CN-122009520-A - Cross-linking measurement device for wing flaps in aircraft wing flap fault test

Abstract

The application relates to a wing flap crosslinking measurement device for an airplane wing flap fault test, which comprises a support cylinder, a load sensor, a displacement sensor, a load measurement end mounting joint, an energy absorption assembly, a punch rod and a displacement measurement end mounting joint, wherein one end of the support cylinder is a load measurement end, the other end of the support cylinder is a displacement measurement end, the load measurement end is externally connected with the load sensor, the load sensor is externally connected with the load measurement end mounting joint, the energy absorption assembly comprises an elastic piece and a punched end, wherein the elastic piece is arranged in the support cylinder, one end of the elastic piece is connected with the load measurement end, the other end of the elastic piece is connected with the punched end, the punched end can slide in the support cylinder, the punch rod penetrates through the displacement measurement end and the punched end and is provided with two punches, the two punches are arranged in the support cylinder and distributed on two sides of the punched end, the displacement sensor is sleeved on the periphery of the punch rod and used for detecting the displacement of the punch rod, and the displacement measurement end mounting joint is connected with one end of the punch rod, which is arranged outside the support cylinder.

Inventors

• CHEN XIANMIN
• LI SANYUAN
• Zhuo Die
• LI CHEN
• ZANG WEIFENG

Assignees

• 中国飞机强度研究所

Dates

Publication Date

20260512

Application Date

20260326

Claims (5)

1. 1. The device for measuring the cross-linking of the wing flaps in the airplane wing flap fault test is characterized by comprising a supporting cylinder (1), a load sensor (2), a displacement sensor (3), a load measuring end mounting joint (4), an energy absorbing assembly (6), a plunger (7) and a displacement measuring end mounting joint (8); One end of the supporting cylinder (1) is a load measuring end, the other end of the supporting cylinder is a displacement measuring end, the load measuring end is externally connected with the load sensor (2), and the displacement measuring end is externally connected with the displacement sensor (3); The load sensor (2) is connected with a load measuring end mounting joint (4); The energy absorption assembly (6) comprises an elastic piece (61) and a punched end (62), wherein the elastic piece (61) is arranged in the supporting cylinder (1), one end of the elastic piece is connected in the load measuring end, the other end of the elastic piece is connected with the punched end (62), and the punched end (62) can slide in the supporting cylinder (1); The punch rod (7) penetrates through the displacement measuring end and the punched end (62), two punches (71) are arranged on the punch rod, and the two punches (71) are positioned in the supporting cylinder (1) and distributed on two sides of the punched end (62); The displacement sensor (3) is sleeved on the periphery of the punch rod (7) and is used for detecting the displacement of the punch rod (7); the displacement measuring end mounting joint (8) is connected to one end of the punch rod (7) positioned outside the supporting cylinder (1).
2. 2. The aircraft flap failure test flap cross-linking measurement device according to claim 1, characterized in that the load sensor (2) is a high-frequency load sensor; the displacement sensor (3) adopts a high-frequency magnetic induction displacement sensor.
3. 3. The device for measuring the cross-linking of the wing flaps in the fault test of the aircraft according to claim 2, wherein a conversion joint (5) is arranged between the load sensor (2) and the load measuring end mounting joint (4) for connection.
4. 4. An aircraft flap failure test flap cross-linking measurement apparatus according to claim 3, characterized in that the elastic member (61) is a bellows.
5. 5. The device for measuring the cross-linking of the wing flap of the airplane wing flap fault test according to claim 4, wherein a nut (9) is connected to the displacement measuring end mounting joint (8) and is connected to the plunger (7) through the nut (9).

Description

Cross-linking measurement device for wing flaps in aircraft wing flap fault test Technical Field The application belongs to the technical field of airplane flap fault test design, and particularly relates to a flap cross-linking measurement device for an airplane flap fault test. Background Flap cross-linking device is located between the inner flap and the outer flap of the aircraft, the two ends of the two are connected through a hinge joint is connected with the inner flap and the outer flap. When the flap machine breaks, breaks away and other faults occur, the relative movement of the inner flap and the outer flap is pulled to a certain extent, the flap crosslinking device can be triggered to be compressed or stretched, and a new force transmission path is established between the inner flap and the outer flap so as to protect the wing flap structure. In the development and evidence obtaining process of the airplane, the cross-linking load after the failure of the front wing needs to be tested through a test. The flap crosslinking device has a complex structure, free idle stroke and axial bidirectional movement, the energy absorbing element is locked after plastic deformation through compression or stretching, the loading and axial deformation process is complex, the device for measuring the load and axial deformation displacement is not provided, the space between the inner flap and the outer flap is narrow, and the crosslinking load and displacement response measurement is difficult to carry out in a flap fault test. Currently, a flap crosslinking measuring device for a flap fault test is designed, a load-speed-energy relation is calibrated and fitted through an impact test, a laser displacement sensor and a reflecting plate are used for measuring displacement, and the following defects exist in the technical scheme: the flap crosslinking measuring device does not refer to the structure and the dynamic performance of the original flap crosslinking device, so that the deviation between the measured result and the actual situation is larger in the test measuring process; the flap crosslinking measuring device can only compress and absorb energy in one direction, and does not meet the requirements of pulling, compressing, absorbing energy and locking of the flap crosslinking device in axial bidirectional movement; The flap crosslinking measuring device cannot directly measure the load, the load and the impact speed are fitted by carrying out compression size-load-energy through a plurality of ground impact tests, the load process and the peak value data cannot be given, the error of the test measuring result is large, and the cost is high; The flap crosslinking measuring device is additionally provided with the laser displacement sensor and the reflecting plate, has large structure and high quality, is inconvenient to install, is easy to interfere with inner and outer flaps in the movement process, influences movement and energy absorption, and introduces extra errors due to structural vibration. The present application has been made in view of the above-described technical drawbacks. Disclosure of Invention The application aims to provide a flap cross-linking measurement device for an aircraft flap fault test, which overcomes or alleviates at least one technical defect of the known aspects. The technical scheme of the application is as follows: The device comprises a supporting cylinder, a load sensor, a displacement sensor, a load measuring end mounting joint, an energy absorption assembly, a plunger rod and a displacement measuring end mounting joint; One end of the supporting cylinder is a load measuring end, the other end of the supporting cylinder is a displacement measuring end, the load measuring end is externally connected with a load sensor, and the displacement measuring end is externally connected with a displacement sensor; The load sensor is connected with a load measuring end mounting joint; The energy absorption assembly comprises an elastic piece and a punched end, wherein the elastic piece is arranged in the supporting cylinder, one end of the elastic piece is connected in the load measuring end, the other end of the elastic piece is connected with the punched end, and the punched end can slide in the supporting cylinder; The punch rod penetrates through the displacement measuring end and the punched end, and is provided with two punches which are positioned in the supporting cylinder and distributed on two sides of the punched end; The displacement sensor is sleeved on the periphery of the punch rod and used for detecting the displacement of the punch rod; the displacement measuring end mounting joint is connected to one end of the punch rod, which is positioned outside the supporting cylinder. According to at least one embodiment of the application, in the above-mentioned airplane flap fault test flap crosslinking measuring device, the load sensor is a high-frequency load sensor; The d