A general measuring device and method for body posture and longitudinal axis direction in free state

Abstract

A kind of free state body posture and longitudinal axis direction general measuring equipment and method, including first longitudinal axis marker pole and second longitudinal axis marker pole, wherein first longitudinal axis marker pole includes vertically arranged first main branch rod.The positive effect of the present application is that the present application is not affected by the influence of the machine belly shelter, and the universality is strong, and the weapon system calibration of the warplane can be created at any time in the field environment, the longitudinal axis of the machine body is measured in the free state of the machine body, compared with the previous old method, the universality is stronger, and the previous method can be used on a few machine models, and the present method can be used on all machine models.The method of the present application requires less operators, saves manpower compared with the old method, and the body posture determination process can be completed by a single person independently, and through on-site use demonstration, the measurement of the body space posture can be completed by a single person in 2-5 minutes after being skilled.

Description

Technical Field

[0001] This invention relates to the field of fighter jet attitude and longitudinal axis measurement technology, specifically to a universal measurement device and method for aircraft attitude and longitudinal axis direction in a free state. Background Technology

[0002] Weapon systems used on various types of combat aircraft, such as armed helicopters and fixed-wing fighters, require calibration after installation or adjustment. Furthermore, during their service life, aircraft also require periodic or multiple calibrations as needed. Before calibrating aircraft weapons, the aircraft's spatial attitude, i.e., the spatial direction of its longitudinal axis, must be determined. Then, the aircraft's weapons and targeting equipment must be aligned with this longitudinal axis. Currently, most existing aircraft weapon system calibrations use the reduced-range target calibration method. This method requires personnel to use lifting tools to level the aircraft before calibration, and then use a string line to determine the aircraft's orientation. This calibration method requires at least a dozen personnel coordinating to level the aircraft, and the string line orientation determination is cumbersome and inefficient. Each aircraft attitude measurement takes at least 3-4 hours, which is insufficient to meet the rapid response requirements of modern warfare. Additionally, the measurement operation requires a high degree of ground flatness, making it unsuitable for calibrating aircraft weapons in field environments. The string line measurement process is also significantly affected by wind, and the accuracy of target calibration in outdoor environments cannot be guaranteed. To meet the needs of field calibration, CN106969744A, a fighter jet airframe spatial attitude measuring instrument and method, is suitable for calibrating fighter jets in the field environment at any time. However, this equipment is only suitable for a few aircraft models where there are no obstructions between the longitudinal axis marking points on the fuselage. Most aircraft models have additional equipment or wheel struts or other obstructions on the fuselage. Existing measurement equipment and methods cannot be used to measure aircraft models with obstructions. Summary of the Invention

[0003] To address the problem of measuring the attitude and longitudinal axis of fighter jets with equipment mounted on their fuselage or obstructions such as wheel struts, the present invention aims to provide a universal measuring device and method for the attitude and longitudinal axis of the aircraft in a free state.

