CN203928892U - The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems - Google Patents
The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems Download PDFInfo
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- CN203928892U CN203928892U CN201420264122.7U CN201420264122U CN203928892U CN 203928892 U CN203928892 U CN 203928892U CN 201420264122 U CN201420264122 U CN 201420264122U CN 203928892 U CN203928892 U CN 203928892U
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Abstract
The utility model provides a kind of equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems, 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.The utility model is simplified step, the lifting calibration efficiency of Fighter Weapons calibration process, in field environment, armament systems is calibrated.
Description
Technical field
The utility model relates to a kind of weapon calibrator (-ter) unit, specifically a kind of equipment 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.
Utility model content
The purpose of this utility model is to provide a kind of equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems, it can effectively simplify step, the lifting calibration efficiency of Fighter Weapons calibration process, 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 utility model for achieving the above object, be achieved through the following technical solutions: 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.The second optical fibre gyro module is connected with supervisory keyboard by soft wire installs the action buttons such as SR and display on supervisory keyboard.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.On the platform of spirit level objective end one side, vertical shaft is set, axle sleeve is installed on vertical shaft, axle sleeve can be along vertical shaft rotary, and axle sleeve is connected with portable plate.In the second optical fibre gyro module, digital display angle instrument is installed.
The utility model has the advantage of: step, the lifting calibration efficiency that can effectively simplify 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, also can realize on motion carrier armament systems are calibrated, not be subject to the own motion effects of carrier etc.
Accompanying drawing explanation
Fig. 1 is structure and the annexation schematic diagram that orientation described in the utility model attitude is determined instrument and the first optical fibre gyro module;
Fig. 2 is that orientation described in the utility model attitude is determined the contour structures schematic diagram that instrument is connected with the first optical fibre gyro module;
Fig. 3 is the structural representation of body longitudinal axis position determining device described in the utility model;
Fig. 4 is the use status architecture schematic diagram of the utility model while using body longitudinal axis position determining device to determine body longitudinal axis orientation;
Fig. 5 is the use view that use fibre optic gyroscope described in the utility model 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. 6 is the use view that use fibre optic gyroscope described in the utility model is calibrated fighter plane armament systems; State while determining that for orientation attitude instrument is placed in gun forward position shown in figure.
The specific embodiment
The equipment that use fibre optic gyroscope described in the utility model 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 described in the utility model can adopt the multiple optical aligners such as holographic aiming device, reflective sight, flat aobvious sight, parallel light tube.The utility model 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 equipment that fighter plane armament systems are calibrated described in the utility model, 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.
So that opportunity of combat is put down to show with gun, be calibrated to example, use the step of the utility model calibration as follows:
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.
Use the utility model identical with said method principle to the calibration steps of the weapon equipment such as Optic-electronic Stabilization Sight, boat rifle, aircraft rocket transmitter, guided missile hanger.
The borescope 29 that the utility model adopted in the experimental stage is straight-9WA borescope, in actual use, can select supporting borescope to use according to type.
The utility model 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 utility model 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 utility model, when definite body 3 roll angle, is measured the roll angle data that opportunity of combat inclination angle obtains body 3 on the level platform that can arrange in opportunity of combat by inclinometer.
There is slight deflection in the utility model 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 described in the utility model is for regulating the attitude angle of the second optical fibre gyro module, for realizing this function, the utility model 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 described in the utility model 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 described in the utility model 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 described in the utility model coordinates the body longitudinal axis described in the utility model 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 utility model also can adopt other body longitudinal axis bearing measuring method and structure, such as existing bracing wire method etc., but inefficiency is grown, measured to these method Measuring Time, 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 described in the utility model 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 described in the utility model 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.
The operating procedure of body longitudinal axis position determining device described in the utility model is 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.
