Non-cooperative target aircraft high-precision orbit parameter identification method
By acquiring line of sight information and relative navigation sensor data, combined with relative navigation filtering algorithm and inertial system conversion matrix calculation, the problem of difficulty in obtaining spatial non-cooperation target track parameters in the prior art is solved, and efficient track parameter identification is achieved.
Patent Information
- Application Number
- CN202510261299.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-06
- Publication Date
- 2025-07-11
AI Technical Summary
In the space non-cooperative target tasks, it is difficult to quickly and with high accuracy to obtain orbital parameter information of the target aircraft, and the computing resource requirements are high, so it cannot meet the real-time requirements.
By obtaining the line of sight information of the target aircraft, combining the installation matrix and deviation position of the relative navigation sensor, the relative navigation filtering algorithm is used to calculate the relative position and speed of the target aircraft to the tracking aircraft system, and the J2000 system position and speed of the target aircraft are further calculated through the inertia system conversion matrix, and finally high-precision orbital parameters are obtained.
It realizes high-precision track parameter identification with low requirements for target morphological characteristics, simple and reliable calculations, high real-time performance, and can quickly obtain track information for non-cooperation targets.
Smart Images
Figure CN120293132A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of space non - cooperative targets, and particularly relates to a method for identifying high - precision orbit parameters of a non - cooperative target aircraft. Background Technique
[0002] In the task of space non - cooperative targets, obtaining the orbit information of the target aircraft is a particularly important link. Patent CN119150920 discloses an orbit positioning technology based on a neural network, which uses different network models to process original data and extract relevant rules to achieve orbit recognition. However, this method requires a large amount of original observation data, high requirements for computing resources and processing speed. At the same time, in practice, it cannot meet the real - time requirements for on - orbit identification of the target orbit of a space aircraft. Patent CN119360218 discloses an identification technology that fuses image and orbit features. By obtaining a measurement image to get the shape and centroid position, and combining the image geometric relationship to determine the orbit features, the target orbit recognition is completed. However, this method has high requirements for the image acquisition device, and is easily interfered by factors such as space stray light and noise during the measurement process. Therefore, the obtained image may cause inaccurate target recognition. Summary of the Invention
[0003] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, providing a method for identifying high - precision orbit parameters of a non - cooperative target aircraft, which can identify the high - precision orbit parameter information of the current target aircraft.
[0004] The object of the present invention is achieved by the following technical solutions: A method for identifying high - precision orbit parameters of a non - cooperative target aircraft includes: obtaining the line - of - sight angle and line - of - sight distance information of the reference point of the target aircraft in the single - aircraft measurement system according to the line - of - sight angle information of the reference point of the target aircraft in the preset single - aircraft measurement system; obtaining the relative position of the target aircraft to the body system of the tracking aircraft according to the installation matrix of the preset relative navigation sensor, the deviation position from the installation position of the preset relative navigation sensor to the centroid of the tracking aircraft body, the line - of - sight angle and line - of - sight distance information of the reference point of the target aircraft in the single - aircraft measurement system, and obtaining the relative position of the reference point of the target aircraft in the orbit system of the target aircraft according to the relative position of the target aircraft to the body system of the tracking aircraft; obtaining the relative position and relative velocity of the target aircraft in the orbit system according to the relative position of the reference point of the target aircraft in the orbit system; obtaining the position and velocity of the target aircraft in the J2000 system according to the relative position and relative velocity of the target aircraft in the orbit system; obtaining the orbit parameter information of the target aircraft according to the position and velocity of the target aircraft in the J2000 system.
[0005] In the above - mentioned method for identifying high - precision orbit parameters of a non - cooperative target aircraft, the relative position Pos of the target aircraft to the body system of the tracking aircraft b is obtained through the following formula:
[0006]
[0007] Among them, Pos b is the relative position of the target aircraft to the local system of the tracking aircraft, and C Sb is the installation matrix of the relative navigation sensor, ΔPos is the deviation position from the installation position of the relative navigation sensor to the centroid of the tracking aircraft's own body, and ρ pec is the line-of-sight distance of the reference point of the target aircraft in the single-aircraft measurement system, and α pec is the azimuth angle of the reference point of the target aircraft in the single-aircraft measurement system, and β pec is the pitch angle of the reference point of the target aircraft in the single-aircraft measurement system.