[0004] The technical solution adopted by this invention to solve its technical problem is: a universal measuring device for body posture and longitudinal axis direction in a free state, including a first longitudinal axis marking rod and a second longitudinal axis marking rod. The first longitudinal axis marking rod includes a vertically arranged first main support rod. A first posture and orientation adjuster is installed at the bottom of the first main support rod. A first lifting rod capable of vertical movement is installed on one side of the first main support rod. A first lifting rod locking nut is installed on the first main support rod. Rotating the first lifting rod locking nut enables vertical positioning of the first lifting rod. A first marking positioning top rod capable of vertical movement is also installed at the top of the first lifting rod. A first top rod locking handle is provided on the first lifting rod, which can position the first marking positioning top rod on the first lifting rod. A first telescope is installed at the lower part of the center line of the first main support rod, and the first telescope is perpendicular to the first main support rod. A second telescope is installed on the first main support rod corresponding to the position of the first telescope. Both the first and second telescopes are equipped with electronic eyepieces. The first telescope can emit aiming crosshairs. A laser coarse locator is installed between the second telescope and the first telescope. The laser coarse locator's laser... The axis is parallel to the optical axes of the first and second telescopes. A first inclinometer and a display are mounted on the other side of the first main support. The first inclinometer is parallel to the first telescope, and the display is connected to the electronic eyepieces of the first and second telescopes via a data cable. The second longitudinal axis marker rod includes a vertically arranged second main support. A second attitude and azimuth adjuster is mounted at the bottom of the second main support. A second lifting rod capable of vertical elevation is mounted on one side of the second main support. A locking nut for the second lifting rod is mounted on the second main support; rotating the locking nut allows for vertical elevation adjustment. The second lifting rod is vertically positioned by a second marking and positioning top rod that can be vertically raised and lowered. A second locking handle is provided on the second lifting rod to position the second marking and positioning top rod. A second inclinometer is also installed on the second main support rod. The horizontal reference plane of the second inclinometer is perpendicular to the second main support rod. A marking line is located at the geometric center of the second main support rod, and the marking line and the tip of the second marking and positioning top rod are on the same vertical axis. The aiming crosshairs emitted by the first telescope can overlap the marking line. The second telescope is a reflecting mirror, and the normal of the reflecting mirror is parallel to the optical axis of the first telescope, with the same or opposite direction.Both the first attitude and orientation adjuster and the second attitude and orientation adjuster include a cross slide. Two sets of adjusting pads are installed side by side at one end of the bottom of the cross slide. A first rotating plate is fixedly installed on the slider of the cross slide via a cross shaft. A second rotating plate is installed on the first rotating plate and fixedly installed at the bottom of the main support rod. The first rotating plate can rotate relative to the second rotating plate. A micrometer is installed on one side of the first and second rotating plates. Rotating the micrometer can adjust the rotation angle between the first and second rotating plates. A tension spring is installed between the first and second rotating plates. The tension spring causes the first and second rotating plates to have a movement tendency opposite to the force of the micrometer. Both the first and second marking positioning push rods include push rod sleeves. A limit nut is installed at the bottom of the push rod sleeve, and a push rod sleeve end is installed at the top of the push rod sleeve. A pin seat is fitted inside the push rod sleeve end. A pin is provided at one end of the pin seat that extends upward through the push rod sleeve end. A limiting flange is provided at the bottom end of the pin seat. The inner diameter of the push rod sleeve end is smaller than the diameter of the limiting flange. The push rod sleeve end can restrict the upward movement of the limiting flange. A spring is also installed inside the push rod sleeve between the limiting flange and the limiting nut. The spring always tends to make the pin extend upward through the push rod sleeve end. A method for measuring aircraft attitude and longitudinal axis direction using a universal measuring device in a free state includes the following steps: ① Place the second longitudinal axis marker rod below the longitudinal axis marker point at the front of the aircraft, adjust the height of the second lifting rod so that the tip of the second marker positioning rod contacts the longitudinal axis marker point at the front of the aircraft, and point the marking line on the second main support rod towards the rear of the aircraft. Adjust the second attitude and azimuth adjuster so that the longitudinal and lateral readings of the second inclinometer are zero; ② Place the first longitudinal axis marker rod below the longitudinal axis marker point at the rear of the aircraft, adjust the height of the first lifting rod so that the tip of the first marker positioning rod contacts the longitudinal axis marker point at the rear of the aircraft, point the first telescope towards the front of the aircraft, and observe the laser line of the laser coarse locator. The deviation of the mark line from the second longitudinal axis mark rod is determined by adjusting the first attitude and azimuth adjuster to make the laser line press against the mark line. Then, the first attitude and azimuth adjuster is adjusted again to make the longitudinal and lateral readings of the first inclinometer on the first longitudinal axis mark rod zero. Finally, the deviation between the crosshairs of the first telescope and the mark line of the second longitudinal axis mark rod is observed through the display. The azimuth is adjusted so that the crosshairs of the first telescope press against the mark line, and the longitudinal and lateral readings of the inclinometer on the first longitudinal axis mark rod are zero. At this time, the axis of the second telescope or the normal of the reflector is the azimuth line of the longitudinal axis of the aircraft with the deviation and not corrected. ③ The azimuth correction angle and pitch correction angle are calculated to correct the azimuth of the axis of the second telescope or the normal of the reflector, so as to obtain the true azimuth of the longitudinal axis azimuth line JO of the aircraft.The horizontal azimuth correction angle ∠OJ'K' = atctg(h·sinθ / (L·cos2β+h·sinβ·sqr(cos2β-sin2θ))); the pitch correction angle ∠JOJ' = β; where θ is the angle between the y-axis of the aircraft's three-dimensional coordinate system and the horizontal plane, β is the angle between the x-axis and the horizontal plane, L is the horizontal distance between the front and rear marker points when the aircraft is in a horizontal state, and h is the horizontal height difference between the rear longitudinal axis marker point K and the front longitudinal axis marker point J when the aircraft is in a horizontal state. Both θ and β are directly measured using a third inclinometer on a dedicated aircraft measurement platform.

