CN106969744B - Space attitude measuring instrument and method for fighter plane body - Google Patents
Space attitude measuring instrument and method for fighter plane body Download PDFInfo
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- CN106969744B CN106969744B CN201710271561.9A CN201710271561A CN106969744B CN 106969744 B CN106969744 B CN 106969744B CN 201710271561 A CN201710271561 A CN 201710271561A CN 106969744 B CN106969744 B CN 106969744B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C1/00—Measuring angles
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
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Abstract
The space attitude measuring instrument comprises a tripod telescopic support, wherein a lower transverse plate is arranged at the top of the tripod telescopic support, one side of the lower transverse plate is connected with an upper transverse plate through a longitudinal support, a through hole is formed in one end, far away from the longitudinal support, of the upper transverse plate, a conical block is installed above the through hole, the bottom surface of the conical block is a spherical crown surface, the spherical crown surface is in contact fit with the through hole, the circle center of the spherical crown surface is coincided with the vertex of the conical block, the center of the bottom of the spherical crown surface is connected with a first observation mirror with a cross sight line through a suspension post, and a first biaxial digital display inclinometer is installed on the first observation mirror. The method is not influenced by the ground flatness and wind power, can create conditions for calibrating a weapon system of a fighter plane at any time in a field environment, can be independently completed by a single person in the body posture determining process, and can complete the measurement work of the body space posture within 5-10 minutes by the single person after proficiency.
Description
Technical Field
The invention relates to a device and a method for measuring the longitudinal axis of a fighter plane, in particular to a device for measuring the space attitude of a fighter plane body and a method for measuring the space attitude of the fighter plane body by using the device.
Background
Weapon systems used on various warplanes such as gunships, fixed-wing warplanes and the like need to be calibrated after being installed or adjusted, the warplanes need to be calibrated regularly or repeatedly according to the needs of pilots during service, before the warplane weapons are calibrated, the space attitude of the warplanes, namely the space direction of the longitudinal axis of the airframe, needs to be determined firstly, and then the warplane weapons and aiming equipment are adjusted to be consistent with the direction of the longitudinal axis of the airframe. The calibration of the existing warplane weapon system mostly adopts a contraction target plate calibration method, the method needs workers to use a hoisting tool to jack the body of the warplane to a horizontal posture before target calibration, the body position is determined by using a horizontal plane as reference and using a pull line method, the calibration method needs at least over ten workers to mutually coordinate and operate when the body is jacked to be flat, the operation steps are complicated when the position is determined by the pull line, the efficiency is low, the time of 3-4 hours is at least needed when the body posture is measured every time, the requirement of modern warfare on quick response to the warplane is difficult to meet, the requirement of measurement operation on the ground flatness is high, the requirement of calibrating the warplane weapon at any time in a field environment cannot be met, the influence of wind force in the pull line measurement process is large, and the accuracy of target calibration in an outdoor environment cannot be guaranteed. In order to meet the requirement of field calibration, the technical personnel in the field have proposed a method and a device for calibrating a weapon system of a fighter by using an optical fiber gyroscope and obtained patent authorization (an authorization publication number: CN 104089529B), the technology mainly provides a scheme and a device for calibrating the weapon system in a field environment and on a moving carrier, but because the method adopts a mode that two groups of devices are in sight with each other to determine the direction of a longitudinal axis of a machine body, the positions of two groups of sighting lines are always changed during adjustment, a worker needs to operate between the two groups of devices for many times, and the space posture of the machine body can be determined usually within more than 30 minutes.
Disclosure of Invention
The invention aims to provide a space attitude measuring instrument for a warplane body, which is not influenced by ground flatness and wind power, can create conditions for calibrating a weapon system of the warplane at any time in a field environment, can independently finish the attitude determination process of the warplane body by a single person, and can finish the measurement work of the space attitude of the warplane body within 5-10 minutes after proficiency.
