Separable loading system for aircraft wheel of aircraft landing gear

Abstract

The invention provides an aircraft landing gear wheel separable loading system, and relates to the technical field of landing gear system simulation equipment. The device comprises a rack, a loading mechanism and a sliding seat, wherein the loading mechanism comprises a plurality of linear power output units arranged on the rack; the sliding seat is arranged on the rack in a liftable manner, an undercarriage mounting part is arranged on the sliding seat, a plurality of bearing and pushing pieces are further arranged on the sliding seat, and each bearing and pushing piece can be driven by a driving unit to be switched between an unfolded state and a folded state; when each bearing and pushing piece is in a retracting state, the sliding seat can cross each linear power output unit to descend; when the bearing and pushing pieces are in the unfolded state, the power output rods can push the bearing and pushing pieces to apply loads to the sliding seat. According to the separable loading system for the aircraft landing gear wheel, the condition that a landing gear system touches the ground in a free falling body mode can be well simulated.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft landing gear system simulation equipment, and in particular to a detachable loading system for aircraft landing gear wheels. Background Art

[0002] After the aircraft landing gear system is developed, it needs to be tested and simulated in advance to verify whether the function of the landing gear meets the index requirements.

[0003] In the prior art, a cylinder disposed on the top of the landing gear generally applies pressure to the landing gear to simulate the load on the landing gear. However, this has the following disadvantages: in the prior art solution, the output end of the cylinder on the top of the landing gear is always connected to the landing gear, so it is difficult to simulate the state of the landing gear system touching the ground in a free fall manner. Summary of the invention

[0004] To this end, the present invention proposes a detachable loading system for aircraft landing gear wheels, so as to better simulate the state of the landing gear touching the ground in a free fall state.

[0005] The technical solution of the present invention is as follows: A detachable loading system for aircraft landing gear wheels, comprising: frame; The loading mechanism comprises a plurality of linear power output units arranged on the frame, each of the linear power output units having a power output rod capable of extending downward; A sliding seat is liftably arranged on the frame, a landing gear mounting portion is provided on the sliding seat, and a plurality of thrust members are also provided on the sliding seat, and a driving unit is provided on the frame; each thrust member can be driven by the driving unit to switch between a deployed state and a retracted state; when each thrust member is in the retracted state, the sliding seat can cross over each linear power output unit and descend; when each thrust member is in the deployed state, each power output rod can push the thrust member and apply a load to the sliding seat.

[0006] Furthermore, a mounting seat is fixedly provided on the sliding seat, and the thrust member includes a thrust plate rotatably provided on the mounting seat, and the thrust plate can rotate between the deployed state and the retracted state.

[0007] Furthermore, the driving unit includes a driving groove arranged on the frame, and a rotating assembly arranged on the thrust member; the driving groove includes a first guide section, an oblique guide section, and a second guide section sequentially connected in series from top to bottom, and the rotating assembly includes a rotating shaft fixed on the thrust plate, a mounting plate sleeved on the rotating shaft, and a guide block arranged on the mounting plate and deviating from the rotating shaft and capable of sliding in the driving groove; when the guide block slides from the first guide section through the oblique guide section and into the second guide section, it can drive the rotating shaft to rotate and rotate the thrust plate from the retracted state to the deployed state.

[0008] Furthermore, the thrust member also includes a limiting plate fixedly connected to the thrust plate and assembled into an L-shape with the thrust plate, and a limiting block is fixed on the mounting seat. When the thrust plate rotates to the expanded state, the limiting plate rotates to abut against the limiting block.

[0009] Furthermore, each of the thrust plates is provided with a spherical groove, and the bottom end surface of each of the power output rods is a spherical surface adapted to the spherical groove. When the power output rod pushes the thrust plate, the spherical surface abuts against the bottom surface of the spherical groove.

[0010] Furthermore, the first guide section and the second guide section extend in the vertical direction respectively, the first guide section is close to the sliding seat relative to the second guide section, and the oblique guide section extends from the end of the first guide section to the end of the second guide section; when the guide block slides from the first guide section through the oblique guide section and into the second guide section, the rotating shaft drives the thrust plate to rotate in the direction away from the sliding seat.

