CN109969428B - Test method of comprehensive test device for reliability and static strength/rigidity of upper lock of nose landing gear of airplane - Google Patents
Test method of comprehensive test device for reliability and static strength/rigidity of upper lock of nose landing gear of airplane Download PDFInfo
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- CN109969428B CN109969428B CN201910380974.XA CN201910380974A CN109969428B CN 109969428 B CN109969428 B CN 109969428B CN 201910380974 A CN201910380974 A CN 201910380974A CN 109969428 B CN109969428 B CN 109969428B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a test method of a comprehensive test device for reliability and static strength/rigidity of an upper lock of an aircraft nose landing gear, which can load corresponding loads according to actual working conditions, and experimental data of reliability is closer to objective requirements. The comprehensive test device comprises an experiment bracket, an upper lock, a loading driving module and a locking ring module; the upper lock is fixedly arranged on a cross beam of the experimental bracket; in the locking ring module, a locking ring base is provided with a bottom surface and two side lugs, and two ends of the locking ring penetrate through a locking ring support body to be respectively and fixedly connected with the two side lugs of the locking ring base; one end of the support column is fixedly connected with one end of the lock ring support body far away from the lock ring, and the other end of the support column is rotatably connected with one side of the experimental support; the loading driving module comprises an actuating cylinder and a pressure sensor, wherein the fixed end of the actuating cylinder is connected with the bottom of the experimental support in a rotatable mode, and the working end of the actuating cylinder is fixedly connected with the bottom surface of the lock ring base through the pressure sensor.
Description
Technical Field
The invention relates to the technical field of reliability tests of upper locks of aviation equipment, in particular to a test device and a method for accurately loading loads on upper locks of nose landing gears of aircrafts.
Background
The upper lock of the landing gear is used for locking or unlocking various motion mechanisms on the aircraft, is an important part of an aircraft landing gear system, and is a key product for ensuring whether the landing gear can work normally. The device has the characteristics of small weight and volume, high static strength requirement, high structural precision and the like. In normal flight, the upper lock should be normally closed and kept in a normally locked state or normally opened, otherwise, the aircraft mission is failed and the flight safety of the aircraft is affected. Particularly, in the stage of airplane landing, if the upper lock cannot be normally opened, the landing gear cannot be normally put down, and serious accidents such as airplane crash and the like are possibly caused. Therefore, in order to evaluate the reliability index of the landing gear uplock, it is necessary to perform a reliability test on the uplock in a laboratory environment in order to increase the reliability level.
Because the reliability test of the upper lock needs to consider comprehensive factors such as vibration, high and low temperature, humidity, hydraulic pressure and the like, the test device is required to have smaller volume, weight and larger rigidity, the motion function of the upper lock can be simulated, and the structure and the functional principle of the test device are required to be as simple as possible in order to ensure the reliability of the test device. In addition, the load of the lock ring loaded on the lock hook in the locking and unlocking processes is one of key factors influencing the unlocking/locking functions and reliability of the upper lock, and the adjustment of the load of the lock hook is necessary in the test process.
Chinese patent document CN107084834a discloses a device for testing the reliability of the upper lock for adjusting the transverse position of the lock ring, and chinese patent document CN103983443a discloses a device for testing the reliability of the upper lock of the landing gear door of an aircraft. The two schemes are complex in structure, and can only complete reliability tests of locking and unlocking functions, but cannot realize accurate loading of loads, so that reliability of the upper lock under real flight conditions is difficult to reflect.
The conventional static strength/rigidity test is implemented by fixing the upper lock on the universal testing machine through a set of special clamps, but the force direction of the universal testing machine is relatively fixed, so that the accurate simulation of the static strength/rigidity cannot be realized.
Disclosure of Invention
In order to enable the reliability test of the upper lock to reflect the actual application scene more comprehensively and truly, and not just complete the reliability test of unlocking and locking functions, the invention provides a comprehensive test device for the reliability and static strength/rigidity of the upper lock of an aircraft nose landing gear, which can load corresponding loads according to the actual working conditions, and experimental data of the reliability is closer to objective requirements.
The technical scheme of the invention is as follows:
the comprehensive test device for the reliability and static strength/rigidity of the upper lock of the nose landing gear of the aircraft comprises an experimental bracket, an upper lock, a loading driving module and a locking ring module;
the upper lock is fixedly arranged on a cross beam of the experimental bracket;
the locking ring module comprises a locking ring, a locking ring support body, a locking ring base and a support column; the locking ring base is provided with a bottom surface and two side lugs, and two ends of the locking ring penetrate through the locking ring support body to be fixedly connected with the two side lugs of the locking ring base respectively; one end of the support column is fixedly connected with one end of the lock ring support body far away from the lock ring, and the other end of the support column is rotatably connected with one side of the experimental support;
the loading driving module comprises an actuating cylinder and a pressure sensor, the fixed end of the actuating cylinder is connected with the bottom of the experimental support in a rotatable mode, the working end of the actuating cylinder is fixedly connected with the bottom surface of the lock ring base through the pressure sensor, and the lock ring and the upper lock hook meet the position relation required by the locking and unlocking functions.
