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Spacecraft relative orbit finite time anti-saturation control method with respect to non-cooperative target

A technology for non-cooperative targets and target spacecraft, which is applied in the field of anti-saturation control for limited time relative to the orbit of spacecraft, which can solve problems such as controller saturation, system chattering, and troublesome solution process, etc., and achieve simple design and flexible response Effect

Active Publication Date: 2016-01-13
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0065] The purpose of the present invention is to solve the complex design of the controller in the existing control scheme, the solution process is cumbersome, the relative orbit transfer process of the spacecraft under the pulse control has weak adaptability to unknown factors, and the sliding mode control is adopted, the controller will switch frequently, Cause system chattering, and in the existing method, the controller in the actual project is not considered to be saturated, cannot converge to the expected value in a limited time, and has certain limitations in the actual engineering application, and proposes a A finite-time anti-saturation control method for relative orbits of spacecraft relative to non-cooperative targets

Method used

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  • Spacecraft relative orbit finite time anti-saturation control method with respect to non-cooperative target
  • Spacecraft relative orbit finite time anti-saturation control method with respect to non-cooperative target
  • Spacecraft relative orbit finite time anti-saturation control method with respect to non-cooperative target

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specific Embodiment approach 1

[0085] Specific implementation mode one: combine figure 1 Describe this embodiment, a spacecraft relative orbit finite time anti-saturation control method relative to a non-cooperative target, characterized in that a spacecraft relative orbit finite time anti-saturation control method relative to a non-cooperative target is specifically carried out in accordance with the following steps of:

[0086] Step 1, establishing a relative orbital motion dynamics model;

[0087] Step 2, decoupling the C-W equation of the relative orbital motion dynamics model to obtain a decoupled double integral system;

[0088] Step 3: Design a finite-time saturation controller according to the decoupled double-integral system.

specific Embodiment approach 2

[0089] Specific embodiment two: the difference between this embodiment and specific embodiment one is: the relative orbital motion dynamics model is established in the described step one; The specific process is:

[0090] Note that the target spacecraft is o, the tracking spacecraft is c, the relative orbital motion coordinate system is the orbital coordinate system o-ijk of the target spacecraft o, and i, j, k are the three coordinate axes of the target spacecraft; the orbital coordinate system o- ijk and the earth-centered inertial coordinate system O I -X I Y I Z I relationship such as figure 2 shown;

[0091] In the absence of perturbation, the orbit of the target spacecraft is a circular orbit, that is, e=0, and the relative distance between the tracking spacecraft and the target spacecraft is relatively close, generally tens of kilometers. Taking an approximation for linearization, the spaceflight can be obtained The constant coefficient linear differential equatio...

specific Embodiment approach 3

[0094]Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: the relative orbital motion dynamics model C-W equation is decoupled in said step 2, and the double integral system after decoupling is obtained; The specific process is:

[0095] The target spacecraft is in the geostationary orbit, and the average angular velocity of the target spacecraft is:

[0096] n = 2 π 24 × 60 × 60 ≈ 7.2722 × 10 - 5 r a d / s - - - ( 3 - 1 )

[0097] For the problem of orbit transfer where two spacecraft are relatively close to each o...

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Abstract

The invention relates to a spacecraft relative orbit finite time anti-saturation control method with respect to a non-cooperative target, and is to solve the problems that in an existing control scheme, the design of a controller is complex, the solving process is troublesome, system buffets due to frequent switching of the controller since sliding-mode control is adopted for the weak strain capacity for unknown factors of the spacecraft relative orbit transfer process under pulse control, and since an existing method fails to consider saturation of the controller in the practical engineering, expected value cannot be converged in the finite time and a certain limitation exists in the practical engineering application. The method comprises the following specific steps: establishing a relative orbit motion dynamics model; carrying out decoupling on a relative orbit motion dynamics model C-W equation to obtain a decoupled double-integral system; and designing a finite time saturation controller according to the decoupled double-integral system. The method is applied to the spaceflight field.

Description

technical field [0001] The invention relates to a limited-time anti-saturation control method for a spacecraft relative to a non-cooperative target. Background technique [0002] With the rapid development of my country's politics, economy, science and technology, etc., my country's comprehensive national strength has been continuously enhanced, and the aerospace industry has also made progress one after another. Since 2000, my country's aerospace industry has entered an important stage of rapid development, from the successful launch of the "Shenzhou" spacecraft, which marked my country's manned spaceflight capability after the United States and the former Soviet Union, to the launch of the "Tiangong" one. The successful docking shows that my country's aerospace industry has been at the forefront of the world. The triumph of "Shenzhou V" symbolizes that my country has mastered the technology of manned spaceflight. From "Chang'e" No. 1 to "Tiangong No. 1", it shows that our...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05D1/10
Inventor 龚有敏孙延超李传江高寒马广富凌惠祥
Owner HARBIN INST OF TECH
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