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Aircraft attitude adjustment device and drop vibration test system

A technology of adjusting device and test system, applied in the field of aircraft, can solve problems such as affecting test efficiency

Active Publication Date: 2019-01-04
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

The precise adjustment of landing attitude directly determines the success of the test on the one hand, and directly affects the efficiency of the test on the other hand
[0003] At present, the development of carrier-based aircraft in China is still in its infancy, and the full-aircraft drop test assessment of carrier-based aircraft in the laboratory is still in the exploratory stage. The scheme proposed in this patent to change the landing attitude of the aircraft based on the adjustment of the lifting point position has not yet seen similar adjustments device application

Method used

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  • Aircraft attitude adjustment device and drop vibration test system
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Embodiment Construction

[0020] In order to make the objectives, technical solutions, and advantages of the implementation of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention, but should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present inv...

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Abstract

The invention discloses an aircraft attitude adjusting device and a drop vibration test system. The adjusting device comprises a bearing frame fixedly connected with the aircraft; a first adjusting member movably disposed on the bearing frame in a first direction; a second adjusting member movably disposed on the bearing frame in a second direction and connected to the first adjusting member; an electromagnetic locking tab movably disposed on the second adjusting member in a second direction; the test system comprises an adjusting device and a force measuring platform. By changing the positionof the lifting point of the aircraft, the pitch angle and the roll angle of the aircraft can be changed equivalently according to the change of the position of the lifting point and the relative center of gravity of the aircraft so as to achieve the adjustment of the attitude of the aircraft.

Description

Technical field [0001] The technical field of aircraft of the present invention specifically relates to an aircraft attitude adjustment device and a drop test system. Background technique [0002] The whole drop test of a carrier-based aircraft is a method to simulate the dynamic load and response of the aircraft body when the carrier-based aircraft is on the ship in the laboratory. In order to comprehensively assess the various landing attitudes of carrier-based aircraft when landing, it is necessary to adjust the landing attitude of the aircraft during the full-plane drop test. The landing attitude mainly involves angles in two directions, namely the pitch angle along the direction of the aircraft fuselage and the roll angle along the direction of the wingspan of the aircraft. During the test, it is necessary to adjust the pitch and roll angles according to the requirements of the test task. After the task requirements are met, the subsequent test preparations can be carried o...

Claims

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Application Information

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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 豆清波秦兴斌
Owner CHINA AIRPLANT STRENGTH RES INST
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