[0005] The positive effects of this invention are as follows: This invention provides a universal measurement method for aircraft attitude and longitudinal axis direction in a free state. It is unaffected by obstructions under the fuselage, has strong versatility, and can create conditions for calibrating the aircraft's weapon systems in field environments. It allows for the measurement of the aircraft's longitudinal axis in a free state, offering greater versatility compared to previous methods, which were only applicable to a limited number of aircraft models. Furthermore, the method requires fewer operators, saving manpower compared to older methods. The aircraft attitude determination process can be completed independently by a single person. Field demonstrations have shown that, with practice, a single person can complete the measurement of the aircraft's spatial attitude within 2-5 minutes. Attached Figure Description

[0006] Figure 1 This is a schematic diagram of the structure of the present invention;

[0007] Figure 2 This is a schematic diagram of the structure of the first vertical axis marker rod;

[0008] Figure 3 This is a schematic diagram of the structure of the second vertical axis marker rod;

[0009] Figure 4 This is a schematic diagram of the attitude and orientation adjuster;

[0010] Figure 5 This is a structural schematic diagram of the positioning rod;

[0011] Figure 6 This is a schematic diagram showing the usage state where the first vertical axis marker is aligned with the second vertical axis marker.

[0012] Figure 7 This is a geometric diagram illustrating the derivation of azimuth and pitch correction values;

[0013] Figure 8 and Figure 9 This is a schematic diagram illustrating the principle of the second method for obtaining the θ and β values. Detailed Implementation

[0014] The universal measuring device for body posture and longitudinal axis direction in a free state described in this invention, such as... Figure 1As shown, it includes a first longitudinal axis marker rod 1 and a second longitudinal axis marker rod 2. The first longitudinal axis marker rod 1 includes a vertically arranged first main support rod 6. A first attitude and orientation adjuster 7 is installed at the bottom of the first main support rod 6. A first lifting rod 3 capable of vertical lifting is installed on one side of the first main support rod 6. A first lifting rod locking nut 5 is installed on the first main support rod 6. Rotating the first lifting rod locking nut 5 can realize the vertical movement and positioning of the first lifting rod 3. A first marking positioning top rod 4 capable of vertical lifting is also installed at the top of the first lifting rod 3. A first top rod locking handle 22 is provided on the first lifting rod 3. The first top rod locking handle 22 can position the first marking positioning top rod 4 on the first lifting rod 3. The center line of the first main support rod 6 is... A first telescope 9 is installed at the lower part, and the first telescope 9 is set perpendicular to the first main support rod 6. A second telescope 8 is installed on the first main support rod 6 corresponding to the position of the first telescope 9. Both the first telescope 9 and the second telescope 8 are equipped with electronic eyepieces. The first telescope 9 can emit aiming crosshairs 13. A laser coarse positioner 10 is installed between the second telescope 8 and the first telescope 9. The laser axis of the laser coarse positioner 10 is parallel to the optical axes of the first telescope 9 and the second telescope 8. A first inclinometer 12 and a display 11 are installed on the other side of the first main support rod 6. The first inclinometer 12 is set parallel to the first telescope 9. The display 11 is connected to the electronic eyepieces of the first telescope 9 and the second telescope 8 through a data cable.

[0015] The second longitudinal axis marker rod 2 includes a vertically arranged second main support rod 18. A second attitude and orientation adjuster 19 is installed at the bottom of the second main support rod 18. A second lifting rod 15 capable of vertical lifting is installed on one side of the second main support rod 18. A second lifting rod locking nut 17 is installed on the second main support rod 18. Rotating the second lifting rod locking nut 17 can realize the vertical movement and positioning of the second lifting rod 15. A second marker positioning top rod 16 capable of vertical lifting is also installed on the top of the second lifting rod 15. The second lifting rod 15 is equipped with... The second push rod locking handle 21 can position the second marking positioning push rod 16 on the second lifting rod 15. A second inclinometer 20 is also installed on the second main support rod 18. The horizontal reference plane of the second inclinometer 20 is perpendicular to the second main support rod 18. A marking line 14 is also provided at the geometric center of the second main support rod 18. The marking line 14 and the tip of the second marking positioning push rod 16 are on the same vertical axis. The aiming crosshair 13 emitted by the first telescope 9 can press against the marking line 14.

[0016] Furthermore, the second telescope 8 is a reflector, and the normal of the reflector surface is parallel to the optical axis of the first telescope 9, and the directions are the same or opposite.