[0008] In the above high-precision orbit parameter identification method for non-cooperative target aircraft, the relative position of the reference point orbit system of the target aircraft is obtained through the following formula:
[0009] Pos To = C bTo ·Pos b ;
[0010] Among them, C bTo is the transformation matrix from the local system of the tracking aircraft to the orbit system of the target aircraft, Pos To is the relative position of the reference point orbit system of the target aircraft, and Pos b is the relative position of the target aircraft to the local system of the tracking aircraft.
[0011] In the above high-precision orbit parameter identification method for non-cooperative target aircraft, the relative position and relative velocity of the target aircraft orbit system are obtained through the following formula:
[0012]
[0013]
[0014] a To = C bTo ·a b ;
[0015]
[0016] P k = [I - K k H k P k,k-1 ;
[0017] P k,k-1 = ΦP k-1 Φ T + Q;
[0018] Z k= Pos To ;
[0019] where R relTo is the relative position of the target vehicle's orbital system, V relTo is the relative velocity of the target vehicle's orbital system, is the predicted value of the current shot state, is the updated value of the previous shot state, Φ is the state transition matrix, Γ is the state estimation matrix, a To is the acceleration of the target vehicle's orbital system, a b is the acceleration of the tracking vehicle's body system, P k,k-1 is the predicted value of the predicted covariance, P k-1 is the value of the updated covariance matrix of the previous shot, Q is the process noise covariance matrix, K k is the filter gain, H k is the observation model matrix, R is the observation noise covariance matrix, Z k is the observation vector, Pos To is the relative position of the reference point of the target vehicle's orbital system, k is the current shot, x k is the relative position component of the target vehicle's orbital system in the rolling axis direction y k is the relative position component of the target vehicle's orbital system in the pitch axis direction, z k is the relative position component of the target vehicle's orbital system in the yaw axis direction, is the relative velocity component of the target vehicle's orbital system in the rolling axis direction, is the relative velocity component of the target vehicle's orbital system in the pitch axis direction, is the relative velocity component of the target vehicle's orbital system in the yaw axis direction.
[0020] In the above non-cooperative target vehicle high-precision orbital parameter identification method, the position of the target vehicle in the J2000 system is obtained through the following formula:
[0021]
[0022] where R TJ2000 is the position of the target vehicle in the J2000 system, R J2000 is the position of the tracking vehicle in the J2000 system, C iTo is the conversion matrix from the inertial system to the target vehicle's orbital system, R relTo is the relative position of the target vehicle's orbital system.
[0023] In the above non-cooperative target vehicle high-precision orbital parameter identification method, the velocity V of the target vehicle in the J2000 system TJ2000 is obtained through the following formula:
[0024]
[0025] Among them, V TJ2000 is the velocity of the target aircraft in the J2000 system, V J2000 is the velocity of the tracking aircraft in the J2000 system, n T is the orbital angular velocity of the target aircraft, C iTo is the transformation matrix from the inertial system to the target aircraft's orbital system, R relTo is the relative position in the target aircraft's orbital system, V relTo is the relative velocity in the target aircraft's orbital system.
[0026] In the above method for identifying high-precision orbital parameters of a non-cooperative target aircraft, the orbital parameter information of the target aircraft includes the semi-major axis a of the target aircraft's orbit T and the orbital angular velocity n of the target aircraft T .
