Test device and method for combined loading of front raising strut of airplane

Abstract

The invention provides a test device and method for combined loading of an airplane front rising strut. The test device comprises a driving chain and a load chain. The driving chain comprises a torsion driving chain and a pulling force driving chain, the torsion driving chain provides a driving torque +M for turning of the front rising strut of the airplane, and the pulling force driving chain provides a pulling force +F for the front rising strut of the airplane; the load chain comprises a torsion load chain and a tension load chain, and the torsion load chain provides a load torque -M balanced with the driving torque +M; and the tension load chain provides a load force -F which is balanced with the pulling force +F. Compared with the prior art, two composite loading items can be independently carried out, a corresponding mechanical structure can be disassembled, assembled and replaced, and implementation by steps is facilitated; and the device is suitable for a ground performance test or a service life test of composite loading of the front rising strut in development, production and maintenance units of the front rising strut of an airplane, and has accuracy, reliability and advancement.

Description

technical field [0001] The invention relates to the technical field of aircraft landing gear testing, in particular to a testing device and method used for composite loading of aircraft nose pillars. Background technique [0002] like figure 1 As shown in the figure, in the ground test of a certain type of aircraft, the front pillars are fixed on the test bench at points O1 and O2. The test task requires the test device to apply drag at the two interfaces C and D as shown in the figure. The resultant force of dynamic turning maneuvering and the resultant force of diverted turning maneuvering are required, and the test device is required to provide a load moment that is balanced with the turning driving moment. It is required that the two working conditions of drag turning and pinning turning are not carried out at the same time. [0003] figure 1 It is the force analysis of the two working conditions of drag-turning control and pinning-turning control. It consists of four...

AI Technical Summary

Problems solved by technology

[0009] 1. It is technically difficult to coordinate and unify the driving load of the test device and the load moment of the tested front pillar. figure 1 As shown, the test of the front pillar of the aircraft requires that the normal tension F be applied to the two interfaces C and D respectively 1X , F 2X and tangential torque F 1Y , F 2Y , and the test device is required to provide the load moments -M1, -M2 balanced with the turning driving moments +M1, +M2 at the same time, which inevitably determines the normal tension F 1X , F 2X and tangential torque F 1Y , F 2Y It must be generated independently of each other and act on the C and D interfaces, and it must also determine the balance of the turning drive torque +M1 and +M2. The load moments -M1 and -M2 must be independent of each other and do not interfere with each other, acting together as a pillar in front of the subject In fact, so many vectors act on the same device in combination, it is necessary to ensure that the loading value is accurate and the direction is accurate. Such a mechanical loading mechanism is difficult to realize.

[0010] 2. The synchronous application of the two pulling forces and the turning steering torque is technically difficult

[0012] 3. Poor feasibility of moving and loading complex mechanical structures in a small space

[0013] The loading functions listed in item 1 and 2 above are required to be coordinated and unified on the same front-lifting pillar test piece. Such a mechanical mechanism has many components, and multi-parameters are prone to mutual interference. In addition, the interfaces of the front-lifting pillar test piece are arranged compactly. , Irregular structure, such a test device has many levels of combination with the front pillar, the movement relationship is complex, and it is prone to interference, improper arrangement and other disadvantages. It is technically difficult to arrange the above elements together in a reasonable and proper manner.

[0014] At present, the composite loading technology has not yet been blank, and this technology is the key technology for the ground test of a new type of aircraft front prop development. Therefore, technological innovation and mastering the composite loading test technology of the aircraft front prop are of great significance to the development of new aircraft

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