CN-117485604-B - Intersection window rapid planning method for low-orbit spacecraft

Abstract

The invention discloses a low-orbit spacecraft-oriented intersection window rapid planning method, and belongs to the field of aerospace. The implementation method of the invention is that after the rocket applied to ground launching reaches the atmosphere edge, the rocket meets a target spacecraft in the ascending process after one maneuver. And obtaining an intersection window for the spacecraft intersection target task. The rapid planning of the intersection window mainly comprises three steps, namely, firstly, obtaining an ascending reachable range according to the envelope of a shutdown point of a rocket and the pulse size, secondly, judging a rough window by utilizing the altitude, the range reachable range of a voyage and the position of a target in a ground fixed system, thirdly, after the rough window is obtained, shooting the rocket to a target direction to obtain the position of the shutdown point under an inertial system, calculating the speed increment based on the point by adopting a Lambert method, and if the constraint is met, judging that the rocket and the target can meet, namely, realizing the rapid planning of the intersection window facing a low-orbit spacecraft. The method has the advantages of high planning speed and strong applicability.

Inventors

• QIAO DONG
• PANG BO
• WEN CHANGXUAN

Assignees

• 北京理工大学

Dates

Publication Date

20260512

Application Date

20231101

Claims (1)

1. 1. A low-orbit spacecraft-oriented intersection window rapid planning method is characterized by comprising the following steps, Taking the condition that the rocket is shut down after exiting the earth atmosphere, applying a pulse at a shutdown point, and then continuously ascending the rocket to a highest point to stop, so as to realize the reachable range prediction; the reachable range refers to a position set which can be reached in the process of reaching the highest point after the rocket is applied with a pulse; neglecting the rotation influence of the earth, each direction can be obtained by adjusting the rocket shooting direction, and the maximum reachable range of any direction is simplified into an in-plane reachable range, and the state of the rocket when the rocket is shut down is defined as Wherein For the sagittal diameter of the earth core when the machine is shut down, To move the center angle in the plane when the machine is turned off, In order to be able to measure the radial velocity, For the speed of the motion plane in the direction vertical to the sagittal direction of the earth, the corresponding speed increment of the pulse is Let the maneuvering direction be Rocket state after pulse Is that Wherein the method comprises the steps of For the magnitude of the radial velocity after the maneuver, The speed of the vertical direction of the sagittal direction of the earth in the plane of motion after maneuver; From this state, the eccentricity of the rocket after the pulse is obtained And true near point angle Wherein the method comprises the steps of Is the gravitational constant of the central celestial body, Pulse velocity, the position reached by the rocket From direction of speed increment And instantaneous true near point angle Fully define, wherein For the instantaneous sagittal diameter of the earth's center, Rocket reach for instantaneous motion plane internal geocentric angle Represented as From rocket position Easy-to-get height And voyage Wherein For the radius of the earth, Is the ascending course in rocket atmosphere; According to the formula - Solving the reachable range of rocket at the tail end vector diameter In a fixed condition, its course Represented as Wherein the method comprises the steps of As the angular momentum after the maneuver, Is the terminal geocentric sagittal diameter; Intermediate function The corresponding pulse direction is satisfied when the range gets the extreme value In the above Will be described in Obtaining equation by term shifting, squaring and finishing Wherein the method comprises the steps of As an intermediate variable: And Is that The higher order of the trigonometric function of (2) is difficult to solve directly, but when When determined, it is Therefore, the quadratic equation of (2) can be solved reversely, and is fixed Solving for its corresponding satisfaction A kind of electronic device Then at Where the velocity increase is taken When the voyage obtains an extremum; Since only consideration is needed to In the case of the following formula Continuing to simplify, get about Is of the primary equation of (1) The analytical formula of (2) is Wherein the method comprises the steps of As an intermediate variable: Traversing By using Calculating the corresponding extreme end height, wherein in the deducing process, the rising condition of the rocket is relaxed, so that the judging condition is needed to be added, and if the obtained height meets the formula It meets the condition of the rising period of the rocket and brings it into the rocket Obtaining the range corresponding to the altitude; In addition, the obtained reachable range envelope is incomplete by considering only the reachable range in the ascending period, and the situation that the range gets the boundary instead of the extreme value is considered, when the range gets the boundary, the true and near point angle is 180 degrees, and the speed increment direction is considered The corresponding extremum range and altitude are The reachable range envelope of a single shutdown point is obtained, the state of the shutdown point is traversed, and the reachable range of the rising period of the rocket is obtained by combining; The calculation of the whole coarse window is divided into three steps, namely, the first step is that Firstly, calculating the ground fixed system position of the target, then calculating the position vector of the target relative to the launching point, obtaining the course, comparing the course with the obtained reachable range in the first step, if the course is smaller than the maximum course, judging that the rocket and the target can meet, traversing the time period to obtain a first coarse window 1 meeting the meeting condition, and secondly, calculating on the basis of the first coarse window 1 Thirdly, calculating illumination conditions on the basis of the second coarse window 2, and eliminating the window if the intersection time is in the earth shadow area to obtain a final third coarse window 3; step three, based on the obtained third coarse window 3, firstly calculating the window interior The method comprises the steps of converting the reachable range envelope of a single shutdown point into the shooting corresponding to the shooting of a shooting point at the moment target to obtain the state of the shutdown point under an inertia system, calculating by adopting a Lambert algorithm based on the point, and if the minimum speed increment is smaller than the allowable speed increment Judging that the rocket and the target can meet, namely realizing the acquisition of a fine window; And step four, planning the intersecting track of the spacecraft according to the intersecting precision window obtained in the step three aiming at the low-orbit spacecraft with the preset height, so as to realize the intersecting of the rocket and the low-orbit spacecraft.

