CN114265421A - Intelligent boresight system for airplane and using method - Google Patents
Intelligent boresight system for airplane and using method Download PDFInfo
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- CN114265421A CN114265421A CN202111514938.1A CN202111514938A CN114265421A CN 114265421 A CN114265421 A CN 114265421A CN 202111514938 A CN202111514938 A CN 202111514938A CN 114265421 A CN114265421 A CN 114265421A
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Abstract
The invention discloses an intelligent aircraft target correcting system which comprises a total station, a measuring rod, a sighting system, a calibration computer and a target correcting holder, wherein a target correcting program is arranged in the calibration computer, the calibration computer is connected with the sighting system through a target correcting data cable, and the calibration computer is connected with the target correcting holder through a servo control cable. The invention surveys and draws the airplane attitude and the target correcting holder through the total station, establishes the relative vertical relation between the target correcting holder and the airplane attitude in the reference system with the total station as the coordinate origin, replaces the mode of adjusting the airplane attitude by adjusting the attitude of the target correcting holder, realizes the manual correction of the yaw angle of the electronic target plate, the intelligent control of the pitch angle and the intelligent control of the target image center and the target image roll angle through the control of a target correcting program of a correcting computer, returns the target correcting compensation coefficient by acquiring the observation data of the observing and aiming system in real time, finishes the target correcting, greatly shortens the target correcting working time, reduces the personnel cooperation requirement and improves the working efficiency.
Description
Technical Field
The invention belongs to the technical field of airplane boresight, and particularly relates to an intelligent airplane boresight system and a using method thereof.
Background
The boresight is the basis for the accurate work of an aircraft sighting system and the accurate positioning of the positions of targets attacked, detected and aerial photographed by the aircraft, and the sighting system, the detection system and the weapon launching system of the aircraft need to be boresight before use. Because the aircraft is a structural body composed of parts with different sizes, the parts are manufactured with processing errors and assembled with assembly errors, and the mounted observing and aiming system has certain system errors, after the aircraft is assembled, the accumulation of the various errors can cause certain precision deviation when the observing and aiming system aims at a target, and in order to find and correct the deviation, the target calibration of the observing and aiming system is needed. Conventional aircraft boresight works by finding a zero offset of the viewing system from the orientation of the aircraft coordinate system X, Y, Z. In order to find the deviation, the aircraft is usually adjusted from an unknown attitude to a horizontal attitude, and then a target is set up, so that the target and the aircraft bear a vertical corresponding relationship in the same horizontal reference plane. The cross line is arranged on the target which is relatively vertical, and when the data of the cross target is measured to have deviation from the known angle, the observing and aiming system needs to correct the deviation within a certain range. In order to let aircraft gesture level park, to this kind of big object of aircraft, need many people to cooperate, through many times of measurement, the cooperation uses tools such as theodolite, hydraulic ram, slowly adjusts aircraft gesture to level, and this process will consume a large amount of manpower, material resources, and artificial influence is great, and work efficiency is not high. Therefore, there is a need for improvement of the existing devices and methods to meet the use requirements.
Disclosure of Invention
In order to solve the problems, the invention aims to provide an intelligent boresight system of an airplane and a using method thereof.
The utility model provides an aircraft intelligence school target system, includes total powerstation, measuring stick, sight system, calibration computer and school target cloud platform, be equipped with the school target procedure in the calibration computer, the calibration computer passes through school target data cable with the sight system and is connected, and the calibration computer passes through servo control cable connection with the school target cloud platform, the school target cloud platform includes the base, the symmetry is equipped with the arc recess on the base, be equipped with the bracing piece in the arc recess, be equipped with the electron target board between two bracing pieces, the bracing piece is electric lift pole.
For convenient intelligent control, the bracing piece includes left branch vaulting pole and right branch vaulting pole, be equipped with the motor on the right branch vaulting pole, the bearing end and the electron target board of motor are connected, be equipped with clutch (not shown in the figure, lower with) between bearing end and the electron target board, be equipped with ball bearing housing on the left branch vaulting pole, ball bearing housing is connected with the electron target board, be equipped with control panel (not shown in the figure, lower with) on the motor, the control panel is connected with the motor, servo control cable is connected with the control panel, is connected with angle displacement sensor and position signal sensor (not shown in the figure, lower with) on the control panel, is equipped with the circuit board on the electron target board, and the control panel is connected with the circuit board, the bracing piece is connected with the control panel, for the direct observation bracing piece pivoted angle of being convenient for, be equipped with the scale on the arc recess.
