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Stability augmentation control method for wingtip hinge combined type flying platform

A flight platform and control method technology, applied in the directions of adaptive control, general control system, control/adjustment system, etc., can solve the problem of stable flight control method in the trim state of a hinged combined flight platform without wingtips, and affect the practical application of related types of aircraft. , unstable flight mode and other problems, to achieve the effect of easy time domain simulation implementation, easy debugging and engineering implementation, and high design efficiency

Active Publication Date: 2021-03-16
BEIHANG UNIV
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  • Summary
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  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing technology shows that the wingtip articulated combined flight platform has different flight characteristics from traditional aircraft, and has an unstable flight mode when flying straight and level, and cannot maintain stability
This feature affects the practical application of related types of aircraft, and there is no control method for the stable flight of the wingtip articulated combined flight platform in trim state

Method used

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  • Stability augmentation control method for wingtip hinge combined type flying platform
  • Stability augmentation control method for wingtip hinge combined type flying platform
  • Stability augmentation control method for wingtip hinge combined type flying platform

Examples

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Embodiment Construction

[0041] Hereinafter, a certain wingtip articulated combined flying platform is taken as an example to illustrate the stability enhancement control method for the wingtip articulated combined flying platform according to the present invention.

[0042] Such as figure 1 The wingtip articulated combined flying platform shown is an example of the combination of two sub-aircraft, and each sub-aircraft is regarded as a rigid body. Each sub-aircraft structure is as follows figure 2 shown. The sub-aircraft structure includes 8 parts: fuselage 1, right wing 2, right wing aileron 3, full-motion vertical tail 4 (can be used as rudder), full-motion horizontal tail 5 (can be used as elevator), left wing 6, left Wing aileron 7, middle wing 8. Two airframes are connected by a one-way hinge, which can rotate freely along the chord direction.

[0043] According to an embodiment of the present invention, the method for stabilizing the wingtip articulated combined flight platform includes: ...

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Abstract

The invention provides a stability augmentation control method for a wingtip hinged combined type flying platform. The wingtip hinged combined type flying platform cannot stably fly under the uncontrolled condition. After a flight mechanical model is established, an independent PID control loop is established for each sub-aircraft, control parameters are adjusted to achieve stable control over thewhole flight platform, and control loops between the sub-aircrafts are not coupled. Simulation analysis shows that the control strategy is practical and effective.

Description

technical field [0001] The invention provides a stability-increasing control method for a wingtip articulated combined flight platform, which belongs to the field of flight mechanics simulation and control strategy design. Background technique [0002] Endurance performance is the core component of flight performance, and it directly determines factors such as the range of activities, endurance flight capability and economy of the aircraft. Improving range and flight time has always been the core and purpose of aircraft endurance performance research. It is an effective way to improve the endurance performance of aircraft to form a combined flight platform by hinged compound flight of multiple aircraft wingtips. As the straight layout conjoined aircraft in CN102658866A, the wingtip docking parallel flying wing unmanned aerial vehicle system etc. in CN103963972A. The uniqueness of this aircraft concept is that it does not require other auxiliary models and supporting facili...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 谢长川安朝孟杨刘晨宇
Owner BEIHANG UNIV
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