In order to achieve the purpose, the invention is realized by the following technical scheme: the three-leg telescopic bracket comprises a three-leg telescopic bracket, wherein a lower transverse plate is arranged at the top of the three-leg telescopic bracket, one side of the lower transverse plate is connected with an upper transverse plate through a longitudinal bracket, one end of the upper transverse plate, which is far away from the longitudinal bracket, is provided with a through hole, a conical block is arranged above the through hole, the bottom surface of the conical block is a spherical crown surface, the spherical crown surface is in contact fit with the through hole, the center of the spherical crown surface is superposed with the vertex of the conical block, the center of the bottom of the spherical crown surface is connected with a first observation mirror with a cross sight through a suspension post, a first biaxial digital display inclinometer is arranged on the first observation mirror and can display the pitching angle and the rolling angle in the direction indicated by the cross sight of the first observation mirror, a second observation mirror with a longitudinal sight is arranged below the first observation mirror, the central axis of the second observation mirror and the vertex of the conical block are always in the same plane, a rotating device is arranged below the second observation mirror, the upper part of the rotating device is connected with the lower transverse plate through an adjusting bracket. The second observation mirror is hinged with the first observation mirror through a hinged seat, a locking nut is installed on a hinged shaft of the hinged seat, and the pitching angle of the second observation mirror relative to the first observation mirror can be adjusted and locked through the locking nut. The rotating and transverse moving device comprises a rotating holder, a rotating part of the rotating holder is connected with an adjusting support, a double-shaft translation table is installed below the rotating holder, the double-shaft translation table can adjust the horizontal position of the rotating holder along the directions of two mutually perpendicular horizontal coordinate axes, and the rotating holder is connected with the double-shaft translation table through a connecting piece with a changeable longitudinal height. The connecting piece that vertical height can change is including horizontal connecting plate between rotatory cloud platform and biax translation platform, and connecting plate one end is connected with biax translation platform top surface, and the connecting plate other end is connected with rotatory cloud platform bottom surface. The eyepiece ends of the first observation mirror and the second observation mirror are both provided with bent tube eyepieces. And the eyepiece ends of the first observation mirror and the second observation mirror are both provided with electronic eyepieces with electronic display screens.
The method for measuring the space attitude of the fighter plane body by using the measuring instrument for the space attitude of the fighter plane body comprises the following steps:
(1) placing a second biaxial digital display inclinometer at an attitude measurement position on the warplane body, and recording the pitch angle and roll angle values of the warplane body displayed by the second biaxial digital display inclinometer;
(2) the space attitude measuring instrument of the fighter plane body is placed below a longitudinal axis marking point at the rear part of the fighter plane, and the height of the three-leg telescopic support is adjusted to enable the top point of the conical block to be in point contact with the longitudinal axis marking point at the rear part of the fighter plane;
(3) and adjusting the rotating traversing device to enable the pitch angle and roll angle values displayed by the first biaxial digital display inclinometer to be consistent with the pitch angle and roll angle values of the airframe measured by the second biaxial digital display inclinometer, and simultaneously ensuring that the longitudinal aiming line of the second observation mirror is superposed with the longitudinal axis mark point at the front part of the fighter, wherein the direction indicated by the cross aiming line of the first observation mirror is the longitudinal axis direction of the airframe of the fighter.
Before the step (3), inserting a marking rod into a concave hole of a longitudinal axis marking point at the front part of the fighter, wherein the marking rod is a truncated cone, a fan-shaped groove is formed in the side wall of the marking rod, two side surfaces of the fan-shaped groove are intersected at the center line of the marking rod, the included angle between the two side surfaces of the fan-shaped groove is 10-120 degrees, and when the rotary traversing device is adjusted, the longitudinal aiming line of the second observation mirror is coincided with the intersection point of the intersection line of the two side surfaces of the fan-shaped groove on the marking rod and the belly junction, so that the coincidence of the longitudinal aiming line of the second observation mirror and the longitudinal axis marking point at the front part of the fighter can be ensured. And the second observation mirror is provided with a laser positioner.
