CN110697077B - It is used for the performance test device of the nose landing gear of the fighter aircraft. - Google Patents

Abstract

The present invention provides a device for testing the performance of the nose landing gear of a fighter plane, which includes a test frame assembly, a front landing gear assembly, a vertical motion assembly and a rotary motion assembly. The rotary motion assembly includes a shaft gear, a guide seat, an encoder, a The first lug plate, the first baffle plate, the rectangular guide rod, the second lug plate and the second baffle plate, the middle part of the guide seat is provided with a rectangular hole that penetrates vertically, and the side surface of the lower part of the rectangular guide rod is provided with a first lug plate and the second lug plate, the first and second lug plates are respectively provided with cylindrical holes that penetrate vertically, the first and second baffle plates are discs with a central cylindrical hole, and the vertical movement components include a swing plate , Loading head, thrust sliding bearing and lifting table, the middle of the short side of the lifting table is provided with a vertical cylindrical hole, the upper end face of the loading head is provided with a ball socket, and the lower end face of the loading head is connected with the upper surface of the swing plate. The invention solves the precise problem of the performance test of the neutralization, can achieve precise loading and detection, and realize the real-time display and storage of data.

Description

It is used for the performance test device of the nose landing gear of the fighter aircraft.

technical field

The invention relates to the technical field of design and development of a performance test device, in particular to a performance test device for the return of the front landing gear of a fighter plane.

Background technique

The nose landing gear of a fighter aircraft is one of the key components of a fighter aircraft. Its working performance, reliability and stability will directly affect the flight safety of the fighter aircraft. Therefore, various ground tests must be carried out on the nose landing gear of the fighter before installation. The nose landing gear return performance test is one of many ground tests.

The test process of the performance of the nose landing gear returning to the center: 1) Install the nose landing gear on the frame, and the piston rod of the buffer strut is in a fully extended state; 2) Compress the piston rod of the buffer strut by at least 200mm, and the piston rod of the buffer strut to the left or right After rotating a certain angle, remove the external force quickly, measure the angular position of the piston rod of the buffer strut after returning to the center and record; 3) The orientation of the force line of the external force applied in the test should be located on the axis of the piston rod of the buffer strut.

In the past, hydraulic jacks were mostly used for manual loading of the nose landing gear in the performance test. The disadvantages are: 1) low loading accuracy, 2) poor detection accuracy, and 3) labor intensity of workers.

SUMMARY OF THE INVENTION

Aiming at the problems existing in the traditional re-centering performance test, the present invention provides a device for the re-centering performance of the nose landing gear of a fighter aircraft, which is mainly to simplify the operation process, improve the loading accuracy, improve the detection accuracy, reduce the labor intensity of workers, and obtain better realistic experimental data.