Based on the scheme, the invention further optimizes the following steps:
the upper lock body can be fixedly connected with the cross beam of the experimental bracket through an upper lock mounting frame.
One end of the support column can be fixedly connected with one end of the lock ring support body, which is far away from the lock ring, through a connecting rod coaxial with the support column.
The lock ring support body is provided with two side lugs, and two ends of the lock ring penetrate through the two side lugs of the lock ring support body to be fixedly connected with the two side lugs of the lock ring base respectively. Of course, the shackle bracket may take other, possibly more complex, shapes and configurations as long as the shackle contact shackle is not compromised.
For the installation of loading drive module, specifically can increase an actuator tube mount pad, actuator tube mount pad fixed mounting is in the bottom of experimental support, and the stiff end and the actuator tube mount pad of actuator tube are articulated. Of course, a pair of lugs can also be directly formed at the bottom of the experimental support for mounting the actuator cylinder.
To the installation of pillar, specifically can set up a pair of tab in one side of experimental support, be provided with the pinhole on the tab, the pillar passes through the pin to be installed between a pair of tab. The pair of lugs can be directly formed on the experimental bracket, or can be additionally arranged and fixedly arranged on the experimental bracket, and the pair of lugs are equivalent to the support column mounting seat.
Based on the device structure, the experimental support can be reinforced, and a pressure sensor with enough precision is adopted, so that the device is not only suitable for reliability tests, but also suitable for static strength/rigidity tests.
The reliability test comprises the following steps:
a1 Initial state): the lock hook is positioned in an open state, and the lock ring is positioned at a preset position;
a2 The hydraulic pressurizing system supplies pressure, a piston rod of the actuating cylinder stretches out to drive the lock ring to move upwards, the lock ring is actively closed after being triggered, and when the pressure of the pressure sensor reaches a set load value, the state is kept for a set period of time;
a3 The oil pressure pressurizing system supplies pressure, a piston rod of the actuating cylinder generates downward tension to the lock ring, and when the tension reaches a set load value, the state is kept for a set period of time;
a4 Controlling the upper lock to unlock, and enabling a piston rod of the actuating cylinder to shrink to drive the lock ring to move back to a preset position;
repeating the steps a 2) to a 4) for a set number of times to complete the reliability test;
the static strength/stiffness test comprises the following steps:
b) Load test born by undercarriage stow up-position lock
b1 Adjusting the upper lock to be in a locking state;
b2 Gradually applying upward pressure to the upper lock hook, and maintaining the set time length in the state when the set pressure is reached;
b3 Recording experimental conditions, and unloading the pressure of the upper lock;
c) Load test born by landing gear lower-upper lock
c1 Adjusting the upper lock to be in a locking state;
c2 Gradually applying downward tension to the upper lock hook, and maintaining the set time length in the state when the set tension is reached;
c3 Recording experimental conditions, and unloading the tension of the upper lock;
thus, the static strength/rigidity test was completed.
The invention has the following beneficial effects:
1. the static strength/rigidity test and the reliability test are integrated in one test bench, two factors of strength and direction are fully considered, load can be applied according to actual working conditions, and experimental data are more referential.
2. Through setting up pressure sensor to with pressure sensor and catch structural connection, make latch hook load feedback to control system, thereby accomplish the reliability test of undercarriage upper lock according to actual design index more accurately.
3. The whole structure is simple, the implementation is simple and convenient, and the comprehensive test cost is low.
Drawings
FIG. 1 is a schematic plan view of the test device in the locked state.
Fig. 2 is a detailed schematic view of the locking ring related structure.
Fig. 3 and 4 are perspective views of the test device in a locked state at two different viewing angles.
Fig. 5 is a schematic plan view of the test device in an unlocked state.
Fig. 6 and 7 are perspective views of the test device in an unlocked state from two different perspectives.
FIG. 8 is a schematic diagram of an overall system architecture for a uplock reliability test.
Reference numerals illustrate:
the device comprises a 1-experiment support, a 2-upper lock mounting frame, a 3-upper lock, a 4-support, a 5-pressure sensor, a 6-lock ring, a 7- (upper lock) lock hook, an 8-actuator cylinder, a 9-lock ring base, a 10-actuator cylinder mounting seat, a 11-experiment support lug (support mounting seat), a 12-lock ring support body and a 13-connecting rod.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1 to 7, the test device can be mainly divided into three parts of a test bench, a locking ring module and a loading driving module. The upper lock is installed on the experiment bench, and the catch module and the loading drive module are arranged in the inner area of the experiment bench. Specifically:
the experiment bench comprises an experiment support 1 and an upper lock mounting frame 2, wherein the upper lock mounting frame is arranged on a cross beam of the experiment support through screws, and the upper lock is arranged on the upper lock mounting frame.