The invention has the advantages that: the method is not influenced by the flatness of the ground and wind power, conditions can be created for calibrating a weapon system of a fighter plane at any time in a field environment, the process of determining the posture of the fighter plane can be independently completed by one person, and the measurement of the space posture of the fighter plane can be completed within 5-10 minutes by one person after proficiency.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a perspective view of FIG. 1;
FIG. 3 is a schematic view of the present invention aimed at a longitudinal axis marking point in front of the fighter plane by the second sight glass 10;
FIG. 4 is a schematic view of the front of the fighter plane of FIG. 3 showing the construction of the marking stick mounted at the marking point on the longitudinal axis;
FIG. 5 is a schematic structural view of an electronic eyepiece with an electronic display screen according to the present invention;
FIG. 6 is a schematic view of the configuration of the elbow eyepiece of the present invention;
fig. 7 is a schematic structural view of the marking stick.
Detailed Description
The space attitude measuring instrument for the fighter plane body comprises a three-foot telescopic support 1, wherein a lower transverse plate 2 is arranged at the top of the three-foot telescopic support 1, one side of the lower transverse plate 2 is connected with an upper transverse plate 4 through a longitudinal support 3, one end, far away from the longitudinal support 3, of the upper transverse plate 4 is provided with a through hole 5, a conical block 6 is arranged above the through hole 5, the bottom surface of the conical block 6 is a spherical crown surface 7, the spherical crown surface 7 is in contact fit with the through hole 5, the center of the spherical crown surface 7 is superposed with the top point of the conical block 6, the center of the bottom of the spherical crown surface 7 is connected with a first observation mirror 9 with a cross sight through a suspension column 8, a first biaxial digital display inclinometer 16 is arranged on the first observation mirror 9, the first biaxial digital display inclinometer 16 can display the pitch angle and the roll angle of the cross sight of the first observation mirror 9 in the indicated direction, a second observation mirror 10 with a longitudinal sight is arranged below the first observation mirror 9, the central axis of the first observation mirror 9, the second observation mirror 10 and the top point of the conical block 6 are always in the same plane, a transverse movement sight, a rotary observation device 13 is arranged below the second observation mirror and connected with the lower transverse observation mirror 2. The transverse position and the angle of the lower end of the adjusting bracket 13 can be adjusted by the rotary traversing device, and the top position of the conical block 6 is kept unchanged when the transverse position and the angle of the lower end of the adjusting bracket 13 are changed because the spherical crown surface 7 at the bottom of the conical block 6 is in contact fit with the through hole 5, so that the posture and the azimuth angle of the adjusting bracket 13 can be adjusted by adjusting the transverse position and the angle of the lower end of the adjusting bracket 13 by the rotary traversing device. The space attitude measuring instrument of the warplane body is placed below a longitudinal axis marking point at the rear part of the warplane when in use, the height of the three-leg telescopic bracket is adjusted to enable the vertex of the conical block to be in point contact with the longitudinal axis marking point at the rear part of the warplane, the horizontal position and the angle of the lower end of the adjusting bracket 13 can be adjusted through the rotating traversing device to adjust the pitch angle, the roll angle and the horizontal direction of the direction indicated by the cross sight of the first observation mirror 9, when the rotating traversing device is adjusted, the spherical crown surface 7 at the bottom of the conical block 6 is in contact fit with the through hole 5, the vertex position of the conical block 6 can be kept unchanged and is always in point contact with the longitudinal axis marking point at the rear part of the warplane, wherein the pitch angle and the roll angle of the direction indicated by the cross sight of the first observation mirror 9 are adjusted according to data measured by another biaxial digital display inclinometer placed at the attitude measuring position of the warplane, the horizontal direction indicated by the longitudinal sight of the second observation mirror 10, and when the longitudinal axis marking point of the second observation mirror 10 is coincident with the longitudinal axis marking point at the front part of the warplane, the horizontal direction indicated by the cross sight of the first observation mirror 9 is consistent with the longitudinal axis marking point. The invention is not influenced by the ground flatness and wind power when measuring the space attitude of the body, can create conditions for calibrating the weapon system of the fighter plane at any time in the field environment, the body attitude determination process can be independently completed by a single person, the aiming line is adjusted by comparing with the fixed mark point on the body during measurement, and the measurement work of the space attitude of the body can be completed by a single person within 5-10 minutes after proficiency.