The present invention provides a test device for the return-to-center performance of the front landing gear of a fighter, which includes a test frame assembly, a front landing gear assembly, a vertical motion assembly and a rotary motion assembly. The front landing gear assembly includes a front landing gear body, a nose landing gear bumper strut, bumper strut piston rod, nose gear bearing head and landing gear eccentric disc, the nose gear assembly is mounted on the lower surface of the upper beam of the test frame, the nose gear bumper strut and the front landing gear The landing gear body is fixedly connected, the front landing gear buffer strut is provided with a vertical central hole, the central hole of the front landing gear buffer strut is connected with the buffer strut piston rod, and the end face of the buffer strut piston rod is connected to the end surface of the buffer strut. The first end face of the eccentric disc of the landing gear is connected, the second end face of the eccentric disc of the landing gear is fixedly connected with the upper end face of the bearing head of the front landing gear, and the lower end face of the bearing head of the front landing gear is provided with an outer convex circle ball. The test frame assembly includes a test frame, an electric control system, a base and a column, the base is located in the middle of the upper surface of the lower beam of the test frame, and the electronic control system is located at the lower beam of the test frame The right end of the upper surface of the upper surface; the rotary motion assembly includes an outer ring gear, a shaft gear, a guide seat, an encoder, an encoder rotating shaft, a first lug plate, a first baffle plate, a rectangular guide rod, and a second lug plate and the second baffle, the middle part of the guide seat is provided with a rectangular hole that penetrates vertically, the side surface of the guide seat is fixedly connected with the outer wall of the buffer strut of the front landing gear, and the shaft gear is from top to bottom. The upper shaft end, the cylindrical gear and the lower shaft end in sequence, the side surface of the lower part of the rectangular guide rod is provided with a first lug plate and a second lug plate, and the first lug plate and the second lug plate are respectively provided with a cylindrical hole that penetrates vertically, the first baffle plate and the second baffle plate are both discs with a central cylindrical hole, the inner diameter of the outer gear ring and the outer cylindrical surface of the buffer strut piston rod Fixed connection. The vertical motion assembly includes rolling guide slider, rolling guide, pull wire sensor, pull wire of pull wire sensor, cantilever beam, sleeve cup, swing plate, loading head, thrust sliding bearing, lifting table, pressure plate, loading cylinder piston rod , Loading oil cylinder, hydraulic station, swing shaft, oil port with rod cavity and oil port without rod cavity, the long side of the lifting table is in the vertical direction, the short side is in the horizontal direction, and the middle of the short side of the lifting table is provided with a vertical The downward cylindrical hole, the thrust sliding bearing is a ring with a central cylindrical hole, the upper end surface of the loading head is provided with a ball socket, and the lower end surface of the loading head is fixed with the upper surface of the swing plate connection, the outer convex spherical surface of the front landing gear carrying head and the ball and socket of the loading head are in clearance fit, the hydraulic station is fixedly connected to the upper surface of the lower beam of the test frame, and is located under the test frame On the left end of the upper surface of the beam, the shell of the pull-wire sensor is fixedly connected with the second side surface of the upright column, and the pull-wire sensor is connected with the electric control system through an electric cable.

Preferably, in the test frame assembly, the shape of the test frame is a back-shaped frame, which is formed by welding an upper beam, a lower beam and left and right uprights, and the test frame is fixedly connected to the concrete foundation. The electric control system and the base are respectively fixedly connected with the upper surface of the lower beam of the test frame, and the end surface of the upright column is fixedly connected with the base.

Preferably, in the rotary motion assembly, the rectangular guide rod is in clearance fit with the rectangular hole of the guide seat, and hangs out of the guide seat from both ends, and the upper shaft end of the shaft gear and the lower shaft The shaft ends are clearance fit with the cylindrical holes of the first lug plate and the second lug plate through the central cylindrical holes of the first baffle plate and the second baffle plate respectively. The second baffle plate is respectively fixedly connected with the upper and lower end surfaces of the cylindrical gear of the shaft gear, the shaft gear is meshed with the outer ring gear, the encoder rotating shaft is fixedly connected with the upper shaft end of the shaft gear, The casing of the encoder is fixedly connected to the side surface of the rectangular guide rod, and the encoder is connected to the electric control system through an electric cable.

Preferably, in the vertical motion assembly, the first side surface of the rolling guide rail and the first side surface of the column are fixedly connected, and the second side surface of the rolling guide rail and the first side surface of the rolling guide rail slider are fixedly connected. connection, the second side of the rolling guide slider is fixedly connected to the outer side of the long side of the lifting platform, the swing shaft is clearance fit with the cylindrical hole on the short side of the lifting platform through the thrust sliding bearing, the The lower end surface of the thrust sliding bearing is fixedly connected to the upper end surface of the short side of the lifting platform, the lower end surface of the swing shaft is fixedly connected to the pressing plate, and the upper end surface of the swing shaft is fixed to the lower surface of the swing plate. The upper surface of the sleeve cup is fixedly connected with the lower end surface of the short side of the lifting platform, the outer circle of the pressure plate is connected with the inner diameter of the sleeve cup, and the upper surface of the pressure plate is connected with the upper surface of the sleeve cup. The surfaces are flush, the lower surface of the sleeve cup is fixedly connected to the upper end surface of the piston rod of the loading cylinder, the lower surface of the loading cylinder is fixedly connected to the upper surface of the base, the cantilever beam and the The upper end face of the short side of the lift table is fixedly connected and hangs out of the lift table to the right side. The tail is fixedly connected with the pull wire sensor.

