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Method and device for determining relative orbit of spacecraft formation

A technology of relative orbit and determination method, applied in the aerospace field, can solve problems such as low flight control accuracy, and achieve the effects of reducing cumbersome calculation, reducing power consumption, and reducing long-distance measurement

Active Publication Date: 2018-09-04
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] In view of this, the embodiment of the present invention expects to provide a method and device for determining the relative orbit of a spacecraft, which at least partially solves the above-mentioned problem of low flight control accuracy

Method used

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  • Method and device for determining relative orbit of spacecraft formation
  • Method and device for determining relative orbit of spacecraft formation
  • Method and device for determining relative orbit of spacecraft formation

Examples

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example 1

[0095] Such as image 3 As shown, this example provides a method for relative orbit determination of a spacecraft formation, which may include:

[0096] Step 1: Measure the absolute position / velocity of star A (equivalent to the aforementioned first spacecraft) at the initial moment by the ground station, obtain the absolute position / velocity of star A within one circle through orbit forecasting, and calculate a The instantaneous orbital elements of star A in the circle.

[0097]Step 2: The measuring instruments carried by the spacecraft itself measure the relative distance and angle of the two spacecraft in a short period of time, and then obtain their estimated values ​​through relative measurement. From the absolute position / velocity of star A at the initial moment and the estimated value of the relative distance and angle of the spacecraft, the relative position / velocity of star B (equivalent to the aforementioned second spacecraft) at the initial moment is obtained. The...

example 2

[0100] This example provides a method for determining the relative orbit of the lunar large elliptical orbit spacecraft formation based on short-term relative measurements on the planet, including:

[0101] Combining the short-term absolute orbit measurement of the ground station and the short-term relative measurement on the star, the relative orbit of the lunar large elliptical orbit spacecraft formation can be determined with high precision; the short time can be the time for a spacecraft to fly around the moon for one week or several weeks.

[0102] Use the ground station to measure the initial orbital elements of the main star measured in a short time, and obtain the orbital elements of the main star in a period through orbital recursion;

[0103] Using the information measurement method of radio distance measurement and angle measurement camera angle measurement, only relative measurement information is required in a relatively short period of time, and the relative avera...

example 3

[0106] Relative measurement:

[0107] The information measurement method of radio distance measurement and angle measurement camera angle measurement is adopted, the distance measurement accuracy is 2m (1σ), and the angle measurement accuracy is 0.02° (1σ).

[0108] Such as Figure 4 As shown, the measurement coordinate system OcXcYcZc is defined: the coordinate origin Oc is the optical center of the goniometric camera, which can be considered to coincide with the center of mass of the satellite, the Xc axis points to the direction of the optical axis, and the Yc axis and the Zc axis correspond to the horizontal and vertical directions of the goniometric camera imaging . Yc forms a right-handed Cartesian coordinate system with the Zc axis and the Xc axis.

[0109] The relative measurement adopts the extended Kalman filter, and its calculation process is as follows:

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Abstract

The embodiment of the invention discloses a method and device for determining a relative orbit of a spacecraft formation. The method comprises: measuring a first motion parameter of a first spacecraftin a spacecraft formation flying around a target object relative to a reference object; according to the first motion parameter, determining a first orbit number of the first spacecraft flying aroundthe target object; measuring a second motion parameter of a second spacecraft in the spacecraft formation relative to the first spacecraft; according to the first orbit number and the second motion parameter, determining a second orbit number of the second spacecraft flying around the target object; and determining an average relative orbital number of movement of the second spacecraft relative to the first spacecraft by combining the first orbit number and the second orbit number.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method and device for determining relative orbits of spacecraft formations. Background technique [0002] A combination of multiple spacecraft flying in formation in a certain order can be called a spacecraft formation. Each spacecraft in the spacecraft formation maintains a predetermined relative orbit, which is the prerequisite for maintaining the flight queue of the spacecraft formation. Therefore, the determination of the relative orbit of the spacecraft formation directly affects the success or failure of the flight control of the spacecraft formation. For example, a lunar orbiter spacecraft pair is a formation of spacecraft orbiting the Moon. The relative orbit determination of the lunar orbit spacecraft formation adopts ground station tracking measurement. For the lunar large elliptical orbit spacecraft formation, due to the long orbital period, the high speed of th...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 吴宝林曹喜滨孔宪仁耿云海张刚许闯
Owner HARBIN INST OF TECH
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