Friction force control buffer device based on piezoelectric driving for aircraft, application and method

Abstract

The invention discloses a piezoelectric driving-based friction force control buffer device for an aircraft, an application and a method, solves the problem that the force of a buffer mechanism in the prior art cannot be accurately adjusted, and has the beneficial effect that the force of the buffer device can be accurately adjusted. According to the specific scheme, the friction force control buffering device based on piezoelectric driving for the aircraft comprises a buffering mechanism, the buffering mechanism comprises a shell, a lead screw nut pair is arranged in the shell, a friction wheel is annularly arranged on a lead screw, a lead screw nut is connected with a sliding push-pull rod, and the sliding push-pull rod penetrates through the shell to be arranged; a lead screw nut in the lead screw nut pair can slide relative to the shell, so that a lead screw rotates to drive the friction wheel to rotate, the force amplification clamp holder is fixed to the shell and penetrates through the shell to clamp the friction wheel, and the piezoelectric actuator is connected with the force amplification clamp holder and connected with the controller. The acceleration sensor is used for obtaining reverse acceleration generated by instant impact force in the landing process.

Description

Technical Field

[0001] The present invention relates to the technical field of landing cushioning, and in particular to a piezoelectric-driven friction force-controlled cushioning device for aircraft, and its application and method. Background Art

[0002] The statements in this section merely provide background information related to the present invention and do not necessarily constitute prior art.

[0003] With the increase in the number of reusable landings and exploration missions of star surface probes, especially the growing demand for lossless landings, higher requirements are placed on the reusable landing cushioning technology and functions of star surface probes.

[0004] Since traditional landing mechanisms do not have functions such as reusability and smooth landing, they cannot adapt to the diversity of future lunar scientific research station construction and exploration missions, and it is difficult to meet the requirements of future heavy tasks such as large-scale multi-point exploration of the star chart and construction of scientific research stations. For this reason, the only way is to launch more probes to carry out star target detection missions, but existing probes or other flight equipment are equipped with landing mechanisms. For example, Chinese patent application CN202010788789.7 discloses a soft landing device with terrain adaptive capability and its landing buffer method, which has the following problems:

[0005] The buffer mechanism of the landing mechanism mainly contacts the outside world through the telescopic mechanism. The landing force of the telescopic mechanism cannot be adjusted. Although it can play a buffering role, it cannot accurately adjust the force during the landing process.

[0006] The mass of the entire buffer mechanism is relatively large;

[0007] In addition, the buffer mechanism has a large instantaneous acceleration after a landing, making it impossible to achieve repeated landings. This requires sending a different lander to the lunar surface each time. At the same time, the buffer mechanism needs to be redesigned for landers with different loads, resulting in a high design cost. Summary of the invention

[0008] In view of the shortcomings of the prior art, the purpose of the present invention is to provide a piezoelectric-driven friction-controlled buffer device for aircraft, which can better solve the problem of lack of corresponding repeatable landing and soft buffer control in the existing satellite probe landing system. It can not only realize soft buffer control, but also complete multiple repeatable landings, improve landing accuracy and work efficiency, and fully meet the requirements of the satellite probe buffer landing process in the aerospace field for repeatable landing mechanism and control method.

[0009] In order to achieve the above object, the present invention is implemented through the following technical solutions:

[0010] A piezoelectrically driven friction force control buffer device for an aircraft, comprising:

[0011] Buffer mechanism: The buffer mechanism includes a housing, a screw nut pair is arranged in the housing, a friction wheel is arranged in the circumferential direction of the screw, the screw nut in the screw nut pair is connected with a sliding push-pull rod, the sliding push-pull rod is arranged through the housing, the screw nut in the screw nut pair can slide relative to the housing, so that the screw rotates and then drives the friction wheel to rotate, the force amplifying clamp is fixed to the housing and the force amplifying clamp passes through the housing to clamp the friction wheel, the piezoelectric driver is connected to the force amplifying clamp, and the piezoelectric driver is connected to the controller;

[0012] The acceleration sensor is used to obtain the reverse acceleration caused by the instantaneous impact force during the landing of the flight equipment. The acceleration sensor is connected to the controller. The controller adjusts the input voltage of the piezoelectric driver according to the information sent by the acceleration sensor to control the output force of the piezoelectric driver, and then adjusts the rotation speed of the screw through the friction force between the force amplifying clamp and the friction wheel to achieve gradual buffering control.

[0013] In the piezoelectrically driven friction force control buffer device for an aircraft as described above, the force amplifying clamp is fixed to the shell, the shell is provided with a hollow portion, and the force amplifying clamp contacts the friction wheel through the hollow portion of the shell.

[0014] As described above, a piezoelectric-driven friction force control buffer device for an aircraft, one end of the piezoelectric driver is detachably connected to the force amplifying clamp, the other end of the piezoelectric driver is arranged through a limit card block, the limit card block is connected to the force amplifying clamp, and the clamping friction block is detachably connected to the force amplifying clamp to clamp the piezoelectric driver.