Preferably, the diameter of the central cylindrical hole of the thrust sliding bearing is larger than the outer diameter of the swing shaft, the width of the cylindrical gear of the shaft gear is larger than the width of the outer ring gear, the first baffle and the The diameter of the central cylindrical hole of the second baffle is larger than the diameter of the upper and lower shaft segments of the shaft gear, and the outer diameters of the first baffle and the second baffle are larger than the teeth of the cylindrical gear of the shaft gear. The diameter of the top circle, the outer diameter of the pressing plate and the inner diameter of the sleeve cup are equal.

Preferably, the axes of the first lug plate, the second lug plate, the first baffle plate, the second baffle plate and the shaft gear are located on the same axis, and the swing plate, the The axes of the swing shaft, the pressing plate, the piston rod of the buffer strut and the piston rod of the loading oil cylinder are located on the same straight line.

Preferably, the swing assembly composed of the swing plate, the swing shaft and the pressure plate and the elevator assembly composed of the lifting platform and the thrust sliding bearing are in clearance fit, and the shaft gear, the The baffle assembly formed by the first baffle and the second baffle forms a clearance fit with the first ear plate and the second ear plate, and the first baffle and the second baffle There is clearance fit with the outer gear ring.

Preferably, the outer ring gear, the shaft gear, the first lug plate, the second lug plate and the rectangular guide rod are made of light polymer materials, and the first The material of the plate and the second baffle is polytetrafluoroethylene.

Compared with the prior art, the present invention has the following advantages:

After the invention saves the process of artificially using a jack to load the force, the loading accuracy of the fighter's front landing gear return performance test is higher and the detection accuracy is also higher, and finally the experimental results are more accurate, close to the reality, and also for the follow-up other other Simulation experiments provide a guarantee basis. Compared with the previous experiment, the present invention can realize real-time display and storage of data, and provide fault reverse inspection data, which improves the simulation accuracy of the horizontal landing speed of the fighter, and also reduces the labor intensity of workers. The invention has the advantages of reasonable structure, wide application, low manufacturing cost, stable performance, simple installation and loading, and is suitable for the performance test of the nose landing gear of different types and models of fighter aircraft.

Description of drawings

Fig. 1 is the front view of the overall structure of the present invention for the nose landing gear return performance test device;

FIG. 2 is a schematic cross-sectional structure diagram of the present invention used in the A-A direction of the nose landing gear return performance test device; and

FIG. 3 is a partial enlarged schematic diagram of the present invention for the performance test device for the nose landing gear of a fighter.

Main reference signs:

Electronic control system 1, rolling guide slider 2, rolling guide 3, cable sensor 4, cable sensor 5, cantilever beam 6, cup 7, swing plate 8, front landing gear buffer strut 9, buffer strut piston rod 10, Front landing gear carrying head 11, loading head 12, thrust sliding bearing 13, lifting platform 14, pressure plate 15, outer gear 16, shaft gear 17, loading cylinder piston rod 18, loading cylinder 19, hydraulic station 20, base 21, Column 22, landing gear eccentric disc 23, test frame 24, swing shaft 25, oil port with rod cavity 26, oil port without rod cavity 27, guide seat 28, encoder 29, encoder rotating shaft 30, first lug 31, the first baffle 32, the rectangular guide rod 33, the second lug plate 34, the second baffle 35.

Detailed ways

In order to detail the technical content, structural features, achieved objects and effects of the present invention, the following will be described in detail with reference to the accompanying drawings.

It is used for the test device for the return performance of the nose landing gear of a fighter, as shown in Figure 1, which includes a test frame assembly, a nose landing gear assembly, a vertical motion assembly and a rotary motion assembly.

The front landing gear assembly includes the front landing gear body, the front landing gear buffer strut 9, the buffer strut piston rod 10, the front landing gear bearing head 11 and the landing gear eccentric disc 23, and the front landing gear assembly is mounted on the test frame 24 on the beam The lower surface of the front landing gear buffer strut 9 is fixedly connected to the front landing gear body, the front landing gear buffer strut 9 is provided with a vertical central hole, and the central hole of the front landing gear buffer strut 9 is connected with the buffer strut piston rod 10, which can be For relative axial movement and relative rotation, the end face of the buffer strut piston rod 10 is connected with the first end face of the landing gear eccentric disc 23, and the second end face of the landing gear eccentric disc 23 is fixedly connected with the upper end face of the front landing gear bearing head 11. The lower end surface of the nose landing gear carrying head 11 is provided with a convex spherical ball.