[0027] In the above method for identifying high-precision orbital parameters of a non-cooperative target aircraft, the semi-major axis a of the target aircraft's orbit T is obtained through the following formula:
[0028] a T = a - a s ;
[0029]
[0030] Ω = arctan2(-C iTo (Y)(1), C iTo (Y)(2));
[0031] U = arctan2(-C iTo (Z)(3), C iTo (X)(3));
[0032] Among them, a T is the semi-major axis of the target aircraft's orbit, R TJ2000 is the position of the target aircraft in the J2000 system, V TJ2000 is the velocity of the target aircraft in the J2000 system, Re is the radius of the earth, a is the instantaneous semi-major axis of the target aircraft's orbit, a s is the short-period term of the semi-major axis of the target aircraft's orbit, μ is the gravitational constant of the earth, E is the energy of orbital motion, J2 is the zonal harmonic term, I is the instantaneous orbital inclination of the target aircraft's orbit, e is the instantaneous eccentricity of the target aircraft's orbit, U is the instantaneous latitude argument of the target aircraft's orbit, ω is the instantaneous argument of perigee of the target aircraft's orbit, L xi is the x-direction component of the vector L, L yi is the y-direction component of the vector L, L zi is the z-direction component of the vector L, Ω is the right ascension of the ascending node of the target aircraft's orbit, C iTo(Y)(3) is the element in the second row and third column of the transformation matrix from the inertial frame to the target vehicle orbit frame, C iTo (Y)(1) is the element in the second row and first column of the transformation matrix from the inertial frame to the target vehicle orbit frame, C iTo (Y)(2) is the element in the second row and second column of the transformation matrix from the inertial frame to the target vehicle orbit frame, C iTo (Z)(3) is the element in the third row and third column of the transformation matrix from the inertial frame to the target vehicle orbit frame, C iTo (X)(3) is the element in the first row and third column of the transformation matrix from the inertial frame to the target vehicle orbit frame.
[0033] In the above non-cooperative target vehicle high-precision orbit parameter identification method, the orbit angular velocity n of the target vehicle T is obtained through the following formula:
[0034]
[0035] where n T is the orbit angular velocity of the target vehicle, a T is the semi-major axis of the target vehicle orbit, and μ is the Earth's gravitational constant.
[0036] A non-cooperative target vehicle high-precision orbit parameter identification system includes: a first module for obtaining the line-of-sight angle and line-of-sight distance information of the target vehicle reference point in the single-vehicle measurement system according to the line-of-sight angle information of the preset target vehicle reference point single-vehicle measurement system; obtaining the relative position of the target vehicle to the tracking vehicle body system according to the preset installation matrix of the relative navigation sensor, the deviation position from the preset installation position of the relative navigation sensor to the centroid of the tracking vehicle body, the line-of-sight angle and line-of-sight distance information of the target vehicle reference point in the single-vehicle measurement system, and obtaining the relative position of the target vehicle reference point orbit system according to the relative position of the target vehicle to the tracking vehicle body system; a second module for obtaining the relative position and relative velocity of the target vehicle orbit system according to the relative position of the target vehicle reference point orbit system; a third module for obtaining the J2000 system position and velocity of the target vehicle according to the relative position and relative velocity of the target vehicle orbit system; a fourth module for obtaining the target vehicle orbit parameter information according to the J2000 system position and velocity of the target vehicle. The present invention has the following beneficial effects compared with the prior art:
[0037] The present invention has relatively low requirements for the target morphological characteristics. Only by combining the obtained target line-of-sight information with data calculation and iteration, it can quickly obtain the high-precision orbit information of the non-cooperative target, with simple and reliable calculation and high real-time performance. Description of the Drawings
[0038] By reading the following detailed description of the preferred embodiments, various other advantages and benefits will become apparent to those of ordinary skill in the art. The drawings are only for the purpose of showing the preferred embodiments and are not considered to be a limitation of the present invention. Moreover, throughout the drawings, the same reference numerals are used to denote the same components. In the drawings:
[0039] Figure 1 is a flowchart of a method for identifying high-precision orbital parameters of a non-cooperative target aircraft provided by an embodiment of the present invention. Detailed implementation manners
[0040] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the drawings. Although the exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided so that the present disclosure can be more thoroughly understood and the scope of the present disclosure can be fully conveyed to those skilled in the art. It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.
