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A three-pulse rendezvous approach guidance method

A three-pulse, pulse technology, applied in the field of three-pulse rendezvous approach guidance, can solve the problems of weak orbital gravity and long GEO orbital period, and achieve the effect of improving the final position accuracy

Active Publication Date: 2017-07-21
SHENZHEN GRADUATE SCHOOL TSINGHUA UNIV
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Problems solved by technology

Most of the above-mentioned research results are based on the double-pulse C-W guidance method. However, due to the long orbital period and weak orbital gravity of GEO, under the interference of the external orbital environment and the limited precision relative navigation and control conditions, the double-pulse C-W guidance method is adopted. Space robots rendezvous close to The actual trajectory of the GEO satellite deviates greatly from the ideal trajectory

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Embodiment Construction

[0064] The present invention will be further described below with reference to the accompanying drawings and in combination with preferred embodiments.

[0065] In order to describe the relative motion relationship between the space robot and the GEO satellite, establish as figure 1 The coordinate systems shown include: the earth-centered inertial coordinate system ΣI, the space robot orbital coordinate system Σc and the GEO satellite orbital coordinate system Σt. Space robots and GEO satellites can be regarded as particles when they are rendezvous and approaching at a long distance.

[0066] The origin of the earth-centered inertial coordinate system ∑I is located at the center of the earth, the reference plane XY is the earth's flat equator plane when the epoch is J2000.0, the +X axis points to the direction of the vernal equinox at this epoch, the +Z axis points to the North Pole, and the Y axis It forms a right-handed coordinate system with the XZ axis. The origin of the...

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Abstract

The invention discloses a three-pulse intersection approaching guidance method. The method comprises following steps: a relative orbit kinetic equation between a space robot and a GEO satellite is established by means of the C-W equation; a three-pulse C-W guidance status transition equation with revised pulses is established by means of the relative orbit kinetic equation; an optimized objective function for minimum fuel consumption and guidance precision is established according to the status transition equation, the pulse size, direction and time are determined as optimizing parameters; optimized results are obtained according to the optimized objective function. According to the three-pulse intersection approaching guidance method, a revised pulse is added between an inceptive pulse and a final pulse approaching the intersection for increasing guidance precision.

Description

technical field [0001] The invention relates to the field of aircraft navigation, guidance and control, in particular to a three-pulse rendezvous approach guidance method. Background technique [0002] In recent years, the use of space robots to provide on-orbit service to geostationary orbit (Geostationary Orbit, GEO) satellites has become a hot topic. The premise of space robots to perform on-orbit service is to realize the autonomous rendezvous and approach of GEO satellites, so it is fast, accurate, and most An optimal approach guidance method for rendezvous is critical. [0003] The main task of the rendezvous approach guidance method is to design a reasonable and safe rendezvous approach trajectory by using the relative orbital dynamics between spacecraft and taking the rendezvous approach time, position accuracy and fuel consumption as constraints. In aerospace engineering, the Clohessy-Wiltshire (C-W) equation is mainly used to describe the relative orbital dynamics...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/11
CPCG06F17/11
Inventor 高学海李成梁斌李志恒王学谦刘厚德
Owner SHENZHEN GRADUATE SCHOOL TSINGHUA UNIV
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