Parachute opening and separating control algorithm for brake parachute of manned spacecraft reentry capsule

A manned spacecraft and separate control technology, applied in the aviation field, can solve the problems of hindering the opening of the main parachute, regardless of the attitude and oscillation amplitude of the return capsule, and achieve the effect of reducing the oscillation amplitude

Pending Publication Date: 2021-11-26
南通智能感知研究院
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The object of the present invention is to provide a kind of drogue parachute parachute opening and separation control algorithm for manned spacecraft return cabin in order to overcome

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  • Parachute opening and separating control algorithm for brake parachute of manned spacecraft reentry capsule
  • Parachute opening and separating control algorithm for brake parachute of manned spacecraft reentry capsule
  • Parachute opening and separating control algorithm for brake parachute of manned spacecraft reentry capsule

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Embodiment Construction

[0031] Embodiments of the present invention will be described in detail below in conjunction with examples, but those skilled in the art will understand that the following examples are only for illustrating the present invention, and should not be considered as limiting the scope of the present invention. Those who do not indicate the specific conditions in the examples are carried out according to the conventional conditions or the conditions suggested by the manufacturer.

[0032] A kind of drogue parachute parachute opening and separation control algorithm for manned spaceship return capsule of the present invention is realized through the following steps:

[0033] Step 1: Use the inertial measurement unit inside the return cabin of the manned spacecraft to provide the current pitch angular velocity q and yaw angular velocity r, and calculate the attitude angle change rate RSS of the return capsule according to the following formula:

[0034] ,Such as figure 1 The workin...

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Abstract

The invention belongs to the technical field of aviation, and particularly relates to a brake parachute opening and separation control algorithm for a manned spacecraft reentry capsule, which comprises the following steps of: providing a current pitch angle speed q and a current yaw angle speed r by using an inertial measurement unit in the manned spacecraft reentry capsule to calculate an attitude angle change rate RSS of the reentry capsule; controlling the brake parachute to be opened by comparing the return capsule attitude angle change rate RSS with the RSS parachute opening threshold value, judging the brake parachute separation condition by comparing the return capsule attitude angle change rate RSS with the RSS separation threshold value or comparing the OF value with the OF separation threshold value, or sending a brake parachute separation instruction when the pitch angle speed q is located at the falling edge and within the specific interval range. According to the algorithm, the oscillation amplitude of the return capsule in the period from brake parachute opening to main parachute opening is remarkably reduced, and the situation that the large bottom faces forwards and is not beneficial to main parachute opening is reduced.

Description

technical field [0001] The invention belongs to the field of aviation technology, and in particular relates to a control algorithm for the opening and separation of a deceleration parachute used in the return cabin of a manned spacecraft. Background technique [0002] When the return capsule descends below 20km, the flight Mach number is less than 1, and the return capsule flies at subsonic speed. At this time, the attitude is unstable, and it is prone to relatively large swings, plane rotations, and rollovers. decrease, this phenomenon will become more and more serious. Relying solely on the control system to maintain the attitude of the return capsule will consume a lot of energy, so a drogue parachute is required. The deceleration parachute, also known as the stable deceleration parachute, has the characteristics of high parachute opening dynamic pressure and large load. It creates favorable conditions for the main parachute to open, plays a key role in the aerodynamic d...

Claims

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Application Information

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IPC IPC(8): B64G1/62G05D1/08
CPCB64G1/62G05D1/0816
Inventor 肖赟辰韩慧杰蒋曼钱渠徐笑张梦周俊波孙德新其他发明人请求不公开姓名
Owner 南通智能感知研究院
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