A time and fuel pulse optimal traversal method for the local range of space objects observed by spacecraft on-orbit service

A space-based, local-scale technology, applied in instrumentation, 3D position/course control, adaptive control, etc., to solve problems such as increased mission execution time, spacecraft mass and volume constraints, etc.

Inactive Publication Date: 2017-10-03
HARBIN INST OF TECH (BEIJING) IND TECH INNOVATION RES INST CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Today's launch vehicle has a very limited carrying capacity, and the mass and volume of the spacecraft are strictly limited, which limits the fuel that the spacecraft can carry. Therefore, the problem of fuel consumption has to be considered when performing space missions, but it cannot Because blindly reducing fuel consumption will inevitably lead to a significant increase in the time for performing missions, so when formulating a space mission plan, it is necessary to comprehensively consider the two important factors of time and fuel consumption

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  • A time and fuel pulse optimal traversal method for the local range of space objects observed by spacecraft on-orbit service
  • A time and fuel pulse optimal traversal method for the local range of space objects observed by spacecraft on-orbit service
  • A time and fuel pulse optimal traversal method for the local range of space objects observed by spacecraft on-orbit service

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specific Embodiment approach 1

[0032] Specific implementation mode 1: The time and fuel pulse optimal traversal method of a spacecraft on-orbit service observation space target local range according to this implementation mode is specifically prepared according to the following steps:

[0033] Step 1. Without considering perturbation, when the target s is in a circular orbit, the relative orbital motion model of the tracking spacecraft is obtained and described as the C-W equation; according to the C-W equation, the relative position r(t) and relative velocity of the tracking spacecraft are obtained The state transition equation of ;

[0034] Step 2. Determine the direction of the center of the local range to be observed as the direction of the observation center line according to the task requirements. In two mutually perpendicular directions in a plane perpendicular to the observation center line, there is an angle range of M°, and the M° angle The range of angles is equally divided into l×l subdivided g...

specific Embodiment approach 2

[0046] Specific embodiment two: the difference between this embodiment and specific embodiment one is: in step one, when the perturbation is not considered, when the target s is in a circular orbit, the relative orbital motion model of the tracking spacecraft is described as a C-W equation; According to the C-W equation, the relative position r(t) and relative velocity of the tracking spacecraft are obtained The specific process of the state transition equation is:

[0047] Let the target be s, and the tracking spacecraft be c; let the spacecraft serve the observation space target in orbit, that is, the target s is in a near-circular orbit, and take the orbital coordinate system s-xyz of the target as the relative motion coordinate system; the relative motion coordinate system The origin is fixed to the center of mass of the target and moves along the orbit with the center of mass of the target, the x-axis of the relative motion coordinate system and the geocentric vector r o...

specific Embodiment approach 3

[0068] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that the traversal order of the spiral form in Step 3 is specifically:

[0069] When l is an even number, the starting grid selects any one of the four vertex grids in all the subdivided grids, and performs the traversal of the spiral form in the clockwise or counterclockwise direction;

[0070] If any one of the four grids in the middle of all the subdivision grids is selected, the helical traversal of the unscrewed form is performed in a clockwise or counterclockwise direction;

[0071] There are a total of 16 optional traversal sequences for spiral traversal in the form of precession and spiral traversal in the form of precession, and one of the 16 optional traversal sequences can be selected arbitrarily according to the actual situation;

[0072] Taking the subdivision grid when l is an even number as an example, the starting grid can choose A, B, C, D, E, F, G, One of the eight grids of ...

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Abstract

The invention discloses a time and fuel pulse optimal traversal method for the local area of ​​space objects observed by spacecraft on-orbit service, and the invention relates to spacecraft orbit control. The present invention aims to solve the problem of multi-directional on-orbit service observation of a certain local area of ​​a space target, and proposes a time and fuel pulse optimal traversal method of a space vehicle on-orbit service to observe a local area of ​​a space target. The method is to firstly obtain the state transition equation for tracking the relative position and relative velocity of the spacecraft; secondly, divide the angle range of M° into l×l subdivided grids; The traversal order is determined by sub-grid traversal; 4. The problem of solving the optimal traversal scheme is transformed into a nonlinear programming problem; 5. According to the real-time situation of the actuator, it is converted into a corresponding speed pulse and applied to the tracking spacecraft. The invention applies to the field of optimal traversal of time and fuel pulses.

Description

technical field [0001] The invention relates to spacecraft orbit control, in particular to a time and fuel pulse optimal traversal method for spacecraft on-orbit service observation space target local range. Background technique [0002] An important research hotspot in today's aerospace field is the close-range relative orbit on-orbit service control of spacecraft, which is often applied to space tasks such as formation flight, on-orbit maintenance, rendezvous and docking, and tracking observation. With the gradual development of aerospace technology, the complexity of on-orbit service space tasks has increased, and at the same time, the refinement requirements for space operations have also greatly increased. When performing tracking and observation tasks on space targets, it is not only required to have a full understanding of the overall situation of the target, but sometimes it is also required to have detailed observation results of multiple directions for a certain lo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10G05B13/04
Inventor 孙延超凌惠祥马广富王俊高寒李传江
Owner HARBIN INST OF TECH (BEIJING) IND TECH INNOVATION RES INST CO LTD
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