Load follow-up loading system for plane flap reliability test

Abstract

The invention relates to a load follow-up loading system for plane flap reliability tests. The system comprises a bearing wall. The system is characterized by further comprising a support component, a load loading adjusting unit and a load detection and adjusting unit, wherein a flap is mounted on a wing; the root of the wing is mounted on the bearing wall; the support component comprises two vertical columns and a transverse beam for supporting the load loading adjusting unit and the load detection and adjusting unit; the load loading unit comprises a moment motor and a steel rope; the moment motor is arranged on the support component and is used for exerting an action force on the flap; the steel rope is connected with the moment motor; the load detection and adjusting unit comprises an angle sensor, a sliding track component and a pulley component. A plurality of loading points are arranged on the surface of the flap, one loading point corresponds to one set of loading system, the size, the direction and an equivalent action point of real-time flap surface aerodynamic force can be simulated.

Description

technical field [0001] The invention relates to the field of aircraft reliability tests, in particular to a load-following loading system for aircraft flap reliability tests. Background technique [0002] The flap mechanism is an important lift-increasing device of an aircraft. It is mainly used to delay the airflow separation on the wing, increase the critical angle of attack of the aircraft, and increase the lift coefficient of the wing. The reliability of the flap mechanism is directly related to the flight safety of the aircraft. In order to expose the potential failure mode of the flap mechanism and improve its reliability level, a reliability test must be carried out on the flap mechanism; Load is the main factor affecting the reliability of its motion function. In addition, the flap mechanism is bulky, heavy, and has complex structures and functional principles, so the follow-up loading of flap aerodynamic loads has become the core content of its reliability test. ...

AI Technical Summary

Problems solved by technology

Its disadvantages are: (a) the range of follow-up loading that can be realized is small, and it is not suitable for flaps, hatches and other motion mechanisms that need to be retracted and retracted in a large range; Dynamic loading system, it is difficult to adapt to the situation of more loading points

[0004] China Patent No. 201210528949.X, Patent No. 201120541107.9, Patent No. 201120000929.6, etc. have proposed a mobile actuator scheme, which has similar functional principles and can better adapt to the situation of loading in a large range, but its disadvantages are: (a ) cannot separately control the direction of the load on each loading point; (b) to meet the requirements of large-scale follow-up loading, a hydraulic actuator with a relatively long length is required, which has poor applicability

[0005] China Patent No. 201110430890.6 designed a follow-up loading system based on servo motors and steel cables, but this solution can only control the size and direction of the load, not the point of action of the load, and is only suitable for single-point simple load loading

The strength and rigidity of the cylindrical guide rod in this scheme are low, and the guide rod and the slider have sliding friction and the contact surface is too short, so it is difficult to withstand a large overturning moment, and it is easy to cause a stuck fault

In addition, the guide rod of this scheme is placed vertically, and the length of the guide rod required in the case of large-scale follow-up loading is relatively long

Therefore, this scheme is difficult to adapt to large-scale follow-up loading situations such as aircraft flaps that are subject to complex and large loads

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