[0011] Furthermore, each of the power output rods is provided with a pressure sensor, and the pressure sensor is used to detect the pressure of the power output rod on the thrust member.

[0012] Furthermore, a displacement sensor for detecting the displacement of the power output rod is provided on the frame.

[0013] Furthermore, two hydraulic cylinders are fixedly arranged on the frame, and the two hydraulic cylinders are disposed on two opposite sides of the sliding seat, and two support plates are arranged on the sliding seat, and the cylinder rods of the two hydraulic cylinders can push the two support plates upward to raise the sliding seat.

[0014] Furthermore, the frame is fixedly provided with a plurality of guide rails, and the sliding seat is fixedly provided with a sliding block capable of sliding on each of the guide rails.

[0015] The working principle and beneficial effects of the present invention are: The aircraft landing gear wheel detachable loading system provided by the present invention is achieved by arranging a plurality of linear power output units on a frame and arranging a plurality of thrust members capable of switching between an extended state and a retracted state on a sliding seat, wherein when the thrust members are in the retracted state, each thrust member can be free from obstruction by each linear power output unit, so that the sliding seat can descend in a nearly free-falling manner, and when the thrust members are in the extended state, the power output rods of each linear power output unit can push the corresponding thrust members downward to apply a simulated load to the landing gear on the sliding seat. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0017] Figure 1 A three-dimensional diagram of a detachable loading system for aircraft landing gear wheels provided by an embodiment of the present invention; Figure 2 A schematic diagram of the internal structure of a detachable loading system for aircraft landing gear wheels provided by an embodiment of the invention; Figure 3 for Figure 1 A partial enlarged view of the middle A; Figure 4 A schematic diagram of the structure of a loading mechanism provided by an embodiment of the present invention; Figure 5 for Figure 4 A partial enlarged view of point B in the middle; Figure 6 for Figure 5 A partial enlarged view of the middle C; Figure 7 A cross-sectional view of a mounting base provided by an embodiment of the present invention; Figure 8 A schematic diagram of the cooperation between the power output rod and the thrust plate provided in an embodiment of the present invention; In the figure: 100, frame; 110, guide rail; 120, second hydraulic cylinder; 200, loading mechanism; 210, linear power output unit; 220, power output rod; 221, spherical surface; 300, sliding seat; 310, landing gear mounting portion; 320, sliding block; 330, mounting seat; 331, limiting block; 400, thrust member; 410, thrust plate; 420, limit plate; 401, spherical groove; 500, driving unit; 510, rotating shaft; 520, mounting plate; 530, guide block; 540, driving groove; 541, first guide section; 542, oblique guide section; 543, second guide section; 600. Pressure sensor. DETAILED DESCRIPTION

[0018] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] This embodiment provides a detachable loading system for aircraft landing gear wheels, referring to Figures 1 to 5 As shown, it includes a frame 100, a loading mechanism 200 and a sliding seat 300. The loading mechanism 200 includes a plurality of linear power output units 210 arranged on the frame 100, and each linear power output unit 210 has a power output rod 220 that can extend downward.

[0020] The sliding seat 300 is escalably mounted on the frame 100, and a landing gear mounting portion 310 is disposed on the sliding seat 300. The sliding seat 300 is also provided with a plurality of thrust members 400, and a driving unit 500 is disposed on the frame 100; each thrust member 400 can be driven by the driving unit 500 to switch between an extended state and a retracted state. When each thrust member 400 is in a retracted state, the sliding seat 300 can cross each linear power output unit 210 and descend; when each thrust member 400 is in an extended state, each power output rod 220 can push the thrust member 400 and apply a load to the sliding seat 300.

[0021] In general, the aircraft landing gear wheel detachable loading system of this embodiment is to apply a simulated load to the landing gear system in time after the landing gear system touches the ground in a free fall state. To this end, in this embodiment, a plurality of thrust members 400 capable of switching between an extended state and a retracted state are arranged on a sliding seat 300 on which the landing gear system is installed, and each linear power output unit 210 is arranged on the frame 100.

