate 16, portable plate 16 is provided with scale away from the one side of spirit level 5 object lens.Body longitudinal axis position determining device 2 of the present invention coordinates the body longitudinal axis of the present invention orientation to determine that method can significantly shorten 3 longitudinal axis azimuthal measurement times of body, and do not need in advance body 3 tops flatly, opportunity of combat is landed rear all can carry out when arbitrarily angled longitudinal axis azimuthal measurement and boresight operation.Except said structure, the present invention also can adopt other body longitudinal axis bearing measuring method and structure, such as existing bracing wire method etc., but these method Measuring Time long, measure inefficiency, need many people to coordinate, and while measuring, affected greatly by the natural causes such as landform, wind-force, certainty of measurement is lower.

The adjusting base of first housing coordinate measuring apparatus 11 of the present invention and second housing coordinate measuring apparatus 12 is for regulating the angle of first housing coordinate measuring apparatus 11 and second housing coordinate measuring apparatus 12, its structure is as follows: described adjusting base 14 comprises that the 2nd x shaft angle position platform 23, the 2nd y shaft angle position platform 24, the 2nd z axle turntable 25, the 2nd z axle lifting platform 26 and the 2nd x axle translation stage 27, the two x shaft angle position platforms 23, the 2nd y shaft angle position platform 24, the 2nd z axle turntable 25, the 2nd z axle lifting platform 26 and the 2nd x axle translation stage 27 are installed on base 28.The 2nd x shaft angle position platform 23 and the 2nd y shaft angle position platform 24 are for regulating the horizontal and vertical level inclination of first housing coordinate measuring apparatus 11 and second housing coordinate measuring apparatus 12, the 2nd z axle turntable 25 is for regulating the vertical direction of first housing coordinate measuring apparatus 11 and second housing coordinate measuring apparatus 12, the 2nd z axle lifting platform 26 and the 2nd x axle translation stage 27 are for regulating level height and the lateral attitude of first housing coordinate measuring apparatus 11 and second housing coordinate measuring apparatus 12, for ease of operation, also the 2nd y axle translation stage 37 can be installed on base 28, the 2nd y axle translation stage 37 is for regulating the spacing between spirit level 5.Except said structure, adjusting base 14 of the present invention also can adopt universal turning bench to coordinate other various structures such as lifting platform, but these structures are compared adjusting operation with preferred structure relative loaded down with trivial details, and accuracy is relatively low simultaneously.

In figure, 34 is tie lines.

Claims

1. use fibre optic gyroscope to the flat aobvious method of calibrating of fighter plane, it is characterized in that: comprise the steps:

1. in the upper first optical fibre gyro module (1) of installing of fighter plane body (3), the first optical fibre gyro module (1) comprises by three optical fibre gyros of three orthogonal space coordinates direction of principal axis of x, y, z setting and corresponding integration resolves module, and the angular velocity information that three optical fibre gyros are measured resolves module through integration to carry out integral operation and can draw (1) three axial angle-data of current the first optical fibre gyro module;

2. body longitudinal axis position determining device (2) is placed on to body (3) below, measure the orientation attitude of body (3), measured the cross hair direction showing in spirit level (5) eyepiece in rear body longitudinal axis position determining device (2) and be body (3) longitudinal axis;

3. orientation attitude is determined to instrument is positioned over body longitudinal axis position determining device (2) the place ahead, the electron-optical aligner (4) that orientation attitude is determined install on instrument is positioned at the dead ahead of spirit level (5), orientation attitude determines that the second optical fibre gyro module (6) of installing on instrument comprises that three optical fibre gyros and the corresponding integration identical with the first optical fibre gyro module (1) structure resolve module, can measure when first three axial angle-data;

4. from spirit level (5) eyepiece of orientation attitude coordinate measuring apparatus, see and look into, can see that spirit level (5) visual field and electron-optical aligner (4) visual field mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of spirit level (5), another determines the cross hair of the electron-optical aligner (4) of installing on instrument for orientation attitude, by regulating orientation attitude, determine that the orientation attitude adjuster (7) of instrument is adjusted to the cross hair of electron-optical aligner (4) with the cross hair of spirit level (5) and overlaps, now the sighted direction of electron-optical aligner (4) is parallel with the cross hair direction of spirit level (5), be body (3) longitudinal axis,

5. after the cross hair of electron-optical aligner (4) overlaps with the cross hair of spirit level (5), press orientation attitude and determine the SR of the second optical fibre gyro module (6) on instrument, now the second optical fibre gyro module (6) is confirmed as identical with the initial relative bearing of the first optical fibre gyro module (1), make zero in relative deviation azimuth, from then on constantly rise, the first optical fibre gyro module (1) starts the record orientation attitude variation of relative universe coordinate system separately with the second optical fibre gyro module (6), computer is by calculating the relative attitude angle of deviation data between the first optical fibre gyro module (1) and the second optical fibre gyro module (6) to the first optical fibre gyro module (1) and the orientation attitude variation separately of the second optical fibre gyro module (6), these relative attitude angle of deviation data are shown on display (32) simultaneously,

