Fast aircraft attitude maneuvering method based on fact that angular acceleration derivatives are in sine curve

A technology of attitude maneuvering and angular acceleration, which is applied in attitude control and other directions, and can solve problems such as unfavorable stability

Active Publication Date: 2014-09-24
BEIJING INST OF CONTROL ENG
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Problems solved by technology

Since the planning method only considers the continuation of the angular acceleration, the derivative of the angular acceleration will jump at the beginning

Method used

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  • Fast aircraft attitude maneuvering method based on fact that angular acceleration derivatives are in sine curve
  • Fast aircraft attitude maneuvering method based on fact that angular acceleration derivatives are in sine curve
  • Fast aircraft attitude maneuvering method based on fact that angular acceleration derivatives are in sine curve

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Embodiment

[0047] Embodiment: Take a typical flexible aircraft rolling axis maneuvering process of 25° as an example, assuming that the aircraft's moment of inertia is 3000kg.m 2 , the fundamental frequency of the flexible sailboard is 0.8Hz, and the control period is 0.125s. Assume that the maximum torque that the aircraft actuator can provide is 55Nm, and the maximum angular momentum envelope is 210Nms. First, according to the maximum output torque and the angular momentum envelope, the maximum angular acceleration of the aircraft maneuvering is determined as a m =1.0° / s, the maximum maneuvering angular velocity is The critical rotor time point is then calculated to obtain t m1 =7.071s,t m2 =7.071s,t m3 =14.142s, thus the maneuvering trajectory curve obtained by this method is obtained, such as figure 2 shown. image 3 , Figure 4 Respectively, the attitude angle error and angular velocity error curves of the aircraft when this method is used to control. Statistics show that ...

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Abstract

The invention discloses a fast aircraft attitude maneuvering method based on the fact that angular acceleration derivatives are in a sine curve. The method comprises the steps that an attitude maneuvering path undergoing the three processes of acceleration, constant speed and deceleration is designed according to the moment and angular momentum providing capacity of an actuating mechanism of a control system, in the processes of acceleration and deceleration, it is guaranteed that the derivatives of the angular acceleration are in the standard sine curve, it is guaranteed that moment output in the entire maneuvering process is continuous and first-order derivatives are continuous, so that the moment output is stably changed in the entire maneuvering process, and the trigger effect on a flexural mode in the attitude maneuvering process is small. After aircraft attitude maneuvering is in place, due to the fact that the vibration amplitude value of the flexural mode is small, the attitude of an aircraft can be stable rapidly, and therefore fast maneuvering and fast stable controlling are achieved. The fast aircraft attitude maneuvering method is particularly suitable for aircrafts which are serious in flexural mode coupling for conducting fast maneuvering control, and fast and stable control demands can be met.

Description

technical field [0001] The invention relates to a fast maneuvering control method for a flexible spacecraft, in particular to a fast maneuvering method for an aircraft attitude based on a sinusoidal angular acceleration derivative, which belongs to the field of spacecraft attitude control. Background technique [0002] Modern spacecraft usually have flexible attachments with light structures such as large solar panels. During the flight of flexible spacecraft, it is often necessary to quickly perform large-angle attitude maneuvers to meet mission requirements. Theoretical analysis shows that due to the strong coupling between the dynamics of the central rigid body of the spacecraft and the vibration of the flexible attachment, the nonlinear dynamic characteristics are more significant when its attitude maneuvers to a large angle, which often leads to continuous strong vibration of the flexible attachment, and then Seriously affect the attitude movement, and even directly thr...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 田科丰宗红姚宁雷拥军王淑一何海锋朱琦吕高见傅秀涛綦艳霞潘立鑫李晶心
Owner BEIJING INST OF CONTROL ENG
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