When the space attitude measuring instrument for the fighter plane body measures a fixed plane type, the distance between the front and rear longitudinal axis mark points of the plane type cannot be changed, so that the second observation mirror 10 and the first observation mirror 9 can be fixedly connected, and the same included angle is always kept. In order to enhance the universality of the space attitude measuring instrument of the fighter plane body, the second observation mirror 10 can be hinged with the first observation mirror 9 through a hinge seat, a lock nut 11 is arranged on the hinge shaft of the hinge seat, and the pitching angle of the second observation mirror 10 relative to the first observation mirror 9 can be adjusted and locked through the lock nut 11. The structure can change the included angle between the second observation mirror 10 and the first observation mirror 9, and the distance between the front and back longitudinal axis mark points of different models is different, so that the space attitude measuring instrument of the fighter plane body can be suitable for the body space attitude measuring work of various models by adjusting the included angle between the second observation mirror 10 and the first observation mirror 9.
The rotary traversing device can adopt various structures, wherein the preferable structure is as follows: the rotating and traversing device comprises a rotating tripod head 12, a rotating part of the rotating tripod head 12 is connected with an adjusting support 13, a double-shaft translation table 14 is installed below the rotating tripod head 12, the double-shaft translation table 14 can adjust the horizontal position of the rotating tripod head 12 along two mutually perpendicular horizontal coordinate axis directions, and the rotating tripod head 12 is connected with the double-shaft translation table 14 through a connecting piece with a changeable longitudinal height. The structure has the advantages of high adjusting precision and accurate positioning, and in order to improve the adjusting speed of the double-shaft translation table 14, the double-shaft translation table provided with the coarse adjusting device and the fine adjusting device can be selected, and the position can be adjusted to an approximate position through the coarse adjusting device and then accurately adjusted by the fine adjusting device. In addition, the rotating and traversing device can also adopt a universal adjusting device consisting of a plurality of groups of ball-head universal joints to be arranged between the adjusting bracket 13 and the lower transverse plate 2 and other structures to realize the adjustment of the pitching angle, the rolling angle and the horizontal direction of the direction indicated by the crosshair of the first observation mirror 9, but the adjusting precision and the positioning precision of the structures are different from the optimal scheme.
When the lower ends of the rotating pan/tilt head 12 and the adjusting bracket 13 are driven to move by the biaxial translation stage 14, the distance between the rotating pan/tilt head 12 and the biaxial translation stage 14 changes, so that it is required to ensure that the height of the connecting piece between the rotating pan/tilt head 12 and the biaxial translation stage 14 can change accordingly, the connecting piece with the variable longitudinal height of the invention can adopt various structures such as a telescopic universal joint, and the preferable structure is as follows: the connecting piece that vertical height can change is including transversely putting connecting plate 15 between rotatory cloud platform 12 and biax translation platform 14, and connecting plate 15 one end is connected with 14 top surfaces of biax translation platform, and the connecting plate 15 other end is connected with rotatory cloud platform 12 bottom surfaces. Compared with other structures, the structure occupies smaller longitudinal space, is beneficial to reducing the height of the space attitude measuring instrument of the fighter plane body, and is convenient to use in the limited space below the fighter plane.
In order to facilitate an operator to observe the line of sight of the first observation mirror 9 and the second observation mirror 10, the bent tube eye lens 30 or the electronic eye lens 31 with an electronic display screen can be mounted at the eyepiece ends of the first observation mirror 9 and the second observation mirror 10. Because organism below space is limited, operating personnel direct observation aiming line is comparatively difficult in the eyepiece department of first sight glass 9 and second sight glass 10, and return bend eyepiece 30 or have electronic display screen's electron eyepiece 31 can make operating personnel observe aiming line in the organism side, promotes the convenience of organism space gesture measurement work by a wide margin, is favorable to further promoting measurement of efficiency.