[0041] Figure 1 is a flowchart of a method for identifying high-precision orbital parameters of a non-cooperative target aircraft provided by an embodiment of the present invention. As Figure 1 shown, the method includes the following steps:
[0042] According to the line-of-sight angle information of the preset target aircraft reference point single-machine measurement system, obtain the line-of-sight angle and line-of-sight distance information of the target aircraft reference point in the single-machine measurement system; according to the preset installation matrix of the relative navigation sensor, the deviation position from the preset installation position of the relative navigation sensor to the centroid of the tracking aircraft body, the line-of-sight angle and line-of-sight distance information of the target aircraft reference point in the single-machine measurement system, obtain the relative position of the target aircraft to the tracking aircraft body system, and obtain the relative position of the target aircraft reference point in the orbital system according to the relative position of the target aircraft to the tracking aircraft body system;
[0043] Obtain the relative position and relative velocity of the target aircraft orbital system according to the relative position of the target aircraft reference point in the orbital system;
[0044] Obtain the position and velocity of the target aircraft in the J2000 system according to the relative position and relative velocity of the target aircraft orbital system;
[0045] Obtain the orbital parameter information of the target aircraft according to the position and velocity of the target aircraft in the J2000 system.
[0046] The relative position Pos of the target aircraft to the tracking aircraft body system b is obtained through the following formula:
[0047]
[0048] Among them, Pos b is the relative position of the target vehicle to the body frame of the tracking vehicle, C Sb is the installation matrix of the relative navigation sensor, ΔPos is the deviation position from the installation position of the relative navigation sensor to the centroid of the tracking vehicle body, ρ pec is the line-of-sight distance of the reference point of the target vehicle in the single-vehicle measurement system, α pec is the azimuth angle of the reference point of the target vehicle in the single-vehicle measurement system, β pec is the pitch angle of the reference point of the target vehicle in the single-vehicle measurement system.
[0049] The relative position of the reference point of the target vehicle in the orbital system is obtained through the following formula:
[0050] Pos To = C bTo ·Pos b ;
[0051] Among them, C bTo is the transformation matrix from the body frame of the tracking vehicle to the orbital system of the target vehicle, Pos To is the relative position of the reference point of the target vehicle in the orbital system, Pos b is the relative position of the target vehicle to the body frame of the tracking vehicle.
[0052] The relative position and relative velocity of the target vehicle in the orbital system are obtained through the following formula:
[0053]
[0054] a To = C bTo ·a b ;
[0055]
[0056] P k = [I - K k H k P k,k-1 ;
[0057] P k,k-1 = ΦP k-1 Φ T + Q;
[0058] Z k = Pos To ;
[0059] Among them, R relTo is the relative position of the target vehicle in the orbital system, VrelTo is the relative velocity of the target vehicle's orbital system, is the predicted value of the current shot state, is the updated value of the previous shot state, Φ is the state transition matrix, Γ is the state estimation matrix, a To is the acceleration of the target vehicle's orbital system, a b is the acceleration of the tracking vehicle's body system, P k,k-1 is the predicted value of the predicted covariance, P k-1 is the updated covariance matrix value of the previous shot, Q is the process noise covariance matrix, K k is the filter gain, H k is the observation model matrix, R is the observation noise covariance matrix, Z k is the observation vector, Pos To is the relative position of the reference point of the target vehicle in the orbital system, k is the current shot calculated by the algorithm, x k is the relative position component of the target vehicle's orbital system in the roll axis direction y k is the relative position component of the target vehicle's orbital system in the pitch axis direction, z k is the relative position component of the target vehicle's orbital system in the yaw axis direction, is the relative velocity component of the target vehicle's orbital system in the roll axis direction, is the relative velocity component of the target vehicle's orbital system in the pitch axis direction, is the relative velocity component of the target vehicle's orbital system in the yaw axis direction.
[0060] The position of the target vehicle in the J2000 system is obtained through the following formula:
[0061]
[0062] where, R TJ2000 is the position of the target vehicle in the J2000 system, R J2000 is the position of the tracking vehicle in the J2000 system, C iTo is the conversion matrix from the inertial system to the target vehicle's orbital system, R relTo is the relative position of the target vehicle's orbital system.
[0063] The velocity V of the target vehicle in the J2000 system TJ2000 is obtained through the following formula:
[0064]
[0065] where, V TJ2000 is the velocity of the target vehicle in the J2000 system, V J2000 is the velocity of the tracking vehicle in the J2000 system, n T is the orbital angular velocity of the target vehicle, C iTois the transformation matrix from the inertial system to the target vehicle's orbital system, R relTo is the relative position in the target vehicle's orbital system, V relTo is the relative velocity in the target vehicle's orbital system.