The lock ring module comprises a lock ring 6, a lock ring support body 12, a connecting rod 13, a lock ring base 9 and a support post 4. The lock ring base is provided with a bottom surface and two side lugs, the lock ring support body is also provided with two side lugs, and two ends of the lock ring 6 penetrate through the two side lugs of the lock ring support body 12 and are respectively fixedly connected with the two side lugs of the lock ring base 9. The right side of experimental support also sets up a pair of tab, sets up the pin hole on a pair of tab respectively, and the right-hand member of pillar 4 passes through the pin to be installed between a pair of tab, and catch support 12 passes through connecting rod 13 and is connected with the left end of pillar 4. The connecting rod 13 has the screw thread at both ends, and one end is installed in the screw hole of pillar 4, through the connecting rod of configuration different length, can adjust the catch to the distance of experimental support tab to adjust the actuation direction (angle) of loading drive module.
The loading driving module comprises an actuator cylinder 8, an actuator cylinder mounting seat 10 and a pressure sensor 5, wherein the actuator cylinder mounting seat 10 is welded on the experimental support, one end of the actuator cylinder 8 is connected to the actuator cylinder mounting seat 10 through a pin, the other end of the actuator cylinder 8 is connected with the pressure sensor 5 through a screw, and the pressure sensor 5 is fixed with the bottom surface of the lock ring base 9 through a screw.
The hinge point of the lock ring 6 and the fixed end of the actuating cylinder naturally forms a triangular stable structure, and the included angle of the lock ring is usually an obtuse angle. The pull rod of the actuating cylinder 8 stretches to drive the lock ring base 9 to move, the lock ring base 9 drives the lock ring support body 12 to do circular motion around the experimental support lug 11, and meanwhile, the lock ring can touch the lock hook 7 to complete unlocking and locking functions through up-and-down reciprocating motion.
Reliability test:
step 1: before locking, the locking hook 7 is in an open state and the locking ring 6 is in a predetermined position.
Step 2: when the lock is locked, the actuating cylinder 8 supplies pressure to the pressure cavity, the piston rod of the actuating cylinder 8 stretches out to drive the lock ring 6 to move upwards, after the upper lock is triggered, the lock hook 7 is actively closed, and when the pressure of the pressure sensor reaches a real flight load value, the state is kept for 3 seconds.
Step 3: after the upper lock is closed, the oil return cavity of the actuator cylinder 8 is pressurized, a piston rod of the actuator cylinder 8 generates downward pulling force on the lock ring 6, and when the pulling force reaches the true flight load value of the upper lock, the state is kept for 3 seconds.
Step 4: the upper lock is controlled to be unlocked, and the piston rod of the actuating cylinder 8 is contracted to drive the lock ring 6 to move to a preset position.
And (3) repeating the steps 2-4 for a set number of times to finish the upper lock reliability test. The structural design of the test device fully simulates the position relation of the upper lock of the actual nose landing gear, and the locking and unlocking directions of the upper lock are consistent with the actual working conditions.
The working principle of the whole system is shown in fig. 8, and the control console sends control signals to the oil pressure loading system to respectively control the action of the actuating cylinder and the upper lock. The pressure sensor is used for measuring the loading load of the upper lock. The pressure sensor of the ram head feeds back force signals and other detection signals to the console. The nose landing gear uplock base portion is mounted on a cross beam on the test stand. The head of a piston rod of the actuating cylinder is provided with a high-precision pressure sensor, and a lock ring positioned at the tail end of the support column is connected with the pressure sensor through a lock ring base. The piston rod of the actuating cylinder stretches to drive the support column to rotate so as to simulate the front landing gear to realize the retraction and the extension actions.
The device can also carry out static strength/rigidity experiments, and the test contents of the experiments comprise:
1) Load test born by front landing gear stowing upper lock
1.1 Adjusting the upper lock to be in a locked state.
1.2 By gradually applying an upward pressure to the nose landing gear uplock hook, when the pressure reaches a set point, the pressure is maintained for a set period of time during which the uplock structure should not be broken.
1.3 After the strain test data of the upper lock are recorded, the pressure of the upper lock is unloaded.
2) Load test born by upper lock of nose landing gear under-arm
2.1 Adjusting the upper lock to be in a locked state.
2.2 By gradually applying a downward pulling force to the nose landing gear uplock hook, when the pulling force reaches a set value, the state of the pulling force is maintained for a set time, and the uplock structure should not be destroyed during the time period.