The use method of the intelligent boresight system for the airplane comprises the following steps:
(1) opening a total station, respectively measuring data of the distance, the height and the angle of a first roll sampling, a second roll sampling, a first pitching sampling and a second pitching sampling on an airplane body by using a measuring rod, and then correspondingly inputting the data into an airplane attitude two, an airplane attitude four, an airplane attitude one and an airplane attitude three in a boresight program;
(2) respectively measuring distance, height and angle data of a first attitude sampling and a second attitude sampling on the target correcting holder by using a total station, inputting the data into a first target plate attitude and a second target plate attitude in a target correcting program, calculating a yaw angle of the airplane through a calculation key of the target correcting program, adjusting a support rod, and rotating the electronic target plate to an angle which is the same as the yaw angle;
calculating the pitch angle of the airplane through a calculation key of a target correcting program, turning on a motor, driving an electronic target plate to rotate by the motor, and adjusting the electronic target plate to the same pitch angle;
(3) measuring distance, height and angle data of a first attitude sampling and a second attitude sampling on the target correcting holder by using a total station, then inputting a first target plate attitude and a second target plate attitude in a target correcting program, and calculating a yaw angle to be 0 degree through a calculation key of the target correcting program, namely, indicating that the axis of the airplane is vertical to the electronic target plate in the horizontal plane, and indicating that the pitch angle of the electronic target plate is the same as the pitch angle of the airplane when the pitch angle is 0 degree;
(4) calculating an intersection point of an extension line of the axis of the airplane and the plane of the electronic target plate through a target correcting program, and when the intersection point is positioned at the edge of the plane of the electronic target plate, starting a motor and starting an electric lifting rod so as to lift the height of the electronic target plate, wherein the axis of the observing and aiming system is parallel to the axis of the airplane, and the distance between the two intersection points of the extension line of the axis of the observing and aiming system and the extension line of the axis of the airplane on the electronic target plate meets the design distance;
(5) calculating the target position by a target correcting program, generating a cross target image on an electronic target plate, observing the target image by an observing and aiming system, transmitting the observed data to a calibration computer in real time through target correcting data cable connection, selecting a target correcting key on the target correcting program to obtain target correcting parameters, transmitting the target correcting parameters to a compensation part in the observing and aiming system by the calibration computer through a target correcting data cable for correction, transmitting the data of the observing and aiming system to the target correcting data of the calibration computer, and finishing target correcting when the values of the pitch angle, the roll angle and the yaw angle are checked to be 0.
Compared with the prior art, the intelligent target correcting system for the airplane and the using method thereof have the beneficial effects that: the invention changes the work of adjusting the attitude of the airplane during the boresight into the work of adjusting the attitude of the boresight holder, effectively avoids the inconvenience caused by adjusting the attitude of a heavy object of the airplane during the boresight, greatly shortens the boresight working time, reduces the personnel cooperation requirement, provides a technical means for quickly finishing the boresight work of the airplane, and improves the working efficiency.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic structural diagram of an intelligent boresight system for an aircraft according to the present invention;
FIG. 2 is a schematic structural diagram of a boresight holder in the intelligent boresight system of an aircraft according to the present invention;
fig. 3 is a schematic structural diagram of a control program in the intelligent boresight system of the aircraft according to the invention.
Shown in the figure, 1-total station, 2-sighting system, 3-axis of sighting system, 4-calibration computer, 5-sighting program, 6-sighting data cable, 7-sighting holder, 8-airplane axis, 9-roll sampling I, 10-roll sampling II, 11-airplane body, 12-pitch sampling I, 13-pitch sampling II, 14-measuring rod, 15-motor, 16-attitude sampling I, 17-attitude sampling II, 18-electronic target plate, 19-target image, 20-base, 21-arc groove, 22-servo control cable, 23-target plate attitude I, 24-target plate attitude II, 25-target position, 26-airplane attitude I, 27-airplane attitude II, 28-airplane attitude three, 29-airplane attitude four, 30-yaw angle, 31-calculation key, 32-target correction key, 33-pitch angle, 34-target correction data, 35-left supporting rod, 36-right supporting rod and 37-ball bearing sleeve.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
It should be understood that the structures, proportions, and dimensions shown in the drawings and described herein are for illustrative purposes only and are not intended to limit the scope of the present invention, which is defined by the claims, but rather by the claims. In addition, the terms such as "upper", "left" and "right" used in the present specification are for convenience of description and are not intended to limit the scope of the present invention, and changes or modifications of the relative relationship thereof may be made without substantial technical changes and modifications.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the term "connected" is to be interpreted broadly, e.g. as a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, an aircraft intelligence school target system, including total powerstation 1, measuring stick 14, sight system 2, calibration computer 4 and school target cloud platform 7, be equipped with school target procedure 5 in the calibration computer 4, calibration computer 4 is connected through school target data cable 6 with sight system 14, and calibration computer 4 is connected through servo control cable 22 with school target cloud platform 7, school target cloud platform 7 includes base 20, the symmetry is equipped with arc recess 21 on the base 20, be equipped with the bracing piece in the arc recess 21, be equipped with electronic target board 18 between two bracing pieces, the bracing piece is electric lift rod. For the convenience of intelligent control, as shown in fig. 2, the support rod comprises a left support rod 35 and a right support rod 36, the right support rod 36 is provided with a motor 15, a bearing end of the motor 15 is connected with the electronic target plate 18, in order to reduce the use of the motor 15, a clutch is arranged between the bearing end and the electronic target plate 18, when the electronic target plate 18 needs to be rotated, the motor 15 is connected with the clutch, the left support rod 35 is provided with a ball bearing sleeve 37, the ball bearing sleeve 37 is connected with the electronic target plate 18, the motor 15 is provided with a control panel, the control panel is connected with the motor 15, the servo control cable 22 is connected with the control panel, the control panel is connected with an angular displacement sensor and a position signal sensor, the electronic target plate 18 is provided with a circuit board, the control panel is connected with the circuit board, the support rod is connected with the control panel, when the support rod needs to be lifted, the motor 15 is disconnected with the clutch, the control panel controls the motor 15 to drive the supporting rod to ascend and descend, and scales are arranged on the arc-shaped groove 21 so as to facilitate direct observation of the rotating angle of the supporting rod.