[0066] The target vehicle's orbital parameter information includes the semi-major axis a of the target vehicle's orbit T and the orbital angular velocity n of the target vehicle T .
[0067] The semi-major axis a of the target vehicle's orbit T is obtained through the following formula:
[0068] a T = a - a s ;
[0069]
[0070] Ω = arctan2(-C iTo (Y)(1), C iTo (Y)(2));
[0071] U = arctan2(-C iTo (Z)(3), C iTo (X)(3));
[0072] where, a T is the semi-major axis of the target vehicle's orbit, R TJ2000 is the position of the target vehicle in the J2000 system, V TJ2000 is the velocity of the target vehicle in the J2000 system, Re is the radius of the Earth, a is the instantaneous semi-major axis of the target vehicle's orbit, a s is the short-period term of the semi-major axis of the target vehicle's orbit, μ is the gravitational constant of the Earth, E is the energy of the orbital motion, J2 is the zonal harmonic term, H is the angular momentum of the satellite about the Earth's center, I is the instantaneous orbital inclination of the target vehicle's orbit, e is the instantaneous eccentricity of the target vehicle's orbit, U is the instantaneous latitude argument of the target vehicle's orbit, ω is the instantaneous argument of perigee of the target vehicle's orbit L xi is the x-direction component of the vector L, L yi is the y-direction component of the vector L, L zi is the z-direction component of the vector L, Ω is the right ascension of the ascending node of the target vehicle's instantaneous orbit C iTo (Y)(3) is the element in the second row and third column of the transformation matrix from the inertial system to the target vehicle's orbital system, C iTo (Y)(1) is the element in the second row and first column of the transformation matrix from the inertial system to the target vehicle's orbital system, C iTo (Y)(2) is the element in the second row and second column of the transformation matrix from the inertial system to the target vehicle's orbital system, C iTo(Z)(3) is the element in the third row and third column of the transformation matrix from the inertial system to the target vehicle orbit system, C iTo (X)(3) is the element in the first row and third column of the transformation matrix from the inertial system to the target vehicle orbit system.
[0073] The orbital angular velocity n of the target vehicle T is obtained through the following formula:
[0074]
[0075] where, n T is the orbital angular velocity of the target vehicle, a T is the semi-major axis of the target vehicle orbit.
[0076] The tracking vehicle carried by this embodiment uses a wide-area detection camera and a relative navigation sensor to search for the target and obtain the target line-of-sight information. The relative position and velocity information are obtained by using the relative navigation filtering algorithm, and then the orbital parameters of the target vehicle based on the current data are obtained by combining the orbital parameter information of the tracking vehicle. Finally, the default orbital parameters of the target vehicle are continuously estimated and iterated by using the update of the relative navigation sensor data, so as to identify the high-precision orbital parameter information of the current target vehicle.
[0077] According to the rough pitch angle β xj , azimuth angle α xj given by the wide-area detection camera, the relative navigation sensor tracks the target and measures the accurate line-of-sight distance ρ pec , pitch angle β pec and azimuth angle α pec .
[0078] 1) Calculate the relative position Pos of the target vehicle to the body coordinate system of the tracking vehicle b
[0079]
[0080] where, ΔPos is the deviation position from the installation position of the relative navigation sensor to the centroid of the tracking vehicle body, C Sb is the installation matrix from the measurement system of the relative navigation sensor to the body coordinate system of the tracking vehicle.
[0081] 2) Calculate the relative position Pos in the target vehicle orbit system To
[0082] Pos To = C bTo · Pos b
[0083] where, C bTo is the transformation matrix from the body coordinate system of the tracking vehicle to the target vehicle orbit system.
[0084] 3) Calculate the relative position R of the target vehicle's orbital system relTo and the relative velocity V relTo
[0085]
[0086] wherein, is the predicted value of the current shot state, is the updated value of the previous shot state, Φ is the state transition matrix, Γ is the state estimation matrix, and a To is the acceleration of the target vehicle's orbital system.
[0087] a To = C bTo ·a b
[0088] wherein, a b is the acceleration of the tracking vehicle's body coordinate system.