2.3 After the strain test data of the upper lock is recorded, the tension of the upper lock is unloaded.
Claims (6)
1. A test method of a comprehensive test device for reliability and static strength/rigidity of an upper lock of an aircraft nose landing gear comprises an experiment bracket, an upper lock, a loading driving module and a locking ring module;
the upper lock is fixedly arranged on a cross beam of the experimental bracket;
the locking ring module comprises a locking ring, a locking ring support body, a locking ring base and a support column; the locking ring base is provided with a bottom surface and two side lugs, and two ends of the locking ring penetrate through the locking ring support body to be fixedly connected with the two side lugs of the locking ring base respectively; one end of the support column is fixedly connected with one end of the lock ring support body far away from the lock ring, and the other end of the support column is rotatably connected with one side of the experimental support;
the loading driving module comprises an actuating cylinder and a pressure sensor, the fixed end of the actuating cylinder is rotatably connected with the bottom of the experimental bracket, the working end of the actuating cylinder is fixedly connected with the bottom surface of the lock ring base through the pressure sensor, and the lock ring and the upper lock hook meet the position relation required by the locking and unlocking functions;
the method is characterized by comprising a reliability test and a static strength/rigidity test;
the reliability test comprises the following steps:
a1 Initial state): the lock hook is positioned in an open state, and the lock ring is positioned at a preset position;
a2 The hydraulic pressurizing system supplies pressure, a piston rod of the actuating cylinder stretches out to drive the lock ring to move upwards, the lock ring is actively closed after being triggered, and when the pressure of the pressure sensor reaches a set load value, the state is kept for a set period of time;
a3 The oil pressure pressurizing system supplies pressure, the piston rod of the actuating cylinder retracts to generate downward pulling force on the lock ring, and when the pulling force reaches a set load value, the state is kept for a set period of time;
a4 Controlling the upper lock to unlock, and enabling a piston rod of the actuating cylinder to shrink to drive the lock ring to move back to a preset position;
repeating the steps a 2) to a 4) for a set number of times to complete the reliability test;
the static strength/stiffness test comprises the following steps:
b) Load test born by front landing gear stowing upper lock
b1 Adjusting the upper lock to be in a locking state;
b2 Gradually applying upward pressure to the upper lock hook, and maintaining the set time length in the state when the set pressure is reached;
b3 Recording experimental conditions, and unloading the pressure of the upper lock;
c) Load test born by upper lock of nose landing gear under-arm
c1 Adjusting the upper lock to be in a locking state;
c2 Gradually applying downward tension to the upper lock hook, and maintaining the set time length in the state when the set tension is reached;
c3 Recording experimental conditions, and unloading the tension of the upper lock;
thus, the static strength/rigidity test was completed.
2. The method for testing the combined test device for reliability and static strength/rigidity of the upper lock of the nose landing gear of the aircraft according to claim 1, wherein the method comprises the following steps: the upper lock is fixedly connected with the cross beam of the experimental support through an upper lock mounting frame.
3. The method for testing the combined test device for reliability and static strength/rigidity of the upper lock of the nose landing gear of the aircraft according to claim 1, wherein the method comprises the following steps: one end of the support column is fixedly connected with one end of the lock ring support body, which is far away from the lock ring, through a connecting rod coaxial with the support column.
4. The method for testing the combined test device for reliability and static strength/rigidity of the upper lock of the nose landing gear of the aircraft according to claim 1, wherein the method comprises the following steps: the lock ring support body is also provided with two side lugs, and two ends of the lock ring penetrate through the two side lugs of the lock ring support body to be fixedly connected with the two side lugs of the lock ring base respectively.
5. The method for testing the combined test device for reliability and static strength/rigidity of the upper lock of the nose landing gear of the aircraft according to claim 1, wherein the method comprises the following steps: the loading driving module further comprises an actuator cylinder mounting seat, wherein the actuator cylinder mounting seat is fixedly arranged at the bottom of the experimental support, and the fixed end of the actuator cylinder is hinged with the actuator cylinder mounting seat.
6. The method for testing the combined test device for reliability and static strength/rigidity of the upper lock of the nose landing gear of the aircraft according to claim 1, wherein the method comprises the following steps: one side of the experiment support is provided with a pair of lugs, the lugs are provided with pin holes, and the support is installed between the lugs through pins.
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| CN201910150451 | 2019-02-28 | ||
| CN2019101504516 | 2019-02-28 |
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| CN114383934B (en) * | 2022-01-10 | 2023-11-21 | 中航飞机起落架有限责任公司 | Landing gear hook ring lock ring test loading device and method |
| CN114813000A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Load monitoring device and method for buffeting test of aircraft key structure |
| CN115195998B (en) * | 2022-09-16 | 2022-12-23 | 成都纵横大鹏无人机科技有限公司 | Undercarriage winding and unwinding devices and aircraft |
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