6. orientation attitude is determined to instrument moves to flat aobvious (8) dead astern, electron-optical aligner (4) sighted direction is aimed to body (3) dead ahead, by regulating orientation attitude adjuster (7) to regulate the orientation attitude angle of the second optical fibre gyro module (6), until the predetermined angular between the flat aobvious sight line of the upper current type of relative attitude data fit showing of display device (32) and the body longitudinal axis, the direction that at this moment direction of the cross hair indication in electron-optical aligner (4) visual field need to be adjusted to for flat aobvious sight line;

7. from the form of electron-optical aligner (4), observe, can see that electron-optical aligner (4) visual field and flat aobvious (8) visual field mutually superpose in the visual field forming and have two cross hairs, a cross hair for flat aobvious (8), one is the cross hair of electron-optical aligner (4), by flat aobvious (8) self adjusting device, will put down the cross hair that shows (8) is adjusted to the cross hair of electron-optical aligner (4) and overlaps, now can determine that the cross hair direction of flat aobvious (8) meets the predetermined angular of the flat aobvious sight line of current type and the body longitudinal axis, complete flat aobvious (8) calibration.

2. use fibre optic gyroscope according to claim 1, to the flat aobvious method of calibrating of fighter plane, is characterized in that: complete after flat aobvious calibration, by following step, gun is calibrated:

8. complete after flat aobvious calibration, gun tube front end at gun (10) is installed borescope (29), orientation attitude is determined to instrument moves to gun (10) the place ahead, the electron-optical aligner (4) that orientation attitude is determined install on instrument is positioned at the dead ahead of borescope (29), electron-optical aligner (4) sighted direction is aimed to body (3) dead ahead, by regulating orientation attitude adjuster (7) to regulate the orientation attitude angle of the second optical fibre gyro module (6), until the upper current type gun of relative attitude data fit showing of display device (32) and the predetermined angular between flat showing, at this moment the direction of the cross hair indication in electron-optical aligner (4) visual field is the direction that gun need to be adjusted to,

9. from borescope (29), can see by borescope (29) visual field and electron-optical aligner (4) visual field and mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of borescope (29), another is the cross hair of electron-optical aligner (4), by regulating the angle of gun (10) that the cross hair of borescope (29) is adjusted to the cross hair of electron-optical aligner (4) and is overlapped, the direction that now can determine gun (10) meets current type gun and the predetermined angular between flat showing, complete gun (10) calibration.

3. use fibre optic gyroscope according to claim 1, to the flat aobvious method of calibrating of fighter plane, is characterized in that: the step of the orientation attitude of measurement body (3) is as follows:

A, first housing longitudinal axis measurement instrument (11) in body longitudinal axis position determining device (2) and second housing longitudinal axis measurement instrument (12) are placed on respectively to body (3) bottom, vertical lift bar (13) top of first housing longitudinal axis measurement instrument (11) and second housing longitudinal axis measurement instrument (12) contacts with former and later two longitudinal axis face gauge points of body (3) bottom respectively, guarantee that the direction that body longitudinal axis position determining device (2) is measured is body (3) longitudinal axis, spirit level (5) on first housing longitudinal axis measurement instrument (11) arranges in opposite directions with the spirit level (5) on second housing longitudinal axis measurement instrument (12),

B, by adjusting first housing longitudinal axis measurement instrument (11), make platform (15) inclination angle and platform (15) inclination angle on second housing longitudinal axis measurement instrument (12) on first housing longitudinal axis measurement instrument (11) all consistent with the inclination angle of body (3) with second housing longitudinal axis measurement instrument (12) adjusting base (14) separately;