Portable plate 16 described in the utility model can cover spirit level 5 objective end or open wide, the spirit level that can be opposite by scale during portable plate 16 shielding status provides aiming reference, for realizing above-mentioned functions, the utility model can adopt following structure to be connected with platform: on the platform 15 of spirit level 5 objective end one sides, vertical shaft 35 is set, axle sleeve 36 is installed on vertical shaft 35, axle sleeve 36 can be along vertical shaft rotary, and axle sleeve 36 is connected with portable plate 16.During use, can its rich vertical shaft 35 rotations be switched by rotary moveable plate 16 and cover or opening-wide state.This structure has advantages of easy to operate.Except said structure, portable plate 16 described in the utility model also can adopt other various ways to be connected with platform 15, for example can near spirit level 5 objective end, slot be set at platform 15, while needing 16 pairs of spirit levels 5 of portable plate to cover, portable plate 16 is inserted in slot, make portable plate 16 block the object lens of spirit level 5, be convenient to another group spirit level and determine sighted direction etc. by the scale on portable plate 16, but relatively loaded down with trivial details during these connected modes operations.
The utility model, in order further to improve calibration speed, can be installed digital display angle instrument 30 in the second optical fibre gyro module 6.Install after digital display angle instrument 30, the inclination data that can show by digital display angle instrument 30 during operation is carried out presetting to attitude adjuster 7, reduces attitude adjuster 7 fine setting required times.
In figure, 34 is tie lines.
Claims (7)
1. 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.
2. the equipment that use fibre optic gyroscope according to claim 1 is calibrated fighter plane armament systems, is characterized in that: the second optical fibre gyro module is connected upper action button and the displays (32) such as SR installed of supervisory keyboard (33) with supervisory keyboard (33) by soft wire.
3. the equipment that use fibre optic gyroscope according to claim 1 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).
4. the equipment that use fibre optic gyroscope according to claim 1 is calibrated fighter plane armament systems, it is characterized in that: 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), 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.
5. the equipment that use fibre optic gyroscope according to claim 4 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).
6. the equipment that use fibre optic gyroscope according to claim 4 is calibrated fighter plane armament systems, it is characterized in that: on the platform (15) of spirit level (5) objective end one side, vertical shaft (35) is set, the upper axle sleeve (36) of installing of vertical shaft (35), axle sleeve (36) can be along vertical shaft rotary, and axle sleeve (36) is connected with portable plate (16).
7. the equipment that use fibre optic gyroscope according to claim 1 is calibrated fighter plane armament systems, is characterized in that: the upper digital display angle instrument (30) of installing of the second optical fibre gyro module (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420264122.7U CN203928892U (en) | 2014-05-22 | 2014-05-22 | The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420264122.7U CN203928892U (en) | 2014-05-22 | 2014-05-22 | The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems |
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| CN203928892U true CN203928892U (en) | 2014-11-05 |
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| CN201420264122.7U Withdrawn - After Issue CN203928892U (en) | 2014-05-22 | 2014-05-22 | The equipment that uses fibre optic gyroscope to calibrate fighter plane armament systems |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104089529A (en) * | 2014-05-22 | 2014-10-08 | 陈远春 | Method and equipment for calibrating fighter weapon system by fiber-optic gyroscope |
| WO2019126932A1 (en) * | 2017-12-25 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Cradle head control method and control device |
| CN111089708A (en) * | 2019-12-09 | 2020-05-01 | 中国航空工业集团公司洛阳电光设备研究所 | System and method for measuring error of head-up display center |
-
2014
- 2014-05-22 CN CN201420264122.7U patent/CN203928892U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104089529A (en) * | 2014-05-22 | 2014-10-08 | 陈远春 | Method and equipment for calibrating fighter weapon system by fiber-optic gyroscope |
| CN104089529B (en) * | 2014-05-22 | 2016-03-02 | 陈远春 | Use the method and apparatus that fibre optic gyroscope is calibrated fighter plane armament systems |
| WO2019126932A1 (en) * | 2017-12-25 | 2019-07-04 | 深圳市大疆创新科技有限公司 | Cradle head control method and control device |
| CN111089708A (en) * | 2019-12-09 | 2020-05-01 | 中国航空工业集团公司洛阳电光设备研究所 | System and method for measuring error of head-up display center |
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