The test frame assembly, as shown in FIG. 1, includes a test frame 24, an electric control system 1, a base 21 and a column 22. The base 21 is located in the middle of the upper surface of the lower beam of the test frame 24, and the electric control system 1 is located in the test frame. The right end of the upper surface of the lower beam of the frame 24, the shape of the test frame 24 is a back-shaped frame, which is welded by the upper beam, the lower beam and the left and right columns 22. The test frame 24 is fixedly connected to the concrete foundation, and the electronic control system 1 and The bases 21 are respectively fixedly connected to the upper surfaces of the lower beams of the test frame 24 , and the end surfaces of the uprights 22 are fixedly connected to the bases 21 .

The rotary motion assembly, as shown in Figure 3, includes the outer ring gear 16, the shaft gear 17, the guide seat 28, the encoder 29, the encoder rotating shaft 30, the first lug plate 31, the first baffle plate 32, and the rectangular guide rod 33. The second lug plate 34 and the second baffle plate 35, the middle part of the guide seat 28 is provided with a rectangular hole that penetrates vertically, the side surface of the guide seat 28 is fixedly connected with the outer wall of the front landing gear buffer strut 9, the shaft gear 17, From top to bottom are the upper shaft end, the cylindrical gear and the lower shaft end. The upper shaft end and the lower shaft end have the same diameter and are coaxial with the index circle of the cylindrical gear. The side of the lower part of the rectangular guide rod 33 is provided with a first lug plate 31 and the second lug plate 34, the first lug plate 31 and the second lug plate 34 are respectively provided with cylindrical holes that penetrate vertically, and the first baffle plate 32 and the second baffle plate 35 are provided with a central cylindrical hole. The disk, the inner diameter of the outer gear ring 16 and the outer cylindrical surface of the buffer strut piston rod 10 are fixedly connected.

In the rotary motion assembly, as shown in FIG. 3 , the rectangular guide rod 33 is clearance fit with the rectangular hole of the guide seat 28 , and hangs out of the guide seat 28 from both ends. The upper shaft end and the lower shaft end of the shaft gear 17 are respectively Through the clearance fit between the central cylindrical holes of the first baffle 32 and the second baffle 35 and the cylindrical holes of the first lug 31 and the second lug 34, the first baffle 32 and the second baffle 35 are respectively connected with the shaft gear 17 The upper and lower ends of the cylindrical gear are fixedly connected, the shaft gear 17 meshes with the outer ring gear 16, the encoder rotating shaft 30 is fixedly connected to the upper shaft end of the shaft gear 17, and the outer casing of the encoder 29 is fixedly connected to the side of the rectangular guide rod 33. , the encoder 29 is connected to the electric control system 1 through an electric cable.

The vertical motion assembly, as shown in Figures 1 and 2, includes a rolling guide slider 2, a rolling guide 3, a pull wire sensor 4, a pull wire sensor 5, a cantilever beam 6, a cup sleeve 7, a swing plate 8, and a loading head 12 , thrust sliding bearing 13, lifting platform 14, pressure plate 15, loading cylinder piston rod 18, loading cylinder 19, hydraulic station 20, swing shaft 25, rod cavity oil port 26 and rodless cavity oil port 27. The hydraulic station 20 is connected with the rod chamber oil port 26 and the rod chamber oil port 27 of the loading cylinder 19 through an oil pipe and a reversing valve.