C, the portable plate (16) of the upper spirit level (5) of first housing longitudinal axis measurement instrument (11) is gone to open mode, and the portable plate (16) of the upper spirit level (5) of second housing longitudinal axis measurement instrument (12) is gone to shielding status, from first housing longitudinal axis measurement instrument (11), in the eyepiece of spirit level (5), observe the scale position that cross hair aims at second housing longitudinal axis measurement instrument (12) portable plate (16), then the portable plate (16) of the upper spirit level (5) of second housing longitudinal axis measurement instrument (12) is gone to open mode, and the portable plate (16) of the upper spirit level (5) of first housing longitudinal axis measurement instrument (11) is gone to shielding status, from second housing longitudinal axis measurement instrument (12), in the eyepiece of spirit level (5), observe the scale position that cross hair aims at first housing longitudinal axis measurement instrument (11) portable plate (16), repeatedly adjust first housing longitudinal axis measurement instrument (11) identical with the scale position that the sight line of the upper spirit level (5) of second housing longitudinal axis measurement instrument (12) aims at the scale position that second housing longitudinal axis measurement instrument (12) adjusting base (14) separately aims at the sight line of the upper spirit level (5) of first housing longitudinal axis measurement instrument (11), determine that the spirit level (5) of first housing longitudinal axis measurement instrument (11) and spirit level (5) sighted direction of second housing longitudinal axis measurement instrument (12) are parallel, platform (15) inclination angle and platform (15) inclination angle on second housing longitudinal axis measurement instrument (12) on first housing longitudinal axis measurement instrument (11) is all consistent with the inclination angle of body (3) simultaneously, vertical lift bar (13) top of first housing longitudinal axis measurement instrument (11) and second housing longitudinal axis measurement instrument (12) contacts with former and later two longitudinal axis face gauge points of body (3) bottom respectively, now towards the sighted direction of the spirit level (5) in body (3) the place ahead, be the longitudinal axis of body (3).

4. the method for using fibre optic gyroscope to calibrate fighter plane Optic-electronic Stabilization Sight, is characterized in that: comprise the steps:

1. in the upper first optical fibre gyro module (1) of installing of fighter plane body (3), the first optical fibre gyro module (1) forms by resolving module by three optical fibre gyros of three orthogonal space coordinates direction of principal axis of x, y, z setting and corresponding integration, and the angular velocity information that three optical fibre gyros are measured resolves module through integration to carry out integral operation and can draw (1) three axial angle-data of current the first optical fibre gyro module;

6. orientation attitude is determined to instrument moves to Optic-electronic Stabilization Sight (9) the place ahead, electron-optical aligner (4) sighted direction is aimed to body (3) dead ahead, by regulating orientation attitude adjuster (7) to regulate the orientation attitude angle of the second optical fibre gyro module (6), until sight line during the upper current type Optic-electronic Stabilization Sight of the relative attitude data fit zero-bit showing of display device (32) and the predetermined angular between the body longitudinal axis, at this moment the direction of the cross hair indication in electron-optical aligner (4) visual field is the direction that Optic-electronic Stabilization Sight sight line need to be adjusted to;

7. Optic-electronic Stabilization Sight (9) is adjusted to zero-bit, now in the Optic-electronic Stabilization Sight significant screen from driving cabin, observe, can see that electron-optical aligner (4) visual field and Optic-electronic Stabilization Sight (9) visual field mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of Optic-electronic Stabilization Sight (9), one is the cross hair of electron-optical aligner (4), adjusting device by Optic-electronic Stabilization Sight (9) self is adjusted to the cross hair of Optic-electronic Stabilization Sight (9) zero-bit with the cross hair of electron-optical aligner (4) and overlaps, sight line when the cross hair direction that now can determine Optic-electronic Stabilization Sight (9) zero-bit meets current type Optic-electronic Stabilization Sight zero-bit and the predetermined angular between the body longitudinal axis, complete Optic-electronic Stabilization Sight (9) calibration.

5. the method that use fibre optic gyroscope according to claim 4 is calibrated fighter plane Optic-electronic Stabilization Sight, is characterized in that: the step of the orientation attitude of measurement body (3) is as follows:

6. the method for using fibre optic gyroscope to calibrate fighter plane gun, is characterized in that: comprise the steps:

2. orientation attitude is determined to instrument is positioned over flat aobvious (8) dead astern, orientation attitude determines that the second optical fibre gyro module (6) of installing on instrument comprises that three optical fibre gyros and the corresponding integration identical with the first optical fibre gyro module (1) structure resolve module, can measure when first three axial angle-data, from the eyepiece of electron-optical aligner (4), see and look into, can see that electron-optical aligner (4) visual field and flat aobvious (8) visual field mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of electron-optical aligner (4), another is the cross hair of flat aobvious (8), by regulating orientation attitude, determine that the orientation attitude adjuster (7) of instrument is adjusted to the cross hair of electron-optical aligner (4) with the cross hair of flat aobvious (8) and overlaps, now the sighted direction of electron-optical aligner (4) is parallel with the cross hair direction of flat aobvious (8),

3. after the cross hair of electron-optical aligner (4) overlaps with the cross hair of flat aobvious (8), press orientation attitude and determine the SR of the second optical fibre gyro module (6) on instrument, now the second optical fibre gyro module (6) is confirmed as identical with the initial relative bearing of the first optical fibre gyro module (1), make zero in relative deviation azimuth, from then on constantly rise, the first optical fibre gyro module (1) starts the record orientation attitude variation of relative universe coordinate system separately with the second optical fibre gyro module (6), computer is by calculating the relative attitude angle of deviation data between the first optical fibre gyro module (1) and the second optical fibre gyro module (6) to the first optical fibre gyro module (1) and the orientation attitude variation separately of the second optical fibre gyro module (6), these relative attitude angle of deviation data are shown on display (32) simultaneously,