As shown in fig. 3, the method for using the intelligent boresight system for the aircraft comprises the following steps:
(1) opening the total station 1, respectively measuring data of distances, heights and angles of a first roll sampling 9, a second roll sampling 10, a first pitch sampling 12 and a second pitch sampling 13 of an airplane body 11 by using a measuring rod 14, wherein the points of the first roll sampling 9, the second roll sampling 10, the first pitch sampling 12 and the second pitch sampling 13 are a plurality of measuring reference points set on an airplane frame during airplane manufacturing, and then correspondingly inputting the data into a second airplane attitude 27, a fourth airplane attitude 29, a first airplane attitude 26 and a third airplane attitude 28 in a boresight program 5;
(2) respectively measuring distance, height and angle data of a first attitude sampling 16 and a second attitude sampling 17 on the target correcting holder 7 by using the total station 1, inputting the data into a first target plate attitude 23 and a second target plate attitude 24 in the target correcting program 5, calculating a yaw angle 30 of the airplane by using a calculation key 31 of the target correcting program 5, adjusting the position of a supporting rod in an arc-shaped groove 21, and rotating the electronic target plate 18 to the same angle as the yaw angle 30;
calculating the pitch angle 33 of the airplane through a calculation key 31 of the target correcting program 5, turning on a motor 15, connecting the motor 15 with a clutch, so as to drive the electronic target plate 18 to rotate, and adjusting the electronic target plate 18 to the same pitch angle 33;
(3) measuring distance, height and angle data of a first attitude sample 16 and a second attitude sample 17 on the target correcting holder 7 by using the total station 1, then inputting a first target plate attitude 23 and a second target plate attitude 24 in the target correcting program 5, and calculating a yaw angle 30 to be 0 degree through a calculation key 31 of the target correcting program 5, namely, indicating that an airplane axis 8 is vertical to the electronic target plate 18 in a horizontal plane, and a pitch angle 33 is 0 degree, namely, indicating that the pitch angle of the electronic target plate 18 is the same as the airplane pitch angle;
(4) calculating an intersection point of an extension line of the airplane axis 8 and the plane of the electronic target plate 18 through the target correcting program 5, and when the intersection point is positioned at the edge of the plane of the electronic target plate 18, turning on the motor 15 and starting the electric lifting rod, so that the height of the electronic target plate 18 is lifted, the axis 3 of the observing and aiming system is parallel to the airplane axis, and the distance between the extension line of the axis 3 of the observing and aiming system and the two intersection points of the extension line of the airplane axis 8 on the electronic target plate 18 meets the design distance;
(5) the target position 25 is calculated by the target correcting program 5, a cross target image 19 is generated on the electronic target plate 18, the target image 19 is observed by the observing and aiming system 2, the observed data is transmitted to the calibrating computer 4 in real time through the target correcting data cable 6 connection, a target correcting key 32 on the target correcting program 5 is selected to obtain a target correcting parameter, the calibrating computer 4 sends the target correcting parameter to a compensating part in the observing and aiming system 2 for correction through the target correcting data cable 6, the data of the observing and aiming system 2 is transmitted to the target correcting data 34 of the calibrating computer 4, and the target correcting is completed when the values of the pitch angle, the roll angle and the yaw angle are checked to be 0.
The invention surveys and draws the airplane attitude and the target correcting holder through the total station, establishes the relative vertical relation between the target correcting holder and the airplane attitude in the reference system with the total station as the coordinate origin, during target correction, replaces the working mode of adjusting the airplane attitude by adjusting the attitude of the target correcting holder, realizes the manual correction of the yaw angle of the electronic target plate, the intelligent control of the pitch angle and the intelligent control of the roll angle of the target image center and the target image through the control of a target correcting program of a correcting computer, and returns the target correcting compensation coefficient through acquiring the observation data of the observing and aiming system in real time to finish the target correction.