The method for measuring the space attitude of the fighter plane body by using the measuring instrument for the space attitude of the fighter plane body comprises the following steps:
(1) placing a second biaxial digital display inclinometer at an attitude measurement position on the warplane body, and recording the pitch angle and roll angle values of the warplane body displayed by the second biaxial digital display inclinometer;
(2) the space attitude measuring instrument of the fighter plane body is placed below a longitudinal axis marking point at the rear part of the fighter plane, and the height of the tripod telescopic bracket 1 is adjusted to enable the top point of the conical block 6 to be in point contact with the longitudinal axis marking point at the rear part of the fighter plane;
(3) the rotating traversing device is adjusted to ensure that the pitch angle and roll angle values displayed by the first biaxial digital inclinometer 16 are consistent with the pitch angle and roll angle values of the airframe measured by the second biaxial digital inclinometer, and simultaneously ensure that the longitudinal aiming line of the second observation mirror 10 is superposed with the longitudinal axis mark point at the front part of the fighter, and the direction indicated by the cross aiming line of the first observation mirror 9 is the longitudinal axis direction of the airframe of the fighter.
The measuring method is not influenced by the ground flatness and wind power, can create conditions for calibrating a weapon system of a fighter plane at any time in a field environment, can be independently completed by a single person in the body posture determining process, and can complete the measuring work of the body space posture within 5-10 minutes by the single person after proficiency.
In order to provide reference for the longitudinal aiming line of the second observation mirror 10 more accurately, before the step (3), a marking rod is inserted into a concave hole of a longitudinal axis marking point at the front part of the warplane, the marking rod is a truncated cone, a fan-shaped groove is formed in the side wall of the marking rod, two side surfaces of the fan-shaped groove are intersected at the center line of the marking rod, the included angle between the two side surfaces of the fan-shaped groove is 10-120 degrees, and when the rotary traversing device is adjusted in the step (3), the longitudinal aiming line of the second observation mirror is overlapped with the intersection point of the two side surfaces of the fan-shaped groove on the marking rod and the intersection point of the belly junction, so that the longitudinal aiming line of the second observation mirror is overlapped with the longitudinal axis marking point at the front part of the warplane. The marking rod 20 is a truncated cone and can be conveniently fixed in a concave hole of a longitudinal axis marking point inserted into the front part of the fighter through interference fit, an intersecting line between two side surfaces of the fan-shaped groove 21 is a longitudinal extension line of the center of the longitudinal axis marking point at the front part of the fighter, the second observation mirror 10 is easier to observe when being aimed by a longitudinal aiming line, and the position of the indicated longitudinal axis marking point is more accurate. When the marking rod 20 is installed, the fan-shaped groove 21 faces the direction of the longitudinal axis marking point at the rear part of the fighter plane, as long as the second observation mirror 10 can see the intersecting line between the two side surfaces of the fan-shaped groove 21, accurate installation is not needed, when the included angle between the two side surfaces of the fan-shaped groove 21 is too small, the visible angle of the intersecting line between the two side surfaces of the fan-shaped groove 21 is too small, and the intersecting line is easily covered by shadow to influence observation; when the angle between both side surfaces of the fan-shaped groove 21 is too large, the intersection line between both side surfaces of the fan-shaped groove 21 is not significant, and the marking stick 20 is easily deviated or dropped from the concave hole of the longitudinal axis marking point of the front part of the fighter plane, so that the angle between both side surfaces of the fan-shaped groove 21 is preferably 10 ° to 120 °.
