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Hypersonic aircraft reentry terminal attitude control method and system

An attitude control and hypersonic technology, applied in the field of aerospace

Active Publication Date: 2019-08-23
BEIJING INST OF CONTROL ENG
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  • Claims
  • Application Information

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Problems solved by technology

During the re-entry process, especially at the end of the re-entry stage, the altitude and speed of the aircraft change drastically. In addition to the dense atmospheric environment around, the aerodynamic characteristics, center of mass, and moment of inertia of the aircraft all undergo rapid changes, resulting in extremely fast time-varying characteristics of the hypersonic aircraft. Significantly, the attitude control system design of hypersonic reentry vehicles faces a huge challenge

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  • Hypersonic aircraft reentry terminal attitude control method and system
  • Hypersonic aircraft reentry terminal attitude control method and system
  • Hypersonic aircraft reentry terminal attitude control method and system

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Embodiment

[0135] Hypersonic vehicles perform BTT-180° maneuvers, which are commonly used in rapid reentry or ground attack phases of aircraft. During this period, the angle of attack command decreased from 20° to 10° in 15 seconds, and then increased to 20° in 15 seconds, while the roll angle increased from 0° to 180° in 6 seconds, and the sideslip angle was maintained at 0°. During the entire flight process, the altitude and speed change rapidly, and the dynamic pressure also changes rapidly, which leads to significant time-varying characteristics of the aircraft. The change curves of height, speed and dynamic pressure are as follows: figure 2 It can be seen from the dynamic pressure change curve that the dynamic pressure has changed by more than 10 times in the last 20 seconds of the reentry stage. Rapid changes in dynamic pressure will lead to rapid changes in the control gain of the rudder surface, the specific changes are as follows: image 3 shown.

[0136] In order to verify...

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Abstract

The invention relates to a hypersonic aircraft reentry terminal attitude control method and system. The method comprises the following steps: (1) selecting an attitude tracking error as a controlled output, and establishing a three-channel attitude error characteristic model by combining a control target and aircraft attitude kinetic analysis; (2) introducing dynamic pressure into a parameter self-adaptive update law through time-varying structural characteristic analysis of characteristic model parameters, and establishing a dynamic pressure-based parameter estimation model; and (3) designingan adaptive output feedback control structure and combining with desired system dynamics to determine controller feedback coefficients. The hypersonic aircraft reentry terminal attitude control method and system has the advantages of high adaptability to a large-range fast time-varying environment, high control precision, simple structure of a controller and the like, and is suitable for high-precision stable control of the reentry attitude of the hypersonic aircraft in a high-speed high-maneuvering mode.

Description

technical field [0001] The invention belongs to the field of aerospace and aviation, and relates to a hypersonic aircraft re-entry terminal attitude control method and system adapted to a large-scale fast time-varying environment. Background technique [0002] Hypersonic reentry vehicles have many advantages such as fast flight speed, short reaction time, strong maneuverability, wide flight range, and strong load capacity, so they have high military and civilian value. During the re-entry process, especially at the end of the re-entry stage, the altitude and speed of the aircraft change drastically. In addition to the dense atmospheric environment around, the aerodynamic characteristics, center of mass, and moment of inertia of the aircraft all undergo rapid changes, resulting in extremely fast time-varying characteristics of the hypersonic aircraft. Significantly, the attitude control system design of hypersonic reentry vehicle faces great challenges. Contents of the inve...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05B13/04
CPCG05D1/0808G05B13/042
Inventor 常亚菲吴宏鑫黄煌龚宇莲
Owner BEIJING INST OF CONTROL ENG