[0022] When the thrust member 400 is in the retracted state, the thrust member 400 is not blocked by the linear power output units 210, so that the sliding seat 300 and the landing gear system on the sliding seat 300 fall in a free fall state; when the thrust member 400 crosses the linear power output unit 210, the thrust member 400 can be converted to the deployed state, after which the power output rod 220 of each linear power output unit 210 can apply a simulated load to the sliding seat 300, that is, the landing gear system, by pushing the corresponding thrust member 400.

[0023] In this embodiment, the frame 100 is a base for installing other components, which can be set as needed and will not be described in detail here.

[0024] refer to Figure 3 and Figure 4 As shown, the linear power output unit 210 of this embodiment is four hydraulic cylinders fixed on the frame 100. In order to distinguish them from the hydraulic cylinders of the push sliding seat 300 described below, the four hydraulic cylinders are referred to as first hydraulic cylinders in this embodiment, and each power output rod 220 is a telescopic rod of the first hydraulic cylinder. In some embodiments, the linear power output unit 210 can also be two, three or other numbers. In some embodiments, the linear power output unit 210 can also be a cylinder, or a rack driven by a motor and capable of moving in a straight line.

[0025] In this embodiment, reference Figure 2 and Figure 3 As shown, a plurality of guide rails 110 are fixedly provided on the frame 100, and the length direction of each guide rail 110 is parallel to the height direction of the frame 100. A slider 320 capable of sliding on each guide rail 110 is provided on the sliding seat 300, so that the sliding seat 300 can be raised and lowered relative to the frame 100, and when the sliding seat 300 descends relative to the frame 100, the sliding seat 300 and the landing gear system installed on the sliding seat 300 can reach a nearly free fall state.

[0026] refer to Figure 1 and Figure 2 As shown, the landing gear mounting portion 310 of this embodiment is a mounting plate fixed to the bottom end of the sliding seat 300. It should be noted that the mounting method of the landing gear system on the mounting plate can refer to the prior art and will not be described in detail here.

[0027] In this embodiment, Figure 1 and Figure 2 As shown, two hydraulic cylinders are fixedly provided on the frame 100, which are referred to as second hydraulic cylinders 120 in this embodiment. The two second hydraulic cylinders 120 are disposed on two opposite sides of the sliding seat 300, and two support plates are provided on the sliding seat 300. The cylinder rods of the two second hydraulic cylinders 120 can push the two support plates upward to make the sliding seat 300 rise.

[0028] In this embodiment, two brake plates are fixed on the frame, and the two brake plates are disposed on two opposite sides of the sliding seat 300, and brakes are respectively disposed on two opposite sides of the sliding seat 300, and the two brakes can correspondingly hold or release the two brake plates, so as to fix the corresponding sliding seat 300 on the frame 100, or release the sliding seat 300 from the frame 100. It should be noted that the brake can be an existing product, which will not be described in detail here, and the brake is not shown in the drawings of this embodiment because it does not affect understanding. .

[0029] In this embodiment, four thrust members 400 are provided on the sliding seat 300 corresponding to the four first hydraulic cylinders. The working principle of each thrust member 400 is the same, and this embodiment will take one of them as an example to introduce it. Figure 3 and Figure 5 As shown, a mounting seat 330 is fixedly provided on the sliding seat 300 , and the thrust member 400 includes a thrust plate 410 rotatably provided on the mounting seat 330 , and the thrust plate 410 can rotate between an extended state and a retracted state.

[0030] In this embodiment, when the thrust plate 410 rotates to the horizontal direction, it is in an extended state and can withstand the push of the power output rod 220; when the thrust plate 410 rotates to the vertical direction, it is in a retracted state and can avoid the linear power output unit 210, so that the sliding seat 300 can fall without being affected.

[0031] In some embodiments, the thrust plate 410 can also be switched between the deployed state and the retracted state by sliding in the horizontal direction.

[0032] refer to Figure 5 and Figure 6 As shown, the driving unit 500 of this embodiment includes a driving slot 540 provided on the frame 100, and a rotating assembly provided on the thrust member 400. The driving slot 540 includes a first guide section 541, an oblique guide section 542, and a second guide section 543 connected in series from top to bottom. The rotating assembly includes a rotating shaft 510 fixedly provided on the thrust member 400, a mounting plate 520 sleeved on the rotating shaft 510, and a guide block 530 provided on the mounting plate 520 and deviating from the rotating shaft 510 and capable of sliding in the driving slot 540.