The long side of the lift table 14 is in the vertical direction, the short side is in the horizontal direction, the middle of the short side of the lift table 14 is provided with a cylindrical hole vertically downward, the thrust sliding bearing 13 is a ring with a central cylindrical hole, and the loading head 12 The upper end face of the load head 12 is provided with a ball socket, the lower end face of the loading head 12 is fixedly connected with the upper surface of the swing plate 8, the convex spherical surface of the front landing gear carrying head 11 and the ball socket of the loading head 12 are clearance fit, the hydraulic station 20 and the test The upper surface of the lower beam of the frame 24 is fixedly connected, and is located at the left end of the upper surface of the lower beam of the test frame 24. The outer shell of the cable sensor 4 is fixedly connected to the second side of the column 22, and the cable sensor 4 and the encoder 29 are connected to the electronic control system. 1. Using electrical connection, the detection data of the pull wire sensor 4 and the encoder 29 can be displayed on the display screen of the electronic control system 1 in real time and recorded and stored in real time.

The first side of the rolling guide 3 is fixedly connected with the first side of the column 22, the second side of the rolling guide 3 is connected with the first side of the rolling guide slider 2, and the second side of the rolling guide block 2 is connected with the lifting platform 14. The outer side of the long side is fixedly connected, the swing shaft 25 is a clearance fit through the thrust sliding bearing 13 and the cylindrical hole on the short side of the lifting table 14, and the lower end face of the thrust sliding bearing 13 and the upper end face of the short side of the lifting table 14 are fixed. connection, wherein the overall shape of the lifting platform 14 is L-shaped. The lower end face of the swing shaft 25 is fixedly connected to the pressing plate 15, the upper part of the swing shaft 25 is overhanging the lift table 14, the upper end face of the swing shaft 25 is fixedly connected to the lower surface of the swing plate 8, and the upper surface of the cup 7 is connected to the lift table 14. The lower end face of the short side of the table 14 is fixedly connected, the outer circle of the pressure plate 15 is connected with the inner diameter of the sleeve cup 7, the upper surface of the pressure plate 15 is flush with the upper surface of the sleeve cup 7, the lower surface of the sleeve cup 7 and the piston rod of the loading cylinder The upper end surface of 18 is fixedly connected, the lower surface of the loading cylinder 19 is fixedly connected to the upper surface of the base 21, the cantilever beam 6 is fixedly connected to the upper end surface of the short side of the lifting platform 14, and the upper surface of the lifting platform 14 is suspended to the right. In addition, the end of the pull wire 5 of the pull wire sensor is fixedly connected to the extension end of the cantilever beam 6 , and the tail of the pull wire 5 of the pull wire sensor is fixedly connected to the pull wire sensor 4 .

As shown in FIG. 1 , the diameter of the central cylindrical hole of the thrust sliding bearing 13 is larger than the outer diameter of the swing shaft 25 , the width of the cylindrical gear of the shaft gear 17 is larger than the width of the outer ring gear 16 , the first baffle 32 and the second baffle The diameter of the central cylindrical hole of 35 is larger than the diameter of the upper and lower shaft segments of the shaft gear 17, the outer diameter of the first baffle 32 and the second baffle 35 is larger than the diameter of the tooth tip circle of the cylindrical gear of the shaft gear 17, and the outer diameter of the pressure plate 15 It is equal to the inner diameter of the sleeve cup 7 .

The axes of the first lug plate 31 , the second lug plate 34 , the first baffle plate 32 , the second baffle plate 35 and the shaft gear 17 are located on the same axis. It is on the same line as the axis of the piston rod 18 of the loading cylinder.

The swing assembly composed of the swing plate 8 , the swing shaft 25 and the pressure plate 15 and the elevator assembly composed of the lifting platform 14 and the thrust sliding bearing 13 are in clearance fit. The shaft gear 17 , the first baffle 32 and the second baffle 35 constitute A clearance fit is formed between the baffle assembly and the first lug plate 31 and the second lug plate 34 , and a clearance fit is formed between the first baffle plate 32 and the second baffle plate 35 and the outer gear ring 16 . The clearance fit ensures the active connection between the components, so that the phenomenon of sticking or falling off will not occur during the whole experiment process, ensuring the stability of the experimental device and the smooth progress of the experiment.

The outer ring gear 16 , the shaft gear 17 , the first lug 31 , the second lug 34 and the rectangular guide rod 33 are made of light polymer materials, and the first baffle 32 and the second baffle 35 are made of polyamide. Tetrafluoroethylene.