[0017] Furthermore, both the first attitude and orientation adjuster 7 and the second attitude and orientation adjuster 19 may include two translation stages and one rotation stage. Adjusting the translation stages and rotation stage can adjust the tilt angle and orientation of the longitudinal axis marker rod in the horizontal plane. Figure 4 As shown, both the first attitude and orientation adjuster 7 and the second attitude and orientation adjuster 19 include a cross slide 23. Two sets of adjusting feet 24 are installed side by side at one end of the bottom of the cross slide 23. By setting the height of the adjusting feet 24, the cross slide 23 can be placed in a relatively horizontal position to facilitate subsequent measurements. A first rotating plate 26 is fixedly mounted on the slider of the cross slide 23 via a cross shaft 25. A second rotating plate 27 is fitted onto the first rotating plate 26 and fixedly mounted on the bottom of the main support rod. The first rotating plate 26 can rotate relative to the second rotating plate 27. A micrometer 28 is mounted on one side of the first rotating plate 26 and the second rotating plate 27. Rotating the micrometer 28 can adjust the rotation angle between the first rotating plate 26 and the second rotating plate 27. A tension spring 36 is installed between the first rotating plate 26 and the second rotating plate 27. The tension spring 36 causes the first rotating plate 26 and the second rotating plate 27 to have a movement tendency opposite to the force exerted by the micrometer 28. The tension spring 36 allows the first rotating plate 26 and the second rotating plate 27 to rotate and reset. When the longitudinal axis marker rod is pressed against the bottom of the machine body, its top position is fixed relative to the machine body. By adjusting the cross slide 23, the pitch angle and roll angle of the longitudinal axis marker rod relative to the horizontal plane can be adjusted.

[0018] The first longitudinal axis marker rod 1 and the second longitudinal axis marker rod 2, with their respective first marker positioning rod 4 and second marker positioning rod 16, lock the first lifting rod locking nut 5 and the second lifting rod locking nut 17 at the two longitudinal axis marker points at the front and rear of the machine body, and lock the first rod locking handle 22 and the second rod locking handle 21 to maintain a preload.

[0019] To achieve the preload of the first longitudinal axis marker rod 1 and the second longitudinal axis marker rod 2 pressing against the machine body, such as Figure 5As shown, both the first positioning rod 4 and the second positioning rod 16 include a rod sleeve 29. A through hole is provided at the top of the lifting rod to mate with the rod sleeve 29. The vertical movement of the rod sleeve 29 on the lifting rod can be limited by the rod locking handle. A limiting nut 30 is installed at the bottom of the rod sleeve 29, and a rod sleeve end 31 is installed at the upper part of the rod sleeve 29. A pin seat 32 is fitted inside the rod sleeve end 31. A pin 33 is provided at one end of the pin seat 32 that extends upwards through the rod sleeve end 31. The pin 33 is used to press against a preset point position below the machine body. To limit the upward movement of the pin 33, a limiting flange 34 is provided at the bottom end of the pin seat 32. The inner diameter of the rod sleeve end 31 is smaller than the diameter of the limiting flange 34, thus limiting the upward movement of the limiting flange 34. A spring 35 is also installed in the push rod sleeve 29 between the limiting flange 34 and the limiting nut 30. The spring 35 always tends to make the push pin 33 extend upward out of the push rod sleeve end 31, so that the first marking positioning push rod 4 and the second marking positioning push rod 16 both maintain an upward pre-tightening force.

[0020] The first attitude and orientation adjuster 7 can be composed of two translation stages and one rotary stage. The tilt of the first longitudinal axis marker rod 1 relative to the water surface is adjusted by adjusting the translation stages until the lateral tilt angle and longitudinal tilt angle readings of the first inclinometer 12 on the first longitudinal axis marker rod 1 return to zero, indicating that the first longitudinal axis marker rod 1 is perpendicular to the horizontal plane. The rotary stage is then adjusted so that the aiming crosshair 13 of the first telescope 9 on the first longitudinal axis marker rod 1 presses against the marking line 14 on the second longitudinal axis marker rod 2.

[0021] The first attitude and orientation adjuster 7 can adjust the tilt angle and orientation of the first longitudinal axis marker rod 1 in the horizontal plane. The upper end of the first attitude and orientation adjuster 7 is fixed to the lower end of the first main support rod 6 with screws. The groove on the side of the first main support rod 6 matches the side of the first lifting rod 3. The first lifting rod 3 can slide up and down in the groove on the side of the first main support rod 6. The first lifting rod 3 can be locked at a certain height by the locking nut 5 of the first lifting rod.

[0022] The first lifting rod 3 has a round hole at its upper part that connects to the first marking and positioning rod 4. The first marking and positioning rod 4 can be raised and lowered freely within the hole. The first marking and positioning rod 4 can be locked at a certain height by the first rod locking handle 22. The top of the first marking and positioning rod 4 is a small rod with a pointed tip. The small rod is fitted inside the first marking and positioning rod 4 and has a spring inside. When the small rod is pushed upward, there is a pre-tightening force when the small rod hits the marking hole, and the entire length of the first marking and positioning rod 4 has a telescopic range.