[0089] P k,k-1 = ΦP k-1 Φ T + Q
[0090] wherein, P k,k-1 is the predicted value of the predicted covariance, P k-1 is the value of the updated covariance matrix of the previous shot, and Q is the process noise covariance matrix.
[0091]
[0092] wherein, K k is the filtering gain, H k is the observation model matrix, and R is the observation noise covariance matrix.
[0093]
[0094] P k = [I - K k H k P k,k-1
[0095]
[0096] wherein, Z k is the observation vector, Z k = Pos To
[0097]
[0098] 4) Calculate the position R of the target vehicle in the J2000 coordinate system TJ2000 and the velocity V TJ2000
[0099]
[0100] Among them, R J2000 is the position of the tracking vehicle in the J2000 system, and C iTo is the transformation matrix from the inertial system to the orbital system of the target vehicle.
[0101]
[0102] Among them, V J2000 is the velocity of the tracking vehicle in the J2000 system, n T is the orbital angular velocity of the target vehicle.
[0103] 5) Calculate the information related to the orbit of the target vehicle
[0104] a) Calculate the transformation matrix C from the inertial system to the orbital system of the target vehicle iTo
[0105]
[0106]
[0107] C iTo (X) = C iTo (Y) × C iTo (Z)
[0108] b) Calculate the semi-major axis a of the target vehicle's orbit T
[0109]
[0110] Among them, μ = 3.986005 × 10 14 .
[0111]
[0112] Among them, p is the semi-latus rectum,
[0113]
[0114] Ω = arctan2(-C iTo (Y)(1), C iTo (Y)(2))
[0115] U = arctan2(-C iTo (Z)(3), C iTo (X)(3))
[0116]
[0117] where J2 = 1.08263×10 -3 , and Re is the radius of the Earth.
[0118] a T = a - a s
[0119] c) Calculate the orbital angular velocity n of the target vehicle T
[0120]
[0121] This embodiment also provides a high-precision orbital parameter identification system for a non-cooperative target vehicle. The system includes: a first module for obtaining the line-of-sight angle and line-of-sight distance information of the target vehicle reference point in the single-vehicle measurement system according to the preset line-of-sight angle information of the target vehicle reference point single-vehicle measurement system; obtaining the relative position of the target vehicle to the tracking vehicle body system according to the preset installation matrix of the relative navigation sensor, the preset deviation position from the installation position of the relative navigation sensor to the centroid of the tracking vehicle body, the line-of-sight angle and line-of-sight distance information of the target vehicle reference point in the single-vehicle measurement system, and obtaining the relative position of the target vehicle reference point in the orbital system according to the relative position of the target vehicle to the tracking vehicle body system; a second module for obtaining the relative position and relative velocity of the target vehicle orbital system according to the relative position of the target vehicle reference point orbital system; a third module for obtaining the position and velocity of the target vehicle in the J2000 system according to the relative position and relative velocity of the target vehicle orbital system; a fourth module for obtaining the orbital parameter information of the target vehicle according to the position and velocity of the target vehicle in the J2000 system.
[0122] This embodiment uses the loaded wide-area camera to search and determine the target, uses the satellite attitude control to assist the relative navigation sensor loaded on itself to obtain the target relative position information, and then uses the orbital information of the tracking vehicle and the target relative position to identify the navigation information and orbital parameters of the target vehicle. Subsequently, relevant guidance tasks are completed according to the calculated data of the target vehicle. This embodiment can identify the high-precision orbital parameter information of the current target vehicle.
[0123] Although the present invention has been disclosed above with preferred embodiments, it is not used to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes, and decorations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention all belong to the protection scope of the technical solution of the present invention.