4. at the gun tube front end of gun (10), borescope (29) is installed, orientation attitude is determined to instrument moves to gun (10) the place ahead, the electron-optical aligner (4) that orientation attitude is determined install on instrument is positioned at the dead ahead of borescope (29), electron-optical aligner (4) sighted direction is aimed to body (3) dead ahead, by regulating orientation attitude adjuster (7) to regulate the orientation attitude angle of the second optical fibre gyro module (6), until the upper current type gun of relative attitude data fit showing of display device (32) and the predetermined angular between the body longitudinal axis, at this moment the direction of the cross hair indication in electron-optical aligner (4) visual field is the direction that gun need to be adjusted to,

5. from borescope (29), can see by borescope (29) visual field and electron-optical aligner (4) visual field and mutually superpose in the visual field forming and have two cross hairs, one is the cross hair of borescope (29), another is the cross hair of electron-optical aligner (4), by regulating the angle of gun (10) that the cross hair of borescope (29) is adjusted to the cross hair of electron-optical aligner (4) and is overlapped, the direction that now can determine gun (10) meets the predetermined angular between current type gun and the body longitudinal axis, complete gun (10) calibration.

7. the equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems, it is characterized in that: comprise that orientation attitude determines instrument and body longitudinal axis position determining device (2), orientation attitude determines that instrument comprises orientation attitude adjuster (7), the upper second optical fibre gyro module (6) of installing of orientation attitude adjuster (7), the second optical fibre gyro module (6) is built-in for analyzing the computer of orientation angles data, upper electron-optical aligner (4) and the display (32) installed of the second optical fibre gyro module (6), the integration of the second optical fibre gyro module (6) resolves module and all by data transmission interface, is connected with computer with display (32), computer resolves module by data transmission interface with the integration of the first optical fibre gyro module (1) and is connected, orientation attitude adjuster (7) can regulate the attitude angle of the second optical fibre gyro module (6), body longitudinal axis position determining device (2) can be measured the current longitudinal axis of body (3), and indicate this direction by the cross hair showing in spirit level (5) eyepiece.

8. the equipment that use fibre optic gyroscope according to claim 7 is calibrated fighter plane armament systems, it is characterized in that: described orientation attitude adjuster (7) comprises an x shaft angle position platform (17), a y shaft angle position platform (18), a z axle turntable (19), a z axle lifting platform (20) and an x axle translation stage (21), an x shaft angle position platform (17), a y shaft angle position platform (18), a z axle turntable (19), a z axle lifting platform (20) and an x axle translation stage (21) are installed on regulator bracket (22).

9. the equipment that use fibre optic gyroscope according to claim 7 is calibrated fighter plane armament systems, it is characterized in that: comprise first housing longitudinal axis measurement instrument (11) and second housing longitudinal axis measurement instrument (12), first housing longitudinal axis measurement instrument (11) and second housing longitudinal axis measurement instrument (12) include adjusting base (14), the upper mounting platform (15) of adjusting base (14), the upper installation of platform (15) the vertical lift bar (13) vertical with platform (15), inclinator (31) and spirit level (5), vertical lift bar (13) can be along the vertical direction lifting of platform (15), inclinator (31) can display platform (15) inclination angle, the axis of sighting of spirit level (5) is parallel with platform (15), the upper spirit level (5) of installing of platform (15) of first housing longitudinal axis measurement instrument (11) arranges in opposite directions with the upper spirit level (5) of installing of platform (15) of second housing longitudinal axis measurement instrument (12), first housing longitudinal axis measurement instrument (11) and the axis of sighting of the spirit level (5) of second housing longitudinal axis measurement instrument (12) equate with the distance between vertical lift bar (13) separately, object lens one end of each spirit level (5) all arranges and spirit level (5) objective end can be covered or unlimited portable plate (16), portable plate (16) is provided with scale away from the one side of spirit level (5) object lens.

10. the equipment that use fibre optic gyroscope according to claim 9 is calibrated fighter plane armament systems, it is characterized in that: described adjusting base (14) comprises the 2nd x shaft angle position platform (23), the 2nd y shaft angle position platform (24), the 2nd z axle turntable (25), the 2nd z axle lifting platform (26) and the 2nd x axle translation stage (27), the 2nd x shaft angle position platform (23), the 2nd y shaft angle position platform (24), the 2nd z axle turntable (25), the 2nd z axle lifting platform (26) and the 2nd x axle translation stage (27) are installed on base (28).