[0023] The first inclinometer 12 and the display 11 are fixed on the upper side of the first main support rod 6. The display 11 can be equipped with its own battery or can be powered by an external power source. The data cable of the display 11 is connected to the electronic eyepieces of the first telescope 9 and the second telescope 8. If the second telescope 8 is a reflector 8, the data cable of the display 11 only needs to be connected to the electronic eyepiece of the first telescope 9, and the images observed by the two telescopes can be displayed separately or simultaneously.

[0024] A first telescope 9 is fixed at the lower part of the centerline of the first main support 6. The first telescope 9 has an electronic eyepiece and is arranged perpendicular to the first main support 6. The first inclinometer 12 is arranged parallel to the first telescope 9. A laser coarse locator 10 is fixed on the centerline of the first main support 6 above the first telescope 9. The laser axis is parallel to the optical axis of the first telescope 9. A second telescope 8 or a reflector 8 is fixed on the first main support 6 above the laser coarse locator 10. The second telescope 8 has an electronic eyepiece. The optical axis of the second telescope 8 is parallel to the optical axis of the first telescope 9, or the normal of the reflector 8 is parallel to the optical axis of the first telescope 8. The directions can be the same or opposite.

[0025] The second attitude and orientation adjuster 19 of the second longitudinal axis marker rod 2 can be composed of two translation stages and one rotary stage. The second attitude and orientation adjuster 19 can adjust the tilt angle and orientation of the second longitudinal axis marker rod 2 in the horizontal plane. The upper end of the second attitude and orientation adjuster 19 is fixed to the lower end of the second main support rod 18 with screws.

[0026] The groove on the side of the second main support rod 18 mates with the side of the second lifting rod 15. The second lifting rod 15 can slide up and down within the groove on the side of the second main support rod 18. The second lifting rod 15 can be locked at a certain height by the second top rod locking handle 21. The upper part of the second lifting rod 15 has a round hole that connects to the second marking positioning top rod 16. The second marking positioning top rod 16 can move up and down freely within the hole. The second marking positioning top rod 16 can be locked at a certain height by the second top rod locking handle 21. The top of the second marking positioning top rod 16 is a small rod with a pointed tip. The small rod is fitted inside the second marking positioning top rod 16 and is equipped with a spring. When the small rod is pushed upward, there is a pre-tightening force when the small rod hits the marking hole, and the entire length of the second marking positioning top rod 16 has a telescopic range.

[0027] A second inclinometer 20 is fixed to the upper side of the second main support rod 18. The horizontal reference plane of the second inclinometer 20 is perpendicular to the second main support rod 18 and is fixed to one side of the second main support rod 18. There is a red marking line 14 at the geometric center of the main support rod 18. The tip of the second marking positioning rod 16 of the second longitudinal axis marking rod 2 is on the same vertical axis as the marking line 14.

[0028] The method for measuring the attitude and longitudinal axis of an aircraft using the aforementioned general measuring equipment includes the following steps:

[0029] ① Place the second longitudinal axis marker rod below the longitudinal axis marker point at the front of the fighter jet, adjust the height of the second lift rod so that the tip of the second marker positioning rod contacts the longitudinal axis marker point at the front of the fighter jet, and the marker line on the second main support rod faces directly behind the fuselage. Adjust the second attitude and azimuth adjuster so that the longitudinal and lateral readings of the second inclinometer are zero.

[0030] ② Place the first longitudinal axis marker rod below the longitudinal axis marker point at the rear of the fighter jet. Adjust the height of the first lift rod so that the tip of the first marker positioning rod contacts the longitudinal axis marker point at the rear of the fighter jet. Point the first telescope directly in front of the aircraft and observe the deviation between the laser line of the laser coarse locator and the marker line of the second longitudinal axis marker rod. Adjust the first attitude and azimuth adjuster so that the laser line presses against the marker line. Then adjust the first attitude and azimuth adjuster so that the longitudinal and lateral readings of the first inclinometer on the first longitudinal axis marker rod are zero. Finally, observe the deviation between the crosshairs of the first telescope and the marker line of the second longitudinal axis marker rod through the display. Adjust the azimuth so that the crosshairs of the first telescope press against the marker line and the longitudinal and lateral readings of the inclinometer of the first longitudinal axis marker rod are zero. At this time, the axis of the second telescope or the normal of the reflector is the azimuth line of the aircraft's longitudinal axis with deviation and no correction.

[0031] ③ For example Figure 7 As shown, the azimuth correction angle and elevation correction angle are calculated, and the azimuth of the second telescope axis or the normal of the reflector is corrected to obtain the true azimuth of the longitudinal axis JO of the aircraft.

