CN209905103U - Comprehensive test device for reliability and static strength/rigidity of aircraft nose landing gear uplock - Google Patents
Comprehensive test device for reliability and static strength/rigidity of aircraft nose landing gear uplock Download PDFInfo
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- CN209905103U CN209905103U CN201920651373.3U CN201920651373U CN209905103U CN 209905103 U CN209905103 U CN 209905103U CN 201920651373 U CN201920651373 U CN 201920651373U CN 209905103 U CN209905103 U CN 209905103U
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Abstract
The utility model provides an aircraft nose landing gear uplock reliability and static strength/rigidity's combined test device can be according to the corresponding load of operating condition loading, and the experimental data of reliability is also close objective requirement more. The comprehensive test device comprises an experiment bracket, an upper lock, a loading drive module and a lock ring module; the upper lock is fixedly arranged on a cross beam of the experiment bracket; in the locking ring module, a locking ring base is provided with a bottom surface and two lateral lugs, and two ends of a locking ring penetrate through a locking ring support body and are respectively fixedly connected with the two lateral lugs of the locking ring base; one end of the strut is fixedly connected with one end of the lock ring support body, which is far away from the lock ring, and the other end of the strut is rotatably connected with one side of the experiment 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 experiment support, 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 utility model relates to an aeronautical equipment uplock reliability test technical field, concretely relates to a test device that is used for accurate loading load of aircraft nose landing gear uplock.
Background
The landing gear uplock is used for locking or unlocking various motion mechanisms on an airplane, is an important part of an airplane landing gear system, and is a key product for judging whether the landing gear can normally work or not. It has the characteristics of small weight and volume, high static strength requirement, high structural precision and the like. In normal flight, the uplock should be normally closed and kept in a normally locked state or normally opened, otherwise, the task of the airplane is failed and the flight safety of the airplane is affected. Particularly, in the landing stage of the airplane, if the uplock cannot be normally opened, the undercarriage 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 and improve the reliability level, it is necessary to perform a reliability test on the uplock in a laboratory environment.
Because the comprehensive factors such as vibration, high and low temperature, humidity, hydraulic pressure and the like need to be considered in the reliability test of the uplock, the uplock testing device is required to have smaller volume, smaller weight and larger rigidity, the motion function of the uplock can be simulated, and the structure and the functional principle of the testing device are also required to be as simple as possible in order to ensure the reliability of the testing device. In addition, the load of the locking ring loaded on the locking hook in the locking and unlocking process is one of the key factors influencing the unlocking/locking function and reliability of the upper locking, and the adjustment of the load of the locking hook needs to be realized in the test process.
Chinese patent document CN107084834A discloses an uplock reliability test device capable of realizing lock ring lateral position adjustment, and chinese patent document CN103983443A discloses a horizontal test device for reliability test of uplock of landing gear doors of aircraft. The two schemes have complex structures, can only complete the reliability test of the locking and unlocking functions, and cannot realize the accurate loading of the load, so that the reliability of the uplock under the real flight condition 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 fixtures, 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.
SUMMERY OF THE UTILITY MODEL
In order to make the overhead lock reliability test can reflect the practical application scene more comprehensively, truthfully, and not only accomplish the reliability test of unblanking, locking function, the utility model provides an aircraft nose landing gear overhead lock reliability and static strength/rigidity's comprehensive test device can be according to the corresponding load of operating condition loading, and the experimental data of reliability also is close objective requirement more.
The technical scheme of the utility model as follows:
a comprehensive test device for reliability and static strength/rigidity of an uplock of a nose landing gear of an airplane comprises an experiment bracket, the uplock, a loading driving module and a lock ring module;
the upper lock is fixedly arranged on a cross beam of the experiment bracket;
the lock ring module comprises a lock ring, a lock ring support body, a lock ring base and a strut; the locking ring base is provided with a bottom surface and two lateral lugs, and two ends of the locking ring penetrate through the locking ring support body and are respectively fixedly connected with the two lateral lugs of the locking ring base; one end of the strut is fixedly connected with one end of the lock ring support body, which is far away from the lock ring, and the other end of the strut is rotatably connected with one side of the experiment 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 experiment support, 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 locking and unlocking functions.
