Aircraft attitude adjustment device and drop shock test system

Abstract

The invention discloses an aircraft attitude adjustment device and a drop shock test system. The adjustment device includes: a bearing frame fixedly connected with the aircraft; a first adjusting part movably arranged on the bearing frame along a first direction The second adjustment part is movably arranged on the bearing frame along the second direction and is connected with the first adjustment part; the electromagnetic lock tongue is movably arranged on the second adjustment part along the second direction above; the test system includes the above-mentioned adjustment device and force measuring platform. By changing the position of the lifting point of the aircraft, the invention can equivalently change the pitch angle and roll angle of the aircraft by changing the relative position of the lifting point and the center of gravity of the aircraft to adjust the attitude of the aircraft.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an aircraft attitude adjustment device and a drop shock test system. Background technique [0002] The drop test of the carrier-based aircraft is a method to simulate the dynamic load and response of the carrier-based aircraft when it lands in the laboratory. In order to comprehensively examine the various landing attitudes of the carrier-based aircraft in the laboratory, it is necessary to adjust the landing attitude of the aircraft during the full-aircraft drop test. The landing attitude mainly involves the angles in two directions, that is, 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, and the follow-up test preparation can only be carried out after meeting the task require...

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

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