Description

Intersection window rapid planning method for low-orbit spacecraft Technical Field The invention relates to a method for rapidly planning a meeting window for a low-orbit spacecraft, in particular to a method for rapidly planning and obtaining the meeting window aiming at the meeting problem of a low-orbit non-cooperative spacecraft, and belongs to the field of aerospace. Background Near-earth space is a major area of many aerospace activities, including satellite launching, space exploration, and international space stations, among others, and there are many hidden hazards to near-earth space, such as space debris, waste satellite fragments, and the like. The meeting of the low-orbit spacecraft is an effective means for ensuring the safety of the task in the near-earth space. There are a large number of aircrafts in the near-earth space at any time, and when the existence of the abandoned or the safety-threatening aircrafts is found, the abandoned or the safety-threatening aircrafts need to be intersected in time. The intersection technology for the low-orbit spacecraft is a key technology in the field, and the determination of the intersection window for the low-orbit spacecraft is a precondition for realizing the intersection. In the research of the developed spacecraft intersection window calculation, in the prior art [1] (see [1] Gu Fei to Han Hongwei, wen ], the target interception emission window calculation based on the ascending track reachable range [ J ]. Astronomy report 2022,43 (04): 403-412.) a emission window planning method using ascending track reachable range analysis is provided for the low-orbit target interception task. And determining the ascending reachable range of the interceptor based on the ascending track optimization model, and performing primary screening on the emission window according to the crossing relation of the target understar point and the outer envelope of the ascending track reachable range. Finally, aiming at the screened quasi-emission window, the position relation between the target understar point and each rising duration reachable range subring is accurately judged, so that the accurate emission window is obtained. Because the optimization solution and the reachable range comparison of the track are required to be continuously carried out, the time consumption is long, and the problem of rapid planning of the intersection window of the non-cooperative spacecraft cannot be solved. Meanwhile, the technology does not consider the conditions of burnup constraint, illumination constraint and the like, and can not solve the problem of meeting windows considering various constraints. In the prior art [2] (see Duan J H.Rapid onboard generation of two-dimensional rendezvous windows for autonomous rendezvous mission[J].The Journal of the Astronautical Sciences,2020,67:1320-1343.),, based on the two-dimensional reachable domain of the spacecraft, firstly, the reachable phase range on the target orbit is calculated by considering the waiting time constraint, then, based on the interceptor fuel constraint, the reachable phase range of the target orbit in the interceptor reachable domain is further judged, and finally, a final intersection window is obtained according to the constraint of the total task time. Disclosure of Invention The intersection described in the present invention refers to the position coincidence of the spacecraft, without constraint on the relative speed. The method aims at the problem of the low-orbit target intersection of the spacecraft, and is characterized in that the action of the target is unknown in advance, so that an intersection window meeting the constraints of speed increment, illumination and the like needs to be obtained in a short time, and the intersection of the target spacecraft is realized. Aiming at a low-orbit space non-cooperative spacecraft, solving the problem of meeting windows conforming to constraints based on spacecraft capability boundaries under the conditions of burnup constraint, illumination constraint and the like, and planning the meeting track of the spacecraft according to the obtained meeting windows. The method has the advantages of high planning speed and strong applicability. The aim of the invention is achieved by the following technical scheme. The invention discloses a low-orbit spacecraft-oriented intersection window rapid planning method which is applied to a rocket launched on the ground to reach the atmosphere edge, and the rocket is intersected with a target spacecraft in the ascending process after one maneuver is carried out on the rocket. And obtaining an intersection window for the spacecraft intersection target task. The rapid planning of the intersection window mainly comprises three steps, namely, firstly, obtaining an ascending reachable range according to the envelope of a shutdown point of a rocket and the pulse size, secondly, judging a rough window by utilizing the altitude, the range reacha