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A solar sail spacecraft three-axis attitude control and its implementation method

A control method and three-axis attitude technology, applied in attitude control, aerospace vehicles, aircraft, etc., can solve problems such as the difficulty of calculating rotation angles, achieve small steady-state errors, suppress huge light pressure torque interference, and reduce quality Effect

Active Publication Date: 2019-01-18
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the form of the actuator designed based on the principle of sail surface rotation is difficult to calculate the rotation angle, so it is necessary to design a reasonable control law to solve the rotation angle of the small sail
But there is no relevant description in the prior art

Method used

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  • A solar sail spacecraft three-axis attitude control and its implementation method
  • A solar sail spacecraft three-axis attitude control and its implementation method
  • A solar sail spacecraft three-axis attitude control and its implementation method

Examples

Experimental program
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Embodiment

[0103] Solar sail spacecraft parameters are J=diag([6000 3000 3000]), A=1200m 2 , m=2kg, m s =151kg,m t =157kg, A v = 2m 2 . Slider sliding distance limit d max = 20m, the length limit of the telescopic pole is l max =20m, l 0 = 10m. Solar pressure constant P s =4.653×10 -6 N / m 2 .

[0104] Initial pose quaternion Q 0 =[0.3827 0 0 0.9239] T , the desired pose quaternion Q d =[0.3696-0.2391-0.0990 0.8924]. Light pressure disturbance torque τ d =[0.0669 1 1] T mNm.

[0105] The controller parameters are: λ=0.01, k 0 =0.3, b=0.08, ε=0.001, δ J Adaptive selection according to the change of rotation variable.

[0106] combine image 3 , the time to maneuver the solar sail attitude angle to the target position is less than 1.2h, the maneuvering time is faster, and the error tends to 0, and the steady-state error is extremely small; the proposed controller can achieve The three-axis attitude control of the solar sail is effectively realized, and its anti-inter...

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Abstract

The invention discloses a solar sail spacecraft triaxial attitude control and realization method. The method comprises the following steps: step 1, establishing a solar sail attitude kinetic model and an attitude dynamic model; step 2, based on the first step, on the basis of a slide mode control theory, constructing a solar sail attitude controller; and step 3, constructing a control low, enabling an execution mechanism to output control moment, realizing tracking of an output quantity of the solar sail attitude controller, and applying the control moment to the solar sail attitude models so as to complete attitude control. The principle of the control law designed in the method is simple, solar sail attitude can be rapidly moved to an expected position, and stable-state errors are quite small.

Description

technical field [0001] The invention relates to the field of attitude control of spacecraft, in particular to a three-axis attitude control of a solar sail spacecraft and a method for realizing it. Background technique [0002] Solar sail spacecraft gain orbital propulsion by bouncing sunlight off their huge sails. Changing the attitude of the solar sail and adjusting the angle of sunlight reflection can adjust the amplitude and direction of the propulsion force, and then change the flight trajectory of the spacecraft. Therefore, the flight mission of the solar sail depends on its attitude control. Complex orbital missions correspond to various attitude maneuvers, and traditional spin stabilization cannot meet the requirements of changing attitudes. In order to serve solar sail orbit transfer and deep space flight missions, it is necessary to study an efficient and accurate three-axis attitude control system. [0003] Compared with traditional spacecraft, solar sails are ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 吴利平郭毓姚伟王璐钟晨星吴益飞郭健陈庆伟
Owner NANJING UNIV OF SCI & TECH