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A Method for Determining the Initial Relative State of Satellites with a Given Boundary in a Circular Reference Orbit

A technology of initial relative and determination methods, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as low design efficiency

Inactive Publication Date: 2017-03-29
TSINGHUA UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] At present, the empirical trial method is usually used, that is, to constantly change a certain state parameter in the initial relative state of the satellite, and through repeated trials and simulation verification, the initial relative state of the satellite can be determined. It can be seen that this design method has the problem of low design efficiency

Method used

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  • A Method for Determining the Initial Relative State of Satellites with a Given Boundary in a Circular Reference Orbit
  • A Method for Determining the Initial Relative State of Satellites with a Given Boundary in a Circular Reference Orbit
  • A Method for Determining the Initial Relative State of Satellites with a Given Boundary in a Circular Reference Orbit

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Embodiment 1

[0085] The present invention provides a method for determining the initial relative state of a satellite with a given boundary under a circular reference orbit, which is specifically used for determining the initial relative state of a given boundary under the condition of periodic relative motion, wherein the circular reference orbit refers to the orbit where the reference satellite is located an orbit with zero eccentricity;

[0086] Such as figure 1 shown, including the following steps:

[0087] S1, establish the first type of optimization model for determining the initial relative state of the given boundary under the condition of periodic relative motion, the objective function of the first type of optimization model is:

[0088]

[0089] The constraints of this first type of optimization model are:

[0090]

[0091] Among them, J is the objective function;

[0092] — the upper bound of the desired interstellar distance;

[0093] — the lower bound of the des...

Embodiment 2

[0150] The invention provides a method for determining the initial relative state of a satellite with a given boundary under a circular reference orbit, which is specifically used for determining the initial relative state of a given boundary under the condition of relative motion around the orbit, wherein the circular reference orbit refers to the orbit where the reference satellite is located. an orbit with zero eccentricity;

[0151] Such as figure 2 shown, including the following steps:

[0152] S10, establishing a second type of optimization model for determining the initial relative state of a given boundary under the condition of relative motion around the fly, the objective function of the second type of optimization model is:

[0153]

[0154] The constraints of this second type of optimization model are:

[0155]

[0156] Among them, J is the objective function;

[0157] — the upper bound of the desired interstellar distance;

[0158] — the lower bound...

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Abstract

The invention provides a determining method for the satellite initial relative state of a set boundary under a round reference orbit. According to the determining method, optimization models which are suitable for periodic relative motion and flying-around relative motion respectively are set, then a certain optimization algorithm is adopted for solving the established optimization models to obtain the initial relative state numerical solution of the set boundary, and the effectiveness and feasibility of the determining method for the satellite initial relative state are verified through simulation; in this way, the satellite initial relative state meeting the set boundary can be rapidly and accurately determined, and meanwhile a theoretical basis is laid for task designing and analyzing of a satellite formation or a cluster with the set boundary.

Description

technical field [0001] The invention belongs to the technical field of spacecraft orbital dynamics, and in particular relates to a method for determining the initial relative state of a satellite with a given boundary under a circular reference orbit. Background technique [0002] In space science missions related to satellite formation or cluster flight, such as satellite formation gravity field measurement, space-based synthetic aperture radar, and asteroid belt detection, more than two satellites often need to participate and cooperate to complete the task. In order to ensure that each satellite in the mission can sense the existence of other members in real time and maintain information connectivity, it is generally required that the relative distance between satellites be naturally kept within a certain range. This leads to the concept of bounded relative motion, that is, the distance between satellites has definite upper and lower bounds. [0003] According to the res...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50G06N3/12
Inventor 张育林王兆魁党朝辉张学阳安梅岩蒋超刘红卫侯振东张斌斌程子龙
Owner TSINGHUA UNIV
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