[0032] Horizontal azimuth correction angle ∠OJ'K'=atctg(h·sinθ / (L·cos2β+h·sinβ·sqr(cos2β-sin2θ)));

[0033] Pitch correction angle ∠JOJ': ∠JOJ' = β;

[0034] Where θ is the angle between the y-axis of the aircraft's three-dimensional coordinate system and the horizontal plane, β is the angle between the x-axis and the horizontal plane, L is the horizontal distance between the front and rear marker points when the aircraft is in a horizontal state, and h is the horizontal height difference between the rear longitudinal axis marker point K and the front longitudinal axis marker point J when the aircraft is in a horizontal state; L and h are fixed known values ​​for each aircraft model;

[0035] The calibration work can extract the azimuth of the second telescope axis or the azimuth of the mirror normal, and then perform azimuth correction on the extracted azimuth line. The horizontal azimuth correction is the value of ∠OJ'K', the elevation correction is the value of ∠JOJ', and finally the true azimuth of JO is obtained.

[0036] The derivation of the correction angle formula in step ③ is as follows: Figure 7 :

[0037] I. Below the front longitudinal axis marker J and the rear longitudinal axis marker K on the abdomen of the aircraft, there are second longitudinal axis markers JJ', which are perpendicular to the horizontal plane of the ground. The first longitudinal axis markers KK' are also perpendicular to the horizontal plane of the ground. Points J' and K' are the projections of points J and K onto the horizontal plane, respectively. Line JO is a line in the longitudinal plane of the aircraft, passing through point J and parallel to the longitudinal axis of the aircraft. O is the perpendicular point of K onto line JO. The aircraft coordinate system Oxyz is translated to point O. The aircraft coordinates are: x-axis corresponds to OJ, z-axis corresponds to OK, y-projection onto the horizontal plane is MO, and KM is perpendicular to OM.

[0038] II. The first longitudinal axis marker rod axis KK', the second telescope 8 or the reflector, and the first telescope 9 are fixedly connected. The central axis KK' of the first longitudinal axis marker rod passes perpendicularly through and is perpendicular to the optical axis of the first telescope 9. The optical axes of the second telescope 8 or the reflector are parallel to those of the first telescope 9. Observe the second longitudinal axis marker rod axis JJ' using the optical axis of the first telescope 9, with the optical axis crosshair aligned with the central axis JJ' of the second longitudinal axis marker rod. The horizontal optical axis of the first telescope 9 passes through point Q on KK' and point T on JJ', and its optical axis is QT.

[0039] III. The normal of the second telescope 8 or the reflector is parallel to the optical axis of the first telescope 9. The normal of the second telescope 8 or the reflector can output the longitudinal axis azimuth TQ represented by the optical axis of the first telescope 9. TQ is the longitudinal axis azimuth line to be corrected. The true longitudinal axis azimuth is JO. Now that TQ is known, the azimuth correction angle ∠K'J'O and the pitch correction angle ∠JOJ' are made on the basis of the TQ azimuth, and the quantities represented by them are corrected to obtain the longitudinal axis azimuth JO of the aircraft.

[0040] IV. Based on geometric relationships Figure 7 We derive that:

[0041] Azimuth correction angle ∠OJ'K': ∠OJ'K'=atctg(h·sinθ / (L·cos2β+h·sinβ·sqr(cos2β-sin2θ)));

[0042] Pitch correction angle ∠JOJ': ∠JOJ' = β;

[0043] Where θ is the angle between the y-axis of the three-dimensional coordinate system and the horizontal plane, β is the angle between the x-axis and the horizontal plane, L is the horizontal distance JO between the front and rear marker points when the system is in a horizontal state, and h is the horizontal height difference between points K and J when the system is in a horizontal state. L and h are fixed known values ​​for each model.

[0044] There are two methods for determining the angle θ between the y-axis and the horizontal plane and the angle β between the x-axis and the horizontal plane in the body coordinate system Oxyz:

[0045] The first method: It can be measured directly on a dedicated measuring platform on the machine body using a third inclinometer;

[0046] The second type: such as Figure 8 As shown, measure the height difference between the four horizontal markers on the aircraft and the horizontal plane. Calculate the angle θ between the y-axis and the horizontal plane, and the angle β between the x-axis and the horizontal plane, using the aircraft's inherent geometry and dimensions. The specific steps are as follows:

[0047] Figure 9 In the diagram, A, B, C, and D are four horizontal markers on the outer surface of the machine body. Points A', B', C', and D' are the vertical projections of the four horizontal markers A, B, C, and D onto the horizontal plane calibrated by the laser level or optical level. AA', BB', CC', and DD' are graduated rulers whose length readings can be read from the optical level or, if using a laser level, from the laser horizontal line projected onto the ruler's scale. E, G, F, and H are the midpoints of the lines connecting AB, BD, DC, and CA, respectively. The machine body's x-axis is associated with FE, and the y-axis is associated with GH.