[0033] In this embodiment, the first guide section 541 and the second guide section 543 extend in the vertical direction respectively, the first guide section 541 is closer to the sliding seat 300 relative to the second guide section 543, and the oblique guide section 542 extends from the end of the first guide section 541 to the end of the second guide section 543; when the guide block 530 slides from the first guide section 541 through the oblique guide section 542 and into the second guide section 543, the rotating shaft 510 drives the thrust plate 410 to rotate in the direction away from the sliding seat 300.

[0034] In this embodiment, by providing the above-mentioned driving groove 540 and the rotating assembly, when the guide block 530 slides in the first guide section 541, the axis of the guide block 530 and the axis of the rotating shaft 510 are on the same horizontal plane, and at this time, the thrust plate 410 is in a vertical state. When the guide block 530 slides into the second guide section 543, the axis of the guide block 530 and the axis of the rotating shaft 510 are on the same vertical plane, and at this time, the thrust plate 410 rotates 90° to the horizontal with the rotating shaft 510 and is in an unfolded state. The process of the guide block 530 sliding from the second guide section 543 to the first guide section 541 is opposite to that of the guide block 530, which will not be described in detail here.

[0035] In this embodiment, by providing the driving unit 500 of the above structure, on the one hand, no additional power device is required, so that the loading system has a simpler structure; on the other hand, it realizes the rotation of the thrust plate 410 through a mechanical structure, which has higher reliability.

[0036] refer to Figures 4 to 6 As shown, the mounting seat 330 of this embodiment is a square tube, and the bearing member of this embodiment also includes a limit plate 420 which is perpendicular to and fixedly connected to the thrust plate 410 and is assembled into an L shape with the thrust plate 410, and a limit block 331 is fixedly provided on the inner wall at the top of the mounting seat 330; when the thrust plate 410 rotates to the unfolded state, the limit block 331 abuts against the limit plate 420 to limit the further rotation of the thrust plate 410. In this embodiment, by providing the above-mentioned limit plate 420 and limit block 331, the thrust plate 410 can withstand the downward load.

[0037] In this embodiment, reference Figure 8 As shown, each of the bearing plates is provided with a spherical groove 401, and the bottom end surface of each of the power output rods 220 is a spherical surface 221 adapted to the spherical groove 401. When the power output rod 220 pushes the thrust plate 410, the spherical surface 221 abuts against the bottom surface of the spherical groove 401.

[0038] refer to Figure 4 As shown, in this embodiment, a pressure sensor 600 is provided on the power output rod 220, and the pressure sensor 600 is used to detect the pressure of the power output rod 220 on the thrust bearing member 400. In this embodiment, by providing the pressure sensor 600, the load applied by the power output rod 220 to the landing gear system can be monitored, and the load applied by the power output rod 220 to the landing gear system can be adjusted according to the monitoring result. It should be noted that the pressure sensor 600 can adopt an existing product, which will not be described in detail here.

[0039] In this embodiment, a displacement sensor for detecting the displacement of the power output rod 220 is provided on the frame 100 to detect the displacement of the power output rod 220. The displacement sensor is, for example, a grating scale displacement sensor.

[0040] Based on the above overall structure, the working process of the aircraft landing gear wheel detachable loading system of this embodiment is as follows: S1. The cylinder rods of the two second hydraulic cylinders 120 push the support plate on the sliding seat 300 upward to raise the sliding seat 300 to a predetermined height. During this process, the thrust plate 410 rotates from the extended state to the retracted state; S2, the two brakes hold the two brake plates tightly, so that the sliding seat 300 is fixed on the frame 100 and is at a predetermined height; S3, the cylinder rods of the two second hydraulic cylinders 120 are retracted so as not to affect the falling of the sliding seat 300; S4, the two brakes release the corresponding brake plates, and the sliding seat 300 falls in a nearly free-falling state. In this process, after the thrust plate 410 crosses the corresponding first hydraulic cylinder, the thrust plate 410 is driven by the rotating shaft 510 to rotate to the unfolded state; S5. After the thrust plate 410 rotates to the deployed state, the power output rod 220 of the first hydraulic cylinder moves downward. When the power output rod 220 contacts the thrust plate 410 and reaches a predetermined displacement, the power output rod 220 applies a load to the landing gear system by pushing the thrust plate 410. The power output rod 220 can be controlled to apply a predetermined load to the landing gear system through the detection result of the pressure sensor 600.

