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Tilt fly-around retention control effect evaluation method based on eccentricity ratio tilt angle vector

A technology of maintaining control and inclination vector, applied in non-electric variable control, control/regulation system, three-dimensional position/channel control and other directions, can solve the problem of less four pulses, improve the accuracy of orbit control, easy to popularize, use, and operate strong effect

Active Publication Date: 2022-02-18
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

At present, the evaluation method for the effect of a single maneuver control is relatively mature, but there is little engineering experience in the use of four-pulse orbiting configuration maintenance control. At the same time, considering the constraints of the spacecraft’s own fuel, the combined control of the inclination angle and the ascending node is in low orbit. It is also rarely implemented in satellite maneuvers, so it is necessary to study the evaluation method of configuration maintenance control effect to improve the accuracy of orbit control based on relative motion model

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  • Tilt fly-around retention control effect evaluation method based on eccentricity ratio tilt angle vector
  • Tilt fly-around retention control effect evaluation method based on eccentricity ratio tilt angle vector
  • Tilt fly-around retention control effect evaluation method based on eccentricity ratio tilt angle vector

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Embodiment Construction

[0074] The present invention will be described in detail below in conjunction with specific embodiments and accompanying drawings.

[0075] The present invention is based on the eccentricity inclination vector's method for evaluating the control effect of tilting around and flying around, such as figure 1 As shown, the specific steps are as follows:

[0076] Step 1: Obtain the ground precision orbit determination system to determine the orbit parameter Orbit before the first pulse maneuver ignition of the orbiting spacecraft C10 ;

[0077] Orbit C10 :{T 1 、a C10 、e C10 i C10 , Ω C10 , ω C10 , M C10}

[0078] Among them, T 1 The time to maintain control of the first impulse maneuver for the orbiting spacecraft, a C10 is the semi-major axis of orbit around the spacecraft before the first pulse maneuver ignition, e C10 is the orbital eccentricity before the first pulse maneuver ignition of the orbiting spacecraft, i C10 is the orbital inclination before the first pu...

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Abstract

The invention discloses a tilt fly-around retention control effect evaluation method based on an eccentricity rate tilt angle vector. According to the method, for a four-pulse configuration retention control process of a formation control model built based on a Gaussian perturbation equation, quick evaluation is carried out on a configuration parameter capture control effect according to the absolute trajectory determination data of a ground measurement and control system; and normal and tangential trajectory control engine thrust efficiency of four pulses is calibrated respectively. With the method adopted, trajectory control precision is improved. The method is high in reliability, high in operability, is easy to popularize and use, and has important guiding significance for task implementation.

Description

technical field [0001] The invention belongs to the technical field of aerospace measurement and control, and in particular relates to a method for evaluating the control effect of tilt fly-around maintenance based on an eccentricity tilt angle vector. Background technique [0002] With the rapid development of small satellite technology, spacecraft formation technology has been widely used. Spacecraft formation flight mission design is generally composed of a group of spatially distributed small satellites flying around each other. The satellites in the formation form a virtual spacecraft through information exchange and cooperative work to realize the functions of large satellites or traditional single satellites. For space missions that cannot be realized by large satellites, a reasonable configuration can provide the stable baseline required to complete the space mission, and it is also conducive to reducing the fuel consumption of each member spacecraft of the system fo...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 马宏孙守明曹静李恒年张智斌钟文冬李超李军锋叶修松肖振国耶刚强杜冬梅
Owner CHINA XIAN SATELLITE CONTROL CENT
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