Based on above scheme, the utility model discloses still further optimize as follows:
the upper lock body can be fixedly connected with the cross beam of the experiment support through the upper lock mounting frame.
One end of the strut can be fixedly connected with one end of the lock ring support body far away from the lock ring through a connecting rod coaxial with the strut.
The locking ring support body is provided with two lateral lugs, and two ends of the locking ring penetrate through the two lateral lugs of the locking ring support body and are fixedly connected with the two lateral lugs of the locking ring base respectively. Of course, the lock ring supporter can also adopt other shapes and structures which can be more complex as long as the lock hook is not influenced to contact the lock ring.
For the installation of the loading driving module, an actuator cylinder mounting seat can be added, the actuator cylinder mounting seat is fixedly installed at the bottom of the experiment support, and the fixed end of the actuator cylinder is hinged with the actuator cylinder mounting seat. Of course, a pair of tabs may be formed directly on the bottom of the experimental frame for mounting the actuator cylinder.
For the installation of the strut, a pair of lugs can be arranged on one side of the experimental support, pin holes are formed in the lugs, and the strut is installed between the lugs through pins. The pair of lugs can be directly formed on the experiment support, or can be additionally arranged and fixedly installed on the experiment support, and is equivalent to a strut mounting seat.
Based on above device structure, can consolidate the experiment support, adopt pressure sensor accurate enough to not only be applicable to the reliability test, also be applicable to static intensity/rigidity test.
The reliability test comprises the following steps:
a1) initial state: the lock hook is in an open state, and the lock ring is in a preset position;
a2) the oil pressure pressurizing system supplies pressure, a piston rod of the actuating cylinder extends out to drive the locking ring to move upwards, the locking 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 time;
a3) the oil pressure pressurizing system supplies pressure, a piston rod of the actuating cylinder generates downward pulling force on the locking ring, and when the pulling force reaches a set load value, the state is kept for a set time;
a4) controlling the upper lock to unlock, and enabling a piston rod of the actuating cylinder to contract to drive the lock ring to move back to a preset position;
repeating the steps a2) to a4) for a set number of times to complete the reliability test;
the static strength/stiffness test comprises the following steps:
b) load test borne by landing gear retraction uplock
b1) Adjusting the upper lock to be in a locking state;
b2) gradually applying upward pressure to the upward locking hook, and keeping the state for a set time when the set pressure is reached;
b3) recording the experimental condition, and unloading the pressure of the upper lock;
c) load test borne by landing gear lowering uplock
c1) Adjusting the upper lock to be in a locking state;
c2) gradually applying a downward pulling force to the upward locking hook, and keeping the set state for a set time when the set pulling force is reached;
c3) recording the experimental condition, and unloading the tension of the upper lock;
at this point, the static strength/stiffness test was completed.
The utility model discloses following beneficial effect has:
1. the static strength/rigidity test and the reliability test are integrated in one test bed, two factors of force and direction are fully considered, load can be applied according to actual working conditions, and the experimental data have reference.
2. Through the arrangement of the pressure sensor and the structural connection of the pressure sensor and the lock ring, the load of the lock hook is fed back to the control system, and therefore the reliability test of the landing gear uplock is completed more accurately according to actual design indexes.
3. The overall structure is simple and clear, the realization is simple and convenient, and the comprehensive test cost is lower.
Drawings
Fig. 1 is a schematic plan view of the test device in the locked state.
Figure 2 is a detailed view of the structure associated with the locking collar.
Fig. 3 and 4 are schematic perspective views of the testing device at two different viewing angles in the locked state.
Fig. 5 is a schematic plan view of the test device in an unlocked state.
Fig. 6 and 7 are schematic perspective views of the test device at two different viewing angles in an unlocked state.
FIG. 8 is a diagram of the overall system architecture for reliability testing of the uplock.
