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Included angle constraining method for full-scale fatigue test

A technology of fatigue test and included angle, which is applied in the direction of aircraft component testing, aircraft parts, ground equipment, etc., can solve the problems of inconvenient installation and replacement, occupation, etc., and achieve the effect of easy replacement, low cost and simple installation

Active Publication Date: 2014-03-12
CHINA AIRPLANT STRENGTH RES INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

In this case, at least 6 points are set for heading and lateral constraints, occupying 6 channels, which is very inconvenient for installation and replacement

Method used

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  • Included angle constraining method for full-scale fatigue test

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Embodiment Construction

[0017] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0018] The included angle constraint method used in the whole aircraft fatigue test of the present invention symmetrically sets four oblique constraints on the strong frame positions of the front fuselage and the rear fuselage of the aircraft.

[0019] Such as figure 1 As shown, the two symmetrical oblique constraints of the front fuselage are set on the front fuselage frame, and the angle relative to the heading is 35°. The two symmetrical oblique constraints of the rear fuselage are set on the rear fuselage strong frame, and the angle relative to the heading is 35°. In addition, the tilt angle of the constraint is not limited to 35°, and can be adjusted according to actual needs, as long as the symmetry is maintained. The included angle of 35° is mainly to solve the extrusion problem of the adhesive tape at the fuselage of equal diameter. At the same tim...

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Abstract

The invention belongs to an aircraft testing constraining technology and particularly relates to an included angle constraining method for a full-scale fatigue test. According to the included angle constraining method for the full-scale fatigue test, four inclined constraints are symmetrically arranged on 1 to 2 strong frame sites of a forebody and a rear fuselage of an aircraft; and the angle of each inclined constraint relative to the heading is 35 degrees. According to the invention, the heading, the lateral displacement and the yaw moment are effectively constrained; an adhesive tape in a load direction is avoided being squeezed; and moreover, the distance from each constraint point and a fixed point is short and in a conventional method, a fuselage needs to be bypassed, but the short-distance setting of the constrain points can avoid influence of the weight of connecting pieces on a constraint load. In addition, the included angle constraining method is simple in installation, is convenient to operate and control, is passage-saving, is low in cost and has high practical application value.

Description

technical field [0001] The invention belongs to aircraft test restraint technology, in particular to an included angle restraint method for fatigue test of the whole aircraft. Background technique [0002] In the fatigue test of full-scale aircraft structure, especially civil aircraft, the fuselage is long and the main body of the fuselage is of equal diameter, and the full-aircraft fatigue test usually has active loads on the landing gear, so it is not suitable to place the heading and lateral constraints on the landing gear , usually set on the fuselage. [0003] When the fuselage is constrained, the constraining adhesive tape needs to be arranged at the strong frame of the nose and tail. For the aircraft structure with the same diameter as the fuselage main body, the commonly used restraint form is relatively long, and its weight has a great influence on the calculation of the restraint force. When setting a heading constraint for the aircraft, two lateral constraints mu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/60
Inventor 刘春艳蔺彦鑫何月洲高利娃潘文涛王大鹏
Owner CHINA AIRPLANT STRENGTH RES INST
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