Other parts of the invention not described in detail are conventional techniques known to the person skilled in the art.
The scope of the present invention is not limited to the technical solutions disclosed in the embodiments, and any modifications, equivalent substitutions, improvements, etc. made to the above embodiments according to the technical spirit of the present invention fall within the scope of the present invention.
Claims (5)
1. An intelligent aircraft target correcting system is characterized by comprising a total station, a measuring rod, a sighting system, a calibration computer and a target correcting holder, wherein a target correcting program is arranged in the calibration computer, the calibration computer is connected with the sighting system through a target correcting data cable, and the calibration computer is connected with the target correcting holder through a servo control cable.
2. The intelligent airplane boresight system as claimed in claim 1, wherein the boresight holder comprises a base, arc-shaped grooves are symmetrically formed in the base, support rods are arranged in the arc-shaped grooves, an electronic target plate is arranged between the two support rods, and the support rods are electric lifting rods.
3. The intelligent target correcting system for the airplane as claimed in claim 2, wherein the support rods comprise a left support rod and a right support rod, the right support rod is provided with a motor, a bearing end of the motor is connected with the electronic target plate, a clutch is arranged between the bearing end and the electronic target plate, the left support rod is provided with a ball bearing sleeve, the ball bearing sleeve is connected with the electronic target plate, the motor is provided with a control board, the control board is connected with the motor, the servo control cable is connected with the control board, the control board is connected with an angular displacement sensor and a position signal sensor, the electronic target plate is provided with a circuit board, the control board is connected with the circuit board, and the support rods are connected with the control board.
4. An intelligent boresight system for aircraft according to claim 2 or 3, wherein the arc-shaped groove is provided with scales.
5. The use method of the intelligent boresight system for the aircraft as claimed in claim 4, is characterized by comprising the following steps:
(1) opening a total station, respectively measuring data of the distance, the height and the angle of a first roll sampling, a second roll sampling, a first pitching sampling and a second pitching sampling on an airplane body by using a measuring rod, and then correspondingly inputting the data into an airplane attitude two, an airplane attitude four, an airplane attitude one and an airplane attitude three in a boresight program;
(2) respectively measuring distance, height and angle data of a first attitude sampling and a second attitude sampling on the target correcting holder by using a total station, inputting the data into a first target plate attitude and a second target plate attitude in a target correcting program, calculating a yaw angle of the airplane through a calculation key of the target correcting program, adjusting a support rod, and rotating the electronic target plate to an angle which is the same as the yaw angle;
calculating the pitch angle of the airplane through a calculation key of a target correcting program, turning on a motor, driving an electronic target plate to rotate by the motor, and adjusting the electronic target plate to the same pitch angle;
(3) measuring distance, height and angle data of a first attitude sampling and a second attitude sampling on the target correcting holder by using a total station, then inputting a first target plate attitude and a second target plate attitude in a target correcting program, and calculating a yaw angle to be 0 degree through a calculation key of the target correcting program, namely, indicating that the axis of the airplane is vertical to the electronic target plate in the horizontal plane, and indicating that the pitch angle of the electronic target plate is the same as the pitch angle of the airplane when the pitch angle is 0 degree;
(4) calculating an intersection point of an extension line of the axis of the airplane and the plane of the electronic target plate through a target correcting program, and when the intersection point is positioned at the edge of the plane of the electronic target plate, starting a motor and starting an electric lifting rod so as to lift the height of the electronic target plate, wherein the axis of the observing and aiming system is parallel to the axis of the airplane, and the distance between the two intersection points of the extension line of the axis of the observing and aiming system and the extension line of the axis of the airplane on the electronic target plate meets the design distance;
(5) calculating the target position by a target correcting program, generating a cross target image on an electronic target plate, observing the target image by an observing and aiming system, transmitting the observed data to a calibration computer in real time through target correcting data cable connection, selecting a target correcting key on the target correcting program to obtain target correcting parameters, transmitting the target correcting parameters to a compensation part in the observing and aiming system by the calibration computer through a target correcting data cable for correction, transmitting the data of the observing and aiming system to the target correcting data of the calibration computer, and finishing target correcting when the values of the pitch angle, the roll angle and the yaw angle are checked to be 0.
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| CN202111514938.1A CN114265421A (en) | 2021-12-13 | 2021-12-13 | Intelligent boresight system for airplane and using method |
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| CN202111514938.1A CN114265421A (en) | 2021-12-13 | 2021-12-13 | Intelligent boresight system for airplane and using method |
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Cited By (1)
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