In order to help a user quickly find the marking rod 20 through the second observation mirror 10, a laser locator (50) can be arranged on the second observation mirror (10). The laser pointer 50 generates a laser light to roughly indicate the alignment direction of the second sight glass 10, and the user can roughly adjust the alignment direction of the second sight glass 10 to the vicinity of the alignment position by the laser pointer 50.
In the figure, 40 is a vertical axis mark point at the front of the fighter plane and 41 is a vertical axis mark point at the rear of the fighter plane.
Claims (9)
1. The space attitude measuring instrument of the fighter plane body is characterized in that: the device comprises a tripod telescopic support (1), a lower transverse plate (2) is arranged at the top of the tripod telescopic support (1), one side of the lower transverse plate (2) is connected with an upper transverse plate (4) through a longitudinal support (3), a through hole (5) is formed in one end, far away from the longitudinal support (3), of the upper transverse plate (4), a conical block (6) is arranged above the through hole (5), the bottom surface of the conical block (6) is a spherical crown surface (7), the spherical crown surface (7) is in contact fit with the through hole (5), the circle center of the spherical crown surface (7) is coincided with the vertex of the conical block (6), the center of the bottom of the spherical crown surface (7) is connected with a first observation mirror (9) with a cross sight line through a suspension column (8), a first biaxial digital display inclinometer (16) is arranged on the first observation mirror (9), the first biaxial digital display inclinometer (16) can display the pitch angle and the roll angle of the direction indicated by the cross sight line of the first observation mirror (9), a second observation mirror (10) is arranged below the first observation mirror (9), a second observation mirror (10) is connected with a rotary observation mirror device, and a rotary observation mirror device (13) arranged below the lower transverse support, and the second observation mirror (6) is connected with the lower transverse movement device, and the lower transverse movement device.
2. The space attitude measurement instrument for a fighter plane body according to claim 1, characterized in that: the second observation mirror (10) is hinged with the first observation mirror (9) through a hinged seat, a locking nut (11) is installed on a hinged shaft of the hinged seat, and the pitching angle of the second observation mirror (10) relative to the first observation mirror (9) can be adjusted and locked through the locking nut (11).
3. The space attitude measurement instrument for a fighter plane body according to claim 1, characterized in that: the rotating and transverse moving device comprises a rotating tripod head (12), a rotating part of the rotating tripod head (12) is connected with an adjusting support (13), a double-shaft translation table (14) is installed below the rotating tripod head (12), the double-shaft translation table (14) can adjust the horizontal position of the rotating tripod head (12) along the directions of two mutually perpendicular horizontal coordinate axes, and the rotating tripod head (12) is connected with the double-shaft translation table (14) through a connecting piece with a changeable longitudinal height.
4. The space attitude measurement instrument for a fighter plane body according to claim 3, characterized in that: the connecting piece that vertical height can change is including violently putting connecting plate (15) between rotatory cloud platform (12) and biax translation platform (14), and connecting plate (15) one end is connected with biax translation platform (14) top surface, and connecting plate (15) other end is connected with rotatory cloud platform (12) bottom surface.
5. The space attitude measurement instrument for a fighter plane body according to claim 1, characterized in that: the eyepiece ends of the first observation mirror (9) and the second observation mirror (10) are both provided with an elbow eyepiece (30).
6. The space attitude measurement instrument for a fighter plane body according to claim 1, characterized in that: and electronic eyepieces (31) with electronic display screens are arranged at the eyepiece ends of the first observation mirror (9) and the second observation mirror (10).
7. A method for measuring the space attitude of a fighter plane body using the fighter plane body space attitude measurement instrument of any of claims 1, 2, 3, 4, 5 or 6, comprising the steps of:
(1) placing a second biaxial digital display inclinometer at an attitude measurement position on the warplane body, and recording the pitch angle and roll angle values of the warplane body displayed by the second biaxial digital display inclinometer;
(2) the space attitude measuring instrument of the fighter plane body is placed below a longitudinal axis marking point at the rear part of the fighter plane, and the height of the three-foot telescopic support (1) is adjusted to enable the top point of the conical block (6) to be in point contact with the longitudinal axis marking point at the rear part of the fighter plane;
(3) the rotating traversing device is adjusted to enable the pitch angle and the roll angle values displayed by the first biaxial digital inclinometer (16) to be consistent with the pitch angle and the roll angle values of the airframe measured by the second biaxial digital inclinometer, and meanwhile, the longitudinal aiming line of the second observation mirror (10) is ensured to be coincident with the longitudinal axis mark point at the front part of the fighter, and the direction indicated by the cross aiming line of the first observation mirror (9) is the longitudinal axis direction of the airframe of the fighter.