The reference numbers illustrate:
1-experimental support, 2-upper lock mounting rack, 3-upper lock, 4-pillar, 5-pressure sensor, 6-lock ring, 7- (upper lock) lock hook, 8-actuator cylinder, 9-lock ring base, 10-actuator cylinder mounting seat, 11-experimental support lug (pillar mounting seat), 12-lock ring support body and 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 testing device can be mainly divided into a testing bench, a lock ring module and a loading driving module. The upper lock is installed on the experiment bench, and the lock ring module and the loading driving module are arranged in the inner area of the experiment bench. Specifically, the method comprises the following steps:
the experiment bench includes experiment support 1 and upper lock mounting bracket 2, and upper lock mounting bracket passes through the screw and installs on the crossbeam of experiment support, and upper lock installs on upper lock mounting bracket.
The shackle module includes a shackle 6, a shackle carrier 12, a connecting rod 13, a shackle base 9, and a post 4. The locking ring base is provided with a bottom surface and two lateral lugs, the locking ring support body is also provided with two lateral lugs, and two ends of the locking ring 6 penetrate through the two lateral lugs of the locking ring support body 12 and are fixedly connected with the two lateral lugs of the locking ring base 9 respectively. The right side of the experimental support is also provided with a pair of lugs, the pair of lugs are respectively provided with a pin hole, the right end of the strut 4 is arranged between the pair of lugs through a pin, and the lock ring support body 12 is connected with the left end of the strut 4 through a connecting rod 13. Both ends of connecting rod 13 all have the screw thread, and one end is installed in the screwed hole of pillar 4, through the connecting rod of configuration different length, can adjust the distance of catch to experiment support auricle to adjust loading drive module's the direction (angle) that actuates.
The loading driving module comprises an actuating cylinder 8, an actuating cylinder mounting seat 10 and a pressure sensor 5, the actuating cylinder mounting seat 10 is welded on the experimental support, one end of the actuating cylinder 8 is connected to the actuating cylinder mounting seat 10 through a pin, the other end of the actuating cylinder is connected with the pressure sensor 5 through a screw, and the pressure sensor 5 and the bottom surface of the lock ring base 9 are fixed through screws.
The pin joint of the locking ring 6, the fixed end of the actuating cylinder and the pin joint at the right end of the strut naturally form a triangular stable structure, and the included angle of the locking ring is an obtuse angle generally. The pull rod of the actuating cylinder 8 stretches and retracts 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 lug 11 of the experiment support, and meanwhile, the lock ring can touch the lock hook 7 to achieve the unlocking and locking functions through the up-and-down reciprocating motion of the lock ring.
And (3) reliability experiment:
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 pressure sensor is locked, the actuator cylinder 8 supplies pressure to the pressure cavity, the piston rod of the actuator cylinder 8 extends out to drive the lock ring 6 to move upwards, the lock hook 7 is actively closed after the upper lock is triggered, and when the pressure of the pressure sensor reaches a real flight load value, the state is kept for 3 seconds.
And step 3: after the upper lock is closed, pressure is supplied to an oil return cavity of the actuating cylinder 8, a piston rod of the actuating cylinder 8 generates downward pulling force on the lock ring 6, and when the pulling force reaches the real flight load value of the upper lock, the state is kept for 3 seconds.
And 4, step 4: the upper lock is controlled to be unlocked, and the piston rod of the actuating cylinder 8 contracts to drive the lock ring 6 to move to a preset position.
And (5) repeating the step (2) to the step (4) for a set number of times to complete the reliability test of the upper lock. The structural design of the test device fully simulates the position relation of the actual upper lock of the nose landing gear, and the locking and unlocking directions of the upper lock are consistent with the real working condition.
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 actuating cylinder and the upper position lock to act. The pressure sensor is used for measuring the loading load of the upper lock. The pressure sensor at the head of the ram feeds back a force signal and other detection signals to the console. The nose landing gear uplock base body part is arranged on a cross beam on a test bed rack. 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 strut is connected with the pressure sensor through a lock ring base. The piston rod of the actuating cylinder stretches and retracts to drive the support column to rotate so as to simulate the front landing gear to realize retraction and extension actions.