[0048] The elevation difference between points F and E is: EE' = (AA' + BB' - CC' - DD') / 2;

[0049] The elevation difference between point H and point G: HH' = (AA' + CC' - BB' - DD') / 2;

[0050] The angle between the x-axis and the horizontal plane is ∠EFE' (let the pitch angle be β): β=∠EFE'=arcsin(EE' / EF);

[0051] The angle between the y-axis and the horizontal plane is ∠HGH' (let the angle be θ): θ=∠HGH'=arcsin(HH / HG).

[0052] The above measurement method can create conditions for calibrating the weapon system of fighter jets at any time in the field environment. The determination of the aircraft attitude and longitudinal direction can be completed by 1-2 people, and after becoming proficient, a single person can complete it within 2-5 minutes.

[0053] When the second lifting rod 15 on the second longitudinal axis marker rod 2 is fixed at different heights, the tip of the second marker positioning rod 16 is always on the same line as the marker line 14; when the first lifting rod 3 on the first longitudinal axis marker rod 1 is fixed at different heights, the tip of the first marker positioning rod 4 is always kept on the vertical line of the first longitudinal axis marker rod 1.

[0054] The technical solutions of this invention are not limited to the embodiments described herein. All technical contents not described in detail herein are well-known technologies.

Claims

1. A universal measuring device for body posture and longitudinal axis direction in a free state, characterized in that: It includes a first longitudinal axis marker rod (1) and a second longitudinal axis marker rod (2). The first longitudinal axis marker rod (1) includes a vertically arranged first main support rod (6). A first attitude and orientation adjuster (7) is installed at the bottom of the first main support rod (6). A first lifting rod (3) that can be vertically raised and lowered is installed on one side of the first main support rod (6). A first lifting rod locking nut (5) is installed on the first main support rod (6). Rotating the first lifting rod locking nut (5) can realize the vertical positioning of the first lifting rod (3). A first marker positioning top rod (4) that can be vertically raised and lowered is also installed on the top of the first lifting rod (3). A first top rod locking handle (22) is provided on the first lifting rod (3). The first top rod locking handle (22) can lock the first... The marking and positioning rod (4) is positioned on the first lifting rod (3). A first telescope (9) is installed at the lower part of the center line of the first main support rod (6). The first telescope (9) is set perpendicular to the first main support rod (6). A second telescope (8) is installed on the first main support rod (6) corresponding to the position of the first telescope (9). Both the first telescope (9) and the second telescope (8) are equipped with electronic eyepieces. The first telescope (9) can emit aiming crosshairs (13). A laser coarse locator (10) is installed between the second telescope (8) and the first telescope (9). The laser axis of the laser coarse locator (10) is parallel to the optical axes of the first telescope (9) and the second telescope (8). On the other side of the first main support rod (6) The device is equipped with a first inclinometer (12) and a display (11). The first inclinometer (12) is set parallel to the first telescope (9). The display (11) is connected to the electronic eyepieces of the first telescope (9) and the second telescope (8) via a data cable. The second longitudinal axis marker rod (2) includes a vertically set second main support rod (18). A second attitude and orientation adjuster (19) is installed at the bottom of the second main support rod (18). A second lifting rod (15) that can be vertically raised and lowered is installed on one side of the second main support rod (18). A second lifting rod locking nut (17) is installed on the second main support rod (18). Rotating the second lifting rod locking nut (17) can realize the vertical positioning of the second lifting rod (15). 15) A second mark positioning rod (16) that can be vertically raised and lowered is also installed at the top. A second rod locking handle (21) is provided on the second lifting rod (15). The second rod locking handle (21) can position the second mark positioning rod (16) on the second lifting rod (15). A second inclinometer (20) is also installed on the second main support rod (18). The horizontal reference plane of the second inclinometer (20) is perpendicular to the second main support rod (18). A mark line (14) is also provided at the geometric center of the second main support rod (18). The mark line (14) and the tip of the second mark positioning rod (16) are on the same vertical axis. The aiming crosshair (13) emitted by the first telescope (9) can press against the mark line (14).

2. The universal measuring device for body posture and longitudinal axis direction in a free state according to claim 1, characterized in that: The second telescope (8) is a reflector, and the normal of the reflector is parallel to the optical axis of the first telescope (9), and the direction is the same or opposite.

