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Total attack angle control method based on normal overload

A technology of normal overload and angle of attack, which is applied to space navigation equipment, space navigation aircraft, and space navigation aircraft guidance devices, etc., can solve problems such as angle of attack measurement errors, jeopardizing the smooth deployment of parachutes, and interfering torque uncertainty. , to improve the success rate, avoid the influence of the angle of attack measurement error on the control accuracy, improve the probability of meeting constraints and the success rate of parachute opening

Active Publication Date: 2021-01-29
BEIJING INST OF CONTROL ENG
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

Moreover, due to large uncertainties in the density of the Martian atmosphere and the aerodynamic coefficient, there is also uncertainty in the disturbance torque. The constraint condition of the angle cannot be satisfied, which seriously endangers the smooth deployment of the parachute

Method used

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  • Total attack angle control method based on normal overload
  • Total attack angle control method based on normal overload
  • Total attack angle control method based on normal overload

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Experimental program
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Embodiment Construction

[0036] The present invention will be further elaborated below in conjunction with embodiment.

[0037] The trim wing is deployed after the Mach number is less than a certain one. When the trim wing is not successfully deployed, the angle of attack needs to be controlled based on the normal overload to control the angle of attack close to 0° to meet the requirements of the parachute opening condition. A total angle of attack control method based on normal overload, such as figure 1 As shown, the specific steps are as follows:

[0038] (1) Analyze the longitudinal short-period motion and simplify the dynamic equation in the pitch plane. Longitudinal short-period motion describes pitch channel attitude motion and attack angle motion. Here it is assumed that the detector's roll angle and side slip angle are controlled at the target attitude of zero degrees, and the inertia product of the detector is zero, the influence of the earth's rotation angular velocity is ignored, and the...

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Abstract

The invention relates to a total attack angle control method based on normal overload. The method comprises the steps of carrying out the control through the following modes when a trim wing is not successfully unfolded: analyzing the longitudinal short-period movement, and simplifying a kinetic equation in a pitching plane; establishing an expected normal overload, i.e., a normal overload instruction is zero; deducing a relation between attack angle deviation and normal overload according to a simplified motion equation in the pitching plane; and based on the deviation between the actually measured normal overload and the expected normal overload, solving the control moment by combining the deduced relation between the normal overload and the attack angle deviation, and carrying out control according to the control moment.

Description

technical field [0001] The invention belongs to the field of guidance and control of the entry process of a small lift body into a thin atmosphere in a deep space exploration planetary surface landing project, and relates to a method for controlling a total angle of attack based on normal overload. Background technique [0002] my country's first Mars exploration mission will implement Mars orbiting, landing and patrol detection through a single launch. The key to the mission is to successfully implement the entry, descent and landing process to achieve a soft landing on the surface of Mars. To achieve a safe and soft landing, the successful opening of the parachute is the key. Therefore, the process of atmospheric entry must be fully designed to meet the constraints of various parachute opening conditions. In addition to strict restrictions on the dynamic pressure, Mach number, and height at the parachute opening point, the conditions for parachute deployment also have clea...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/22B64G1/24
CPCB64G1/22B64G1/24
Inventor 郭敏文黄翔宇李茂登黄盘兴魏春岭徐超胡锦昌王晓磊
Owner BEIJING INST OF CONTROL ENG
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