8. The method of measuring the attitude of a warplane body of claim 7, wherein: before the step (3) is carried out, a marking rod (20) is inserted into a concave hole of a longitudinal axis marking point at the front part of the warplane, the marking rod (20) is a truncated cone, a fan-shaped groove (21) is formed in the side wall of the marking rod (20), two side faces of the fan-shaped groove (21) are intersected at the center line of the marking rod (20), the included angle between the two side faces of the fan-shaped groove (21) is 10-120 degrees, and when the rotary traversing device is adjusted in the step (3), the longitudinal aiming line of the second observation mirror (10) is coincided with the intersection point of the intersection line of the two side faces of the fan-shaped groove (21) on the marking rod (20) and the cross point of the belly junction, so that the longitudinal aiming line of the second observation mirror (10) can be coincided with the longitudinal axis marking point at the front part of the warplane.
9. The method of claim 8, wherein the method further comprises the steps of: the second observation mirror (10) is provided with a laser positioner (50).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710271561.9A CN106969744B (en) | 2017-04-24 | 2017-04-24 | Space attitude measuring instrument and method for fighter plane body |
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| CN201710271561.9A CN106969744B (en) | 2017-04-24 | 2017-04-24 | Space attitude measuring instrument and method for fighter plane body |
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| CN106969744B true CN106969744B (en) | 2022-12-16 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1677125A1 (en) * | 2004-12-28 | 2006-07-05 | Leica Geosystems AG | Method and rotative laser for determining a positional information of at least one object |
| CN203116749U (en) * | 2013-02-25 | 2013-08-07 | 上海米度测量技术有限公司 | Precise attitude measurement device |
| CN104006787A (en) * | 2014-05-01 | 2014-08-27 | 哈尔滨工业大学 | High-precision attitude determination method for spacecraft attitude motion simulation platform |
| CN203928893U (en) * | 2014-05-22 | 2014-11-05 | 李平金 | For the body longitudinal axis position determining device that fighter plane armament systems are calibrated |
| CA2853803A1 (en) * | 2013-06-14 | 2014-12-14 | Kabushiki Kaisha Topcon | Flying vehicle guiding system and flying vehicle guiding method |
| CN206683618U (en) * | 2017-04-24 | 2017-11-28 | 焦锋利 | Opportunity of combat body spatial attitude measuring instrument |
-
2017
- 2017-04-24 CN CN201710271561.9A patent/CN106969744B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1677125A1 (en) * | 2004-12-28 | 2006-07-05 | Leica Geosystems AG | Method and rotative laser for determining a positional information of at least one object |
| CN203116749U (en) * | 2013-02-25 | 2013-08-07 | 上海米度测量技术有限公司 | Precise attitude measurement device |
| CA2853803A1 (en) * | 2013-06-14 | 2014-12-14 | Kabushiki Kaisha Topcon | Flying vehicle guiding system and flying vehicle guiding method |
| CN104006787A (en) * | 2014-05-01 | 2014-08-27 | 哈尔滨工业大学 | High-precision attitude determination method for spacecraft attitude motion simulation platform |
| CN203928893U (en) * | 2014-05-22 | 2014-11-05 | 李平金 | For the body longitudinal axis position determining device that fighter plane armament systems are calibrated |
| CN206683618U (en) * | 2017-04-24 | 2017-11-28 | 焦锋利 | Opportunity of combat body spatial attitude measuring instrument |
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