The following is a further description of the present invention for a fighter nose landing gear return performance test device:

As shown in FIG. 1 , the electronic control system 1 sends an instruction to the hydraulic station 20. The hydraulic station 20 is connected to the oil port 27 of the rodless cavity of the loading cylinder 19 through the oil pipe and the reversing valve. The rodless cavity of 19 is fed with oil, and the loading stroke of the loading cylinder 19 is very slow, because the oil supplied by the hydraulic station 20 to the rodless cavity of the loading cylinder 19 is high pressure and small flow.

Under the action of high pressure oil, the piston rod 18 of the loading cylinder moves upwards evenly and slowly, pushing the cup 7, the lifting table 14, the swing shaft 25, the thrust sliding bearing 13, the pressure plate 15, the swing plate 8 and the loading head 12 connected to it. , the rolling guide slider 2 and other components move upward slowly together, and then push the buffer strut piston rod 10 to move upward through the front landing gear bearing head 11 and the landing gear eccentric disc 23, thereby driving the outer cylinder fixed to the buffer strut piston rod 10. The ring gear 16 moves, the shaft gear 17 meshing with the outer ring gear 16 and the first baffle 32 , the second baffle 35 , the first lug 31 , the second lug 34 , the rectangular guide rod 33 connected with the shaft gear 17 Move up slowly together with the encoder 29 etc.

The pull wire sensor 4 is connected to the cantilever beam 6 through the pull wire 5 of the pull wire sensor, and the cantilever beam 6 is fixedly connected to the upper end surface of the short side of the lifting platform 14. Therefore, during the upward movement of the vertical motion component, the pull wire sensor 4 will monitor the buffer strut piston in real time. The moving distance of the rod 10, when the displacement reaches the initial set value, the electronic control system 1 sends an instruction to control the hydraulic station 20 to brake the piston rod 18 of the loading cylinder and maintain this position. The locking process passes through the interior of the hydraulic station 20. The hydraulic lock is realized by rotating the buffer strut piston rod 10 counterclockwise or clockwise to reach a certain angle. This action is realized by the front landing gear assembly. When the buffer strut piston rod 10 rotates at a certain angle, the loading head 12, the swing plate 8, The thrust sliding bearing 13, the swing shaft 25, the pressure plate 15, the front landing gear bearing head 11 and the landing gear eccentric disc 23 also rotate together; at the same time, the encoder rotating shaft 30 is driven to rotate through the outer ring gear 16 and the shaft gear 17, and the encoder 29 will monitor the rotation angle in real time, and when the rotation angle reaches the set value, the electronic control system 1 sends an instruction to stop the rotation movement.

As shown in FIG. 1 , the electronic control system 1 sends an instruction to the hydraulic station 20. The hydraulic station 20 is connected with the oil port 26 of the rod cavity of the loading cylinder 19 through the oil pipe and the reversing valve. The rod cavity of 19 enters the oil, and the return stroke of the loading cylinder 19 is very fast. Since the hydraulic station 20 supplies the oil in the rod cavity of the loading cylinder 19 with a low pressure and a large flow rate, it can make the loading head 12 and the front landing gear bearing head. 11 can be quickly disengaged to ensure that the buffer strut piston rod 10 automatically returns to the center without external force.

When the piston rod 18 of the loading cylinder moves downwards rapidly, the cup 7, the lifting table 14, the swing shaft 25, the thrust sliding bearing 13, the pressure plate 15, the swing plate 8, the loading head 12 and the rolling guide slider 2 are pulled together. Move downward rapidly, so that the loading head 12 and the nose landing gear bearing head 11 are quickly out of contact, and at the same time, the rotational driving torque of the buffer strut piston rod 10 is also removed, the buffer strut piston rod 10 will quickly return to the original position, and the cable sensor 4 And the encoder 29 will monitor the return error of the buffer strut piston rod 10 in real time, and the electronic control system 1 will display and record all the data of the test process in real time.

During the whole experiment, a nitrogen buffer spring is arranged inside the buffer strut 9 of the front landing gear. When an upward external force or torque is applied to the piston rod 10 of the buffer strut to make it move up or rotate, the nitrogen buffer spring is compressed; when the external force When removed, the buffer strut piston rod 10 quickly returns to its original position under the action of the nitrogen buffer spring.