3. The universal measuring device for body posture and longitudinal axis direction in a free state according to claim 1, characterized in that: Both the first attitude and orientation adjuster (7) and the second attitude and orientation adjuster (19) include a cross slide (23). Two sets of adjusting feet (24) are arranged side-by-side at one end of the bottom of the cross slide (23). A first rotating plate (26) is fixedly mounted on the slider of the cross slide (23) via a cross shaft (25). A second rotating plate (27) is fitted onto the first rotating plate (26). The second rotating plate (27) is fixedly mounted at the bottom of the main support rod. The first rotating plate (26) can... The second rotating plate (27) is rotated, and a micrometer (28) is installed on one side of the first rotating plate (26) and the second rotating plate (27). Rotating the micrometer (28) can adjust the rotation angle position between the first rotating plate (26) and the second rotating plate (27). A tension spring (36) is installed between the first rotating plate (26) and the second rotating plate (27). The tension spring (36) causes the first rotating plate (26) and the second rotating plate (27) to have a movement tendency opposite to the top force of the micrometer (28).

4. The universal measuring device for body posture and longitudinal axis direction in a free state according to claim 1, characterized in that: Both the first marking positioning push rod (4) and the second marking positioning push rod (16) include a push rod sleeve (29). A limit nut (30) is installed at the bottom of the push rod sleeve (29). A push rod sleeve end (31) is installed at the upper part of the push rod sleeve (29). A pin seat (32) is installed inside the push rod sleeve end (31). A pin (33) is provided at one end of the pin seat (32) that extends upward through the push rod sleeve end (31). A limit flange (34) is provided at the bottom end of the pin seat (32). The inner diameter of the push rod sleeve end (31) is smaller than the diameter of the limit flange (34). The push rod sleeve end (31) can restrict the upward movement of the limit flange (34). A spring (35) is also installed inside the push rod sleeve (29) between the limit flange (34) and the limit nut (30). The spring (35) always tends to make the pin (33) extend upward through the push rod sleeve end (31).

5. A method for measuring the attitude and longitudinal direction of an aircraft body in a free state using a universal measuring device for the attitude and longitudinal direction of an aircraft body in a free state, as described in any one of claims 1, 2, 3, or 4, characterized in that: Includes the following steps: ① Place the second longitudinal axis marker rod below the longitudinal axis marker point at the front of the fighter jet, adjust the height of the second lift rod so that the tip of the second marker positioning rod contacts the longitudinal axis marker point at the front of the fighter jet, and the marker line on the second main support rod faces directly behind the fuselage. Adjust the second attitude and azimuth adjuster so that the longitudinal and lateral readings of the second inclinometer are zero. ② Place the first longitudinal axis marker rod below the longitudinal axis marker point at the rear of the fighter jet. Adjust the height of the first lift rod so that the tip of the first marker positioning rod contacts the longitudinal axis marker point at the rear of the fighter jet. Point the first telescope directly in front of the aircraft and observe the deviation between the laser line of the laser coarse locator and the marker line of the second longitudinal axis marker rod. Adjust the first attitude and azimuth adjuster so that the laser line presses against the marker line. Then adjust the first attitude and azimuth adjuster so that the longitudinal and lateral readings of the first inclinometer on the first longitudinal axis marker rod are zero. Finally, observe the deviation between the crosshairs of the first telescope and the marker line of the second longitudinal axis marker rod through the display. Adjust the azimuth so that the crosshairs of the first telescope press against the marker line and the longitudinal and lateral readings of the inclinometer of the first longitudinal axis marker rod are zero. At this time, the axis of the second telescope or the normal of the reflector is the azimuth line of the aircraft's longitudinal axis with deviation and no correction. ③ Calculate the azimuth correction angle and elevation correction angle, correct the azimuth of the second telescope axis or the normal of the reflector, and obtain the true azimuth of the longitudinal axis JO of the aircraft.

6. The method for measuring the body posture and longitudinal axis direction according to claim 5, characterized in that: Horizontal azimuth correction angle ∠OJ'K'=atctg(h•sinθ / (L•cos2β+h•sinβ•sqr(cos2β-sin2θ))); Pitch correction angle ∠JOJ' = β; Where θ is the angle between the y-axis of the body's three-dimensional coordinate system and the horizontal plane, β is the angle between the x-axis and the horizontal plane, L is the horizontal distance between the front and rear marker points when the body is in a horizontal state, and h is the horizontal height difference between the rear longitudinal axis marker point K and the front longitudinal axis marker point J when the body is in a horizontal state.

7. The method for measuring the attitude and longitudinal axis direction of an aircraft body according to claim 6, characterized in that: Both θ and β were directly measured using a third inclinometer on a dedicated measurement platform for the machine body.

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