Claims
1. A method for identifying high-precision orbital parameters of a non-cooperative target aircraft, characterized in that Including: Obtaining the line-of-sight angle and line-of-sight distance information of the target aircraft reference point in the single-aircraft measurement system based on the line-of-sight angle information of the single-aircraft measurement system of the preset target aircraft reference point; obtaining the relative position of the target aircraft to the tracking aircraft body system based on the preset installation matrix of the relative navigation sensor, the deviation position from the preset installation position of the relative navigation sensor to the centroid of the tracking aircraft body, the line-of-sight angle and line-of-sight distance information of the target aircraft reference point in the single-aircraft measurement system, and obtaining the relative position of the target aircraft reference point in the orbital system based on the relative position of the target aircraft to the tracking aircraft body system; Obtaining the relative position and relative velocity of the target aircraft orbital system based on the relative position of the target aircraft reference point in the orbital system; Obtaining the position and velocity of the target aircraft in the J2000 system based on the relative position and relative velocity of the target aircraft orbital system; Obtaining the orbital parameter information of the target aircraft based on the position and velocity of the target aircraft in the J2000 system.
2. The high-precision orbital parameter identification method for a non-cooperative target aircraft according to claim 1, characterized in that: The relative position Pos of the target vehicle to the tracking vehicle's own system b is obtained through the following formula: Among them, Pos b is the relative position of the target vehicle to the body system of the tracking vehicle, C Sb is the installation matrix of the relative navigation sensor, ΔPos is the deviation position from the installation position of the relative navigation sensor to the centroid of the tracking vehicle body, ρ pec is the line-of-sight distance of the reference point of the target vehicle in the single-vehicle measurement system, α pec is the azimuth angle of the reference point of the target vehicle in the single-vehicle measurement system, β pec is the pitch angle of the reference point of the target vehicle in the single-vehicle measurement system.
3. The high-precision orbit parameter identification method for non-cooperative target aircraft according to claim 1, characterized in that: The relative position of the target aircraft reference point in the orbital system is obtained through the following formula: Pos To = C bTo ·Pos b ; Among them, C bTo is the transformation matrix for tracking the conversion from the local system of the vehicle to the orbital system of the target vehicle, and Pos To is the relative position in the orbital system of the reference point of the target vehicle, and Pos b is the relative position from the target vehicle to the local system of the tracking vehicle.
4. The high-precision orbital parameter identification method for a non-cooperative target aircraft according to claim 1, characterized in that: The relative position and relative velocity of the target aircraft orbital system are obtained through the following formula: a To = C bTo ·a b ; P k = [I - K k H k P k,k-1 ; P k,k-1 = ΦP k-1 Φ T + Q; Z k = Pos To ; where R relTo is the relative position of the target vehicle's orbital system, V relTo is the relative velocity of the target vehicle's orbital system, is the predicted value of the current shot state, is the updated value of the previous shot state, Φ is the state transition matrix, Γ is the state estimation matrix, a To is the acceleration of the target vehicle's orbital system, a b is the acceleration of the tracking vehicle's body system, P k,k-1 is the predicted value of the predicted covariance, P k-1 is the updated covariance matrix value of the previous shot, Q is the process noise covariance matrix, K k is the filtering gain, H k is the observation model matrix, R is the observation noise covariance matrix, Z k is the observation vector, Pos To is the relative position of the target vehicle's reference point in the orbital system, k is the current shot, x k is the relative position component of the target vehicle's orbital system in the roll axis direction, y k is the relative position component of the target vehicle's orbital system in the pitch axis direction, z k is the relative position component of the target vehicle's orbital system in the yaw axis direction, v xk is the relative velocity component of the target vehicle's orbital system in the roll axis direction, v yk is the relative velocity component of the target vehicle's orbital system in the pitch axis direction, v zk is the relative velocity component of the target vehicle's orbital system in the yaw axis direction.
5. The high-precision orbital parameter identification method for non-cooperative target aircraft according to claim 1, characterized in that: The position of the target aircraft in the J2000 system is obtained through the following formula: Among them, R TJ2000 is the position of the target aircraft in the J2000 coordinate system, and R J2000 is the position of the tracking aircraft in the J2000 coordinate system. C iTo is the transformation matrix from the inertial coordinate system to the orbit coordinate system of the target aircraft, and R relTo is the relative position in the orbit coordinate system of the target aircraft.