During the loading process of the whole experiment, since there is a large eccentric distance between the force application point of the piston rod 10 of the buffer strut and the axis of the piston rod 18 of the loading cylinder, a large bending moment will be generated. The slider 2, the rolling guide 3 and the upright column 22 bear, while the loading cylinder 19 only bears the axial load.

The above-mentioned embodiments are only to describe the preferred embodiments of the present invention, and do not limit the scope of the present invention. On the premise of not departing from the design spirit of the present invention, those of ordinary skill in the art can make various technical solutions of the present invention. Such deformations and improvements shall fall within the protection scope determined by the claims of the present invention.

Claims (6)

1. A performance test device for the return of a nose landing gear of a fighter plane comprises a nose landing gear assembly, a test frame assembly, a vertical motion assembly and a rotary motion assembly, wherein the nose landing gear assembly comprises a nose landing gear body, a nose landing gear buffer strut, a buffer strut piston rod, a nose landing gear bearing head and a landing gear eccentric disc, the nose landing gear assembly is arranged on the lower surface of an upper cross beam of a test frame, the nose landing gear buffer strut is fixedly connected with the nose landing gear body, the nose landing gear buffer strut is provided with a lead vertical central hole, the central hole of the nose landing gear buffer strut is connected with the buffer strut piston rod, the end surface of the buffer strut piston rod is connected with the first end surface of the landing gear eccentric disc, the second end surface of the landing gear eccentric disc is fixedly connected with the upper end surface of the nose landing gear bearing head, and the lower end surface of the nose landing gear, it is characterized by comprising:

the test frame assembly comprises a test shape frame, an electric control system, a base and an upright post, wherein the base is positioned in the middle of the upper surface of the lower cross beam of the test shape frame, and the electric control system is positioned at the right end of the upper surface of the lower cross beam of the test shape frame; the rotary motion assembly comprises an outer gear ring, a shaft gear, a guide seat, an encoder rotating shaft, a first lug plate, a first baffle plate, a rectangular guide rod, a second lug plate and a second baffle plate, wherein a rectangular hole through which lead vertically penetrates is formed in the middle of the guide seat, the side surface of the guide seat is fixedly connected with the outer wall of the front undercarriage buffer strut, the shaft gear sequentially comprises an upper shaft end, a cylindrical gear and a lower shaft end from top to bottom, the first lug plate and the second lug plate are arranged on the side surface of the lower portion of the rectangular guide rod, cylindrical holes through which lead vertically penetrates are respectively formed in the first lug plate and the second lug plate, the first baffle plate and the second baffle plate are discs with central cylindrical holes, and the inner diameter of the outer gear ring is fixedly connected with the outer cylindrical surface of a buffer strut piston rod;

in the rotary motion assembly, rectangular holes of the rectangular guide rod and the guide seat are in clearance fit and are suspended out of the guide seat from two ends, an upper shaft end and a lower shaft end of the shaft gear are in clearance fit with cylindrical holes of the first lug plate and the second lug plate through central cylindrical holes of the first baffle plate and the second baffle plate respectively, the first baffle plate and the second baffle plate are fixedly connected with the upper end face and the lower end face of the cylindrical gear of the shaft gear respectively, the shaft gear is meshed with the outer gear ring, a rotary shaft of the encoder is fixedly connected with an upper shaft end of the shaft gear, a shell of the encoder is fixedly connected with the side face of the rectangular guide rod, and the encoder is connected with the electric control system through an electric cable;

