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Time and fuel pulse optimal traversal method for observing local scope of spatial target during on-orbit service of spacecraft

A local-scale, space-observing technology, applied to instruments, three-dimensional position/course control, adaptive control, etc., can solve the problems of increased mission execution time, spacecraft mass and volume limitations, etc.

Inactive Publication Date: 2015-12-09
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

Method used

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  • Time and fuel pulse optimal traversal method for observing local scope of spatial target during on-orbit service of spacecraft
  • Time and fuel pulse optimal traversal method for observing local scope of spatial target during on-orbit service of spacecraft
  • Time and fuel pulse optimal traversal method for observing local scope of spatial target during on-orbit service of spacecraft

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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 the 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 subdivid...

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 vertex of the four vertex grids in all subdivided grids, and then performs the traversal of the helical form of the precession 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,...

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Abstract

The invention discloses a time and fuel pulse optimal traversal method for observing a local scope of a spatial target during the on-orbit service of a spacecraft, and relates to spacecraft track control. The invention aims at the multi-azimuth on-orbit service observation of one local scope of the spatial target, and provides the method. The method comprises the steps:1, obtaining a state transition equation of the relative position and speed of a tracking spacecraft; 2, enabling an M-degree scope to be divided into 1*1 fine grids; 3, carrying out the traversal of all fine grids in a spiral mode, and determining the traversal sequence; 4, converting the solving of an optimal traversal scheme into a non-linear planning problem; 5, enabling all speed pulses to be converted into the corresponding speed pulses applied to the tracking spacecraft according to the real-time condition of an executing mechanism. The method is used in the field of time and fuel pulse optimal traversal.

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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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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