[0041] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A detachable loading system for aircraft landing gear wheels, characterized in that: include: frame; The loading mechanism comprises a plurality of linear power output units arranged on the frame, each of the linear power output units having a power output rod capable of extending downward; A sliding seat is liftably arranged on the frame, a landing gear mounting portion is provided on the sliding seat, and a plurality of thrust members are also provided on the sliding seat, and a driving unit is provided on the frame; each thrust member can be driven by the driving unit to switch between a deployed state and a retracted state; when each thrust member is in the retracted state, the sliding seat can cross over each linear power output unit and descend; when each thrust member is in the deployed state, each power output rod can push the thrust member and apply a load to the sliding seat.

2. The aircraft landing gear wheel detachable loading system according to claim 1, characterized in that: A mounting seat is fixedly arranged on the sliding seat, and the thrust member comprises a thrust plate rotatably arranged on the mounting seat, and the thrust plate can rotate between the deployed state and the retracted state.

3. The aircraft landing gear wheel detachable loading system according to claim 2, characterized in that: The driving unit includes a driving groove arranged on the frame, and a rotating assembly arranged on the thrust member; the driving groove includes a first guide section, an oblique guide section, and a second guide section connected in series from top to bottom, and the rotating assembly includes a rotating shaft fixed on the thrust plate, a mounting plate sleeved on the rotating shaft, and a guide block arranged on the mounting plate and deviating from the rotating shaft and capable of sliding in the driving groove; when the guide block slides from the first guide section through the oblique guide section and into the second guide section, the rotating shaft can be driven to rotate to rotate the thrust plate from the retracted state to the deployed state.

4. The aircraft landing gear wheel detachable loading system according to claim 2, characterized in that: The thrust member also includes a limiting plate which is fixedly connected to the thrust plate and is assembled into an L shape with the thrust plate, and a limiting block is fixedly provided on the mounting seat. When the thrust plate rotates to the expanded state, the limiting plate rotates to abut against the limiting block.

5. The aircraft landing gear wheel detachable loading system according to claim 2, characterized in that: Each of the thrust plates is provided with a spherical groove, and the bottom end surface of each of the power output rods is a spherical surface adapted to the spherical groove. When the power output rod pushes the thrust plate, the spherical surface abuts against the bottom surface of the spherical groove.

6. The aircraft landing gear wheel detachable loading system according to claim 3, characterized in that: The first guide section and the second guide section extend in the vertical direction respectively, the first guide section is close to the sliding seat relative to the second guide section, and the oblique guide section extends from the end of the first guide section to the end of the second guide section; when the guide block slides from the first guide section through the oblique guide section into the second guide section, the rotating shaft drives the thrust plate to rotate in the direction away from the sliding seat.

7. The aircraft landing gear wheel detachable loading system according to claim 1, characterized in that: A pressure sensor is provided on each of the power output rods, and the pressure sensor is used to detect the pressure of the power output rod on the thrust member.

8. The aircraft landing gear wheel detachable loading system according to claim 1, characterized in that: The frame is provided with a displacement sensor for detecting the displacement of the power output rod.

9. The aircraft landing gear wheel detachable loading system according to claim 1, characterized in that: Two hydraulic cylinders are fixedly arranged on the frame, and the two hydraulic cylinders are arranged on two opposite sides of the sliding seat. Two supporting plates are arranged on the sliding seat, and the cylinder rods of the two hydraulic cylinders can push the two supporting plates upward to make the sliding seat rise.

10. The aircraft landing gear wheel detachable loading system according to claim 1, characterized in that: The frame is fixedly provided with a plurality of guide rails, and the sliding seat is fixedly provided with a sliding block capable of sliding on each of the guide rails.

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