the vertical motion assembly comprises a rolling guide rail sliding block, a rolling guide rail, a stay wire sensor, a stay wire of the stay wire sensor, a cantilever beam, a sleeve cup, a swing disc, a loading head, a thrust sliding bearing, a lifting platform, a pressing plate, a loading oil cylinder piston rod, a loading oil cylinder, a hydraulic station, a swing shaft, a rod cavity oil port and a rodless cavity oil port, wherein the long edge of the lifting platform is positioned in the vertical direction, the short edge of the lifting platform is positioned in the horizontal direction, a cylindrical hole with a vertical lead is arranged in the middle of the short edge of the lifting platform, the thrust sliding bearing is a circular ring with a central cylindrical hole, a ball socket is arranged on the upper end surface of the loading head, the lower end surface of the loading head is fixedly connected with the upper surface of the swing disc, an outer convex spherical surface of the front undercarriage bearing head is in clearance fit with the ball socket of the loading head, the pull wire sensor is positioned at the left end of the upper surface of the lower cross beam of the test frame, the shell of the pull wire sensor is fixedly connected with the second side surface of the upright post, and the pull wire sensor is connected with the electric control system through an electric cable;

in the vertical motion assembly, a first side face of the rolling guide rail is fixedly connected with a first side face of the upright column, a second side face of the rolling guide rail is connected with a first side face of the rolling guide rail sliding block, a second side face of the rolling guide rail sliding block is fixedly connected with an outer side face of a long edge of the lifting platform, the swinging shaft is in clearance fit with a cylindrical hole of a short edge of the lifting platform through the thrust sliding bearing, a lower end face of the thrust sliding bearing is fixedly connected with an upper end face of the short edge of the lifting platform, a lower end face of the swinging shaft is fixedly connected with the pressing plate, an upper end face of the swinging shaft is fixedly connected with a lower surface of the swinging disc, an upper surface of the sleeve cup is fixedly connected with a lower end face of the short edge of the lifting platform, an outer circle of the pressing plate is connected with an inner diameter of the sleeve cup, and, the lower surface of the sleeve cup is fixedly connected with the upper end face of the piston rod of the loading oil cylinder, the lower surface of the cylinder body of the loading oil cylinder is fixedly connected with the upper surface of the base, the cantilever beam is fixedly connected with the upper end face of the short side of the lifting platform and extends out of the lifting platform towards the right side, the end part of the stay wire sensor is fixedly connected with the extending end of the cantilever beam, and the tail part of the stay wire sensor is fixedly connected with the stay wire sensor.

2. The device for testing the return performance of the nose landing gear of the warplane according to claim 1, wherein in the test frame assembly, the test frame is shaped like a return frame and is formed by welding an upper cross beam, a lower cross beam, a left upright and a right upright, the test frame is fixedly connected with a concrete foundation, the electronic control system and the base are respectively fixedly connected with the upper surface of the lower cross beam of the test frame, and the end surfaces of the uprights are fixedly connected with the base.

3. The device for testing the neutral performance of the nose landing gear of a warplane according to claim 1, wherein the diameter of the central cylindrical hole of the thrust sliding bearing is larger than the outer diameter of the swing shaft, the width of the cylindrical gear of the shaft gear is larger than the width of the outer ring gear, the diameter of the central cylindrical hole of the first baffle and the second baffle is larger than the diameter of the upper shaft section and the lower shaft section of the shaft gear, the diameter of the outer circle of the first baffle and the second baffle is larger than the diameter of the addendum circle of the cylindrical gear of the shaft gear, and the outer diameter of the pressure plate is equal to the inner diameter of the sleeve cup.

4. The apparatus of claim 1, wherein the axes of the first lug plate, the second lug plate, the first baffle plate, the second baffle plate and the shaft gear are located on the same axis, and the axes of the wobble plate, the wobble shaft, the pressure plate, the cushion strut piston rod and the load cylinder piston rod are located on the same line.

5. The device for testing the neutral return performance of the nose landing gear of a warplane according to claim 1 or 3, wherein a swing assembly formed by the swing disc, the swing shaft and the pressure plate and a lifting assembly formed by the lifting platform and the thrust sliding bearing are in clearance fit, a baffle assembly formed by the shaft gear, the first baffle and the second baffle and the first lug and the second lug are in clearance fit, and the first baffle and the second baffle and the outer gear ring are in clearance fit.

6. The device for testing the neutral return performance of the nose landing gear of a warplane according to claim 1, wherein the outer gear ring, the shaft gear, the first lug plate, the second lug plate and the rectangular guide rod are all made of light polymer materials, and the first baffle plate and the second baffle plate are made of polytetrafluoroethylene.

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