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Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit)

A control device and self-adaptive technology, applied in the direction of heat reduction structure, etc., can solve the problems of complex control scheme and important structure, and achieve the effect of light weight, less equipment and stable operation

Active Publication Date: 2015-05-06
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to solve the existing limitations of directly using the DC-DC high-voltage module to drive the MFC, or the complexity of the control scheme, which greatly increases the importance of the structure, and provides a control device based on the adaptive trailing edge structure of the MFC

Method used

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  • Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit)
  • Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit)
  • Control device of self-adaptive trailing edge structure based on MFC (microfunction circuit)

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specific Embodiment approach 1

[0021] Specific implementation mode one: the following combination figure 1 Describe this embodiment, the control device based on the adaptive trailing edge structure of MFC described in this embodiment, the adaptive trailing edge structure based on MFC is that a substrate 6 is respectively arranged on the trailing edge of the left and right wings, and each substrate 6 are provided with n pairs of double-chip structures, each pair of double-chip structures includes an upper MFC4 and a lower MFC5, n upper MFC4s are pasted on the upper surface of the substrate 6, and n lower MFC5s are correspondingly pasted on the lower surface of the substrate 6;

[0022] The control device based on the MFC adaptive trailing edge structure includes a left wing control device and a right wing control device. DC-DC high voltage module V1, n second DC-DC high voltage modules V2;

[0023] The DC power signal output end of the DC power supply 1 is connected to the DC power signal input end of the c...

specific Embodiment approach 2

[0028] Specific implementation mode two: the following combination figure 2 Describe this embodiment, this embodiment will further explain the first embodiment, the voltage divider circuit 3 includes a voltage divider resistor R1, a voltage divider resistor R2, a voltage divider resistor R3, a voltage divider resistor R4, a bleeder resistor R5, a bleeder resistor R6, Diode D1, diode D2, diode D3, diode D4, diode D5 and diode D6;

[0029] The anode of the diode D5 is connected to the positive terminal of the DC output power of the first DC-DC high voltage module V1, and the negative terminal of the DC output power of the first DC-DC high voltage module V1 is connected to one end of the discharge resistor R5 and then grounded;

[0030] The cathode of the diode D5 is simultaneously connected to the other end of the discharge resistor R5, one end of the voltage dividing resistor R1, the anode of the upper MFC4 and the cathode of the diode D3;

[0031] The other end of the voltag...

specific Embodiment approach 3

[0042] Specific implementation mode three: the following combination image 3 The present embodiment will be described, and the present embodiment will give specific examples.

[0043]The left wing control device controls the output voltage of all first DC-DC high-voltage modules V1 on the left wing 7 to be 0V, and the output voltage of all second DC-DC high-voltage modules V2 to be 2000V. At this time, all upper MFC4 on the left wing 7 Contraction, all the lower MFC5 elongate, and all bimorphs on the trailing edge of the aircraft left wing 7 are structurally bent upwards.

[0044] The right wing control device controls the output voltage of all first DC-DC high-voltage modules V1 on the right wing 8 to be 0V, and the output voltage of all second DC-DC high-voltage modules V2 to be 2000V. At this time, all upper MFC4 on the right wing 8 Contraction, all lower MFC5 elongation, all bimorph structures on the trailing edge of the aircraft's right wing 8 are bent upwards.

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Abstract

The invention discloses a control device of a self-adaptive trailing edge structure based on an MFC (microfunction circuit), and belongs to the field of the morphing control of morphing aircraft. The control device provided by the invention solves the problems in the prior art that the structure importance is greatly enhanced as the limitation exists in that the DC (direct current)-DC high-pressure module is directly utilized to drive the MFC, or a control scheme is complex. The control device provided by the invention comprises a direct-current low-voltage power supply, a controller, high-voltage modules and voltage division circuits; the adaptation trailing edge structure based on the MFC is composed of multiple groups of twin-lamella structures, and each group of twin-lamella structures uses the independent high-pressure modules and the voltage division circuits; and each voltage division circuit can enable the upper and lower MFCs of the structure to be adjusted in a two-way manner in an operation voltage range, the controller can control the output voltage of each high-voltage module so as to control the transformation of the structure, and the direct-current low-voltage power supply is used as an input power source of the high-voltage modules.

Description

technical field [0001] The invention relates to a control device based on an MFC adaptive trailing edge structure, and belongs to the field of deformation control of a variant aircraft. Background technique [0002] Since the invention of the aircraft, how to improve the aerodynamic performance of the aircraft has always been one of the important research contents of aircraft designers. The wings of current fixed-wing aircraft extend outward from the fuselage at a fixed angle and are strong enough to fly without significant movement or twisting, although it has leading and trailing edge flaps to improve flight efficiency. The aerodynamic operating part itself is still a rigid surface, and it is difficult to change the characteristics of the wing according to the flight conditions during flight, and the aerodynamic efficiency of the aircraft wing cannot be optimized. However, bird wings in nature can be subtly adjusted according to the needs of flight at any time, achieving ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/36
Inventor 李承泽尹维龙王长国董中杰姚永涛
Owner HARBIN INST OF TECH