6. The high-precision orbital parameter identification method for non-cooperative target aircraft according to claim 1, wherein: The velocity V of the target aircraft in the J2000 system TJ2000 is obtained through the following formula: Among them, V TJ2000 is the velocity of the target aircraft in the J2000 coordinate system, V J2000 is the velocity of the tracking aircraft in the J2000 coordinate system, n T is the orbital angular velocity of the target aircraft, C iTo is the transformation matrix from the inertial coordinate system to the orbital coordinate system of the target aircraft, R relTo is the relative position in the orbital coordinate system of the target aircraft, V relTo is the relative velocity in the orbital coordinate system of the target aircraft.
7. The high-precision orbital parameter identification method for non-cooperative target aircraft according to claim 1, wherein: The orbital parameter information of the target vehicle includes the semi-major axis a of the target vehicle's orbit T and the orbital angular velocity n of the target vehicle T .
8. The high-precision orbit parameter identification method for a non-cooperative target aircraft according to claim 7, characterized in that: Semi-major axis a of the target vehicle orbit T Obtained by the following formula: a T = a - a s ; Ω = arctan2(-C iTo (Y)(1), C iTo (Y)(2)); U = arctan2(-C iTo (Z)(3), C iTo (X)(3)); Among them, a T is the semi-major axis of the target vehicle's orbit, R TJ2000 is the position of the target vehicle in the J2000 coordinate system, V TJ2000 is the velocity of the target vehicle in the J2000 coordinate system, Re is the radius of the Earth, a is the instantaneous semi-major axis of the target vehicle's orbit, a s is the short-period term of the semi-major axis of the target vehicle's orbit, μ is the gravitational constant of the Earth, E is the energy of the orbital motion, J2 is the zonal harmonic term, I is the instantaneous orbital inclination of the target vehicle's orbit, e is the instantaneous eccentricity of the target vehicle's orbit, U is the instantaneous argument of latitude of the target vehicle's orbit, ω is the instantaneous argument of perigee of the target vehicle's orbit, L xi is the x-direction component of the vector L, L yi is the y-direction component of the vector L, L zi is the z-direction component of the vector L, Ω is the right ascension of the ascending node of the target vehicle's orbit, C iTo (Y)(3) is the element in the second row and third column of the transformation matrix from the inertial coordinate system to the target vehicle's orbital coordinate system, C iTo (Y)(1) is the element in the second row and first column of the transformation matrix from the inertial coordinate system to the target vehicle's orbital coordinate system, C iTo (Y)(2) is the element in the second row and second column of the transformation matrix from the inertial coordinate system to the target vehicle's orbital coordinate system, C iTo (Z)(3) is the element in the third row and third column of the transformation matrix from the inertial coordinate system to the target vehicle's orbital coordinate system, C iTo (X)(3) is the element in the first row and third column of the transformation matrix from the inertial coordinate system to the target vehicle's orbital coordinate system.
9. The high-precision orbit parameter identification method for non-cooperative target aircraft according to claim 7, characterized in that: Target vehicle orbital angular velocity n T Obtained by the following formula: where n T is the orbital angular velocity of the target vehicle, a T is the semi-major axis of the target vehicle's orbit, and μ is the gravitational constant of the Earth.
10. A high-precision orbit parameter identification system for a non-cooperative target aircraft, characterized in that Including: The first module is used to obtain the line-of-sight angle and line-of-sight distance information of the target aircraft reference point in the single-aircraft measurement system according to the line-of-sight angle information of the single-aircraft measurement system of the preset target aircraft reference point; obtaining the relative position of the target aircraft to the tracking aircraft body system based on the preset installation matrix of the relative navigation sensor, the deviation position from the preset installation position of the relative navigation sensor to the centroid of the tracking aircraft body, the line-of-sight angle and line-of-sight distance information of the target aircraft reference point in the single-aircraft measurement system, and obtaining the relative position of the target aircraft reference point in the orbital system based on the relative position of the target aircraft to the tracking aircraft body system; The second module is used to obtain the relative position and relative velocity of the target aircraft orbital system according to the relative position of the target aircraft reference point in the orbital system; The third module is used to obtain the position and velocity of the target aircraft in the J2000 system according to the relative position and relative velocity of the target aircraft orbital system; The fourth module is used to obtain the orbital parameter information of the target aircraft according to the position and velocity of the target aircraft in the J2000 system.