The device can also carry out static strength/rigidity experiments, and the test contents of the experiments comprise:
1) load test borne by nose landing gear retraction uplock
1.1) adjusting the upper lock to be in a locking state.
1.2) by gradually applying upward pressure to the nose landing gear uplock hook, when the pressure reaches a set value, the pressure state is maintained for a set time, and the uplock structure should not be damaged in the time period.
1.3) after the upper lock strain test data is recorded, unloading the pressure of the upper lock.
2) Load test borne by nose landing gear lowering uplock
2.1) adjusting the upper lock to be in a locking state.
2.2) gradually applying downward pulling force to the lock hook of the upper lock of the nose landing gear, when the pulling force reaches a set value, keeping the set time in the pulling force state, and preventing the structure of the upper lock from being damaged in the time period.
And 2.3) unloading the tension of the uplock after the log of the uplock strain test data is finished.
Claims (6)
1. The utility model provides an integrated test device of aircraft nose landing gear uplock reliability and quiet intensity/rigidity which characterized in that: the device comprises an experiment bracket, an upper lock, a loading driving module and a lock ring module;
the upper lock is fixedly arranged on a cross beam of the experiment bracket;
the lock ring module comprises a lock ring, a lock ring support body, a lock ring base and a strut; the locking ring base is provided with a bottom surface and two lateral lugs, and two ends of the locking ring penetrate through the locking ring support body and are respectively fixedly connected with the two lateral lugs of the locking ring base; one end of the strut is fixedly connected with one end of the lock ring support body, which is far away from the lock ring, and the other end of the strut is rotatably connected with one side of the experiment 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 experiment support, 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 locking and unlocking functions.
2. The integrated test device for reliability and static strength/rigidity of the uplock of the nose landing gear of the aircraft according to claim 1, characterized in that: the upper lock is fixedly connected with the cross beam of the experiment support through an upper lock mounting frame.
3. The integrated test device for reliability and static strength/rigidity of the uplock of the nose landing gear of the aircraft according to claim 1, characterized in that: one end of the strut is fixedly connected with one end of the lock ring support body far away from the lock ring through a connecting rod coaxial with the strut.
4. The integrated test device for reliability and static strength/rigidity of the uplock of the nose landing gear of the aircraft according to claim 1, characterized in that: the locking ring support body is also provided with two lateral lugs, and two ends of the locking ring penetrate through the two lateral lugs of the locking ring support body and are respectively and fixedly connected with the two lateral lugs of the locking ring base.
5. The integrated test device for reliability and static strength/rigidity of the uplock of the nose landing gear of the aircraft according to claim 1, characterized in that: the loading driving module further comprises an actuating cylinder mounting seat, the actuating cylinder mounting seat is fixedly mounted at the bottom of the experiment support, and the fixed end of the actuating cylinder is hinged to the actuating cylinder mounting seat.
6. The integrated test device for reliability and static strength/rigidity of the uplock of the nose landing gear of the aircraft according to claim 1, characterized in that: one side of the experiment support is provided with a pair of lug plates, pin holes are formed in the lug plates, and the supporting column is installed between the lug plates through pins.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920254485 | 2019-02-28 | ||
| CN2019202544855 | 2019-02-28 |
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| CN209905103U true CN209905103U (en) | 2020-01-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109969428A (en) * | 2019-02-28 | 2019-07-05 | 西安生淼机电科技有限责任公司 | A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method |
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2019
- 2019-05-08 CN CN201920651373.3U patent/CN209905103U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109969428A (en) * | 2019-02-28 | 2019-07-05 | 西安生淼机电科技有限责任公司 | A kind of aircraft nose landing gear uplock reliability and static strength/rigidity integrated experiment device and method |
| CN109969428B (en) * | 2019-02-28 | 2024-03-29 | 西安生淼机电科技有限责任公司 | Test method of comprehensive test device for reliability and static strength/rigidity of upper lock of nose landing gear of airplane |
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