Fluid thrust vector exciter

A technology of thrust vector and exciter, which is applied in the direction of affecting the airflow flowing through the surface of the aircraft, aircraft parts, aircraft control, etc., which can solve the problems of unmanned aerial vehicles such as lightness, complex structure, and few applications, and achieve simple drive form , Reasonable design, light and thin structure

Inactive Publication Date: 2022-01-21
中国空气动力研究与发展中心设备设计与测试技术研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the latest research, synthetic jet circulation control has been studied exploratoryly, but is currently less applied
On the other hand, the traditional thrust vectoring nozzle has a complex structure and high mass, which contradicts the lightness of the UAV

Method used

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  • Fluid thrust vector exciter
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Embodiment Construction

[0022] The following will be combined with Figure 1-Figure 3 The present invention is described in detail, and the technical solutions in the embodiments of the present invention are clearly and completely described.

[0023] like figure 1 As shown, a fluid thrust vector actuator includes a body 2, a bistable diaphragm 3, an excitation sheet 4, a first Tesla check valve 1 and a second Tesla check valve 5,

[0024] The body 2 has an open chamber, and the chamber has a fluid inlet and a fluid outlet;

[0025] The bistable diaphragm 3 is fixed and sealed to the opening of the chamber;

[0026] The excitation piece 4 is a piezoelectric composite fiber diaphragm, which is attached to the bistable diaphragm 3, and under the action of alternating voltage, it drives the bistable diaphragm to realize mode transition and realize the change of the fluid volume in the chamber ;

[0027] The first Tesla one-way valve 1 completes the entry of fluid, and its outlet port is connected to ...

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PUM

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Abstract

The invention relates to the technical field of flow lift enhancement and drag reduction of aircrafts, and particularly discloses a fluid thrust vector exciter which comprises a machine body, a bistable diaphragm, an excitation piece and two Tesla one-way valves, the machine body is provided with a cavity with an opening, and the cavity is provided with a fluid inlet and a fluid outlet; the bistable diaphragm is fixedly sealed at the opening of the cavity; the excitation piece is a piezoelectric composite fiber membrane, is attached to the bistable membrane, and drives the bistable membrane to realize modal transformation under the action of alternating voltage, so that the volume of fluid in the cavity is changed; the two Tesla one-way valves are respectively communicated with the fluid inlet and the fluid outlet; the fluid thrust vector exciter has the advantages of being light, thin and compact in structure, free of mechanical connecting rod moving parts and the like, can be flexibly arranged in the rear edge of the wing, changes local lifting resistance of the wing, forms pitching or rolling torque, forms fluid thrust vector control, can also play a role of the gas compressor and can be used for blowing and sucking gas in a boundary layer.

Description

technical field [0001] The invention relates to the technical field of aircraft flow increase and drag reduction, in particular to a fluid thrust vector exciter. Background technique [0002] Active flow control can control the flow by directly applying appropriate disturbances in the flow field and coupling with the intrinsic modes of the flow. Its advantage is that it appears at the required time and place, and through local energy input, a local or global effective flow change is obtained, thereby significantly improving the flight performance of the aircraft. The blowing / suction flow control technology can effectively intervene and control the boundary layer flow. The mixed laminar flow technology combined with the blowing / suction flow control technology and the modification is currently one of the flow control technologies with the most development prospects and application value. one. [0003] Studies have shown that carrying out suction at the leading edge of the wi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C21/02B64C21/04B64C21/06
CPCB64C21/025B64C21/04B64C21/06Y02T50/10
Inventor 张伟高鑫宇聂旭涛陈万华蔡清青
Owner 中国空气动力研究与发展中心设备设计与测试技术研究所
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