[0015] As described above, a piezoelectric-driven friction force control buffer device for an aircraft is provided with a preload fine-tuning mechanism at the limit block, which passes through the limit block and is connected to the piezoelectric driver. The preload fine-tuning mechanism limits the axial movement of the piezoelectric driver and adjusts the preload force between the force amplification clamp and the friction wheel.

[0016] As described above, a piezoelectrically driven friction force control buffer device for an aircraft, the force amplifying clamp includes a positioning plate, the positioning plate is used to connect to the shell, the two sides of the positioning plate are respectively connected to the connecting plate by hinges, a clamping plate is set at one end of the connecting plate, the clamping plates on both sides are in contact with the friction wheel to clamp the friction wheel, the piezoelectric driver is supported by the other end of the connecting plate, and the distance between the positioning plate and the clamping plate is greater than the distance between the positioning plate and the piezoelectric driver.

[0017] In the above-mentioned friction force control buffer device based on piezoelectric drive for aircraft, guide optical axes are arranged on both sides of the lead screw nut, the guide optical axes are arranged in the housing, one end of the lead screw nut is connected to the sliding bracket, openings are arranged on both sides of the sliding bracket, sliding bearings are arranged at the openings, the sliding bearings all pass through the corresponding guide optical axes, and the lead screw nut is circumferentially limited by the guide optical axes;

[0018] The lead screw is provided with a first buffer spring in an annular direction, and one end of the first buffer spring close to the friction wheel is fixed.

[0019] A piezoelectrically driven friction force control buffer device for an aircraft as described above, wherein the end of the sliding bracket away from the friction wheel is connected to the sliding push-pull rod, a portion of the sliding push-pull rod is located in the circumferential direction of the lead screw, and one end of the sliding push-pull rod passes through the shell and is hinged to the foot end;

[0020] A second buffer spring is arranged in the annular direction of the part of the sliding push-pull rod located in the shell, and one end of the second buffer spring close to the foot end ball joint is fixed.

[0021] As described above, a piezoelectrically driven friction force control buffer device for an aircraft, the shell includes an end cover and a buffer mechanism body, the friction wheel is located in the buffer mechanism body, the end cover is connected to the buffer mechanism body, the buffer mechanism body is connected to an outer tube, part of the lead screw is located inside the outer tube, the other end of the outer tube away from the buffer mechanism body is connected to the axial positioning end cover, and the guide light axis passes through the axial positioning end cover and is fixedly connected to the axial positioning end cover.

[0022] In a second aspect, the present invention also provides an application of a piezoelectrically driven friction force control buffer device for an aircraft, which is applied to a star map detector.

[0023] In a third aspect, the present invention further provides a working method of a piezoelectrically driven friction force control buffer device for an aircraft, comprising the following contents:

[0024] When the sliding push-pull rod is subjected to axial impact force, it drives the lead screw nut to move linearly relative to the housing. Due to the setting of the lead screw nut nut pair, the lead screw is driven to rotate relative to the housing, and the friction wheel is driven to rotate;

[0025] The acceleration sensor is used to obtain the reverse acceleration caused by the instantaneous impact force during the landing of the flight equipment. The controller adjusts the input voltage of the piezoelectric driver according to the information sent by the acceleration sensor to control the output force of the piezoelectric driver, and then adjusts the rotation speed of the screw through the friction force between the force amplifying clamp and the friction wheel to achieve gradual buffering control.

[0026] The beneficial effects of the present invention are as follows:

[0027] 1) In the present invention, a screw nut pair is arranged inside the buffer mechanism, in which the screw nut is connected to the sliding push-pull rod. When the sliding push-pull rod is impacted, it can drive the screw nut to slide, thereby causing the screw to rotate relative to the housing, and driving the friction wheel to rotate. The friction wheel is in contact with the force amplifying clamp. The controller adjusts the input voltage of the piezoelectric driver according to the information sent by the acceleration sensor to control the output force of the piezoelectric driver, and then adjusts the rotation speed of the screw through the friction force between the force amplifying clamp and the friction wheel, thereby realizing gradual buffering control, so that the entire buffer device can make the landing smoother when applied to the landing mechanism.

[0028] 2) The force amplifying clamp in the present invention has a reasonable structure. The force amplifying clamp is a multi-hinge force amplifying mechanism. Under the vertical force of the piezoelectric driver, it can clamp the friction wheel with symmetrical force and amplify a smaller force. By adjusting the design parameters, the force amplifying clamp can achieve a maximum amplification factor of 20 times.

[0029] 3) In the present invention, a first buffer spring is arranged in the circumferential direction of the lead screw. During the landing buffering process, the first buffer spring is compressed and also plays a role of auxiliary buffering, thereby controlling the buffering process of the control mechanism. A second buffer spring is arranged at the part of the sliding push-pull rod located in the shell. The arrangement of the first buffer spring and the second buffer spring can gradually push the lead screw nut back until it moves to the force balance position of the first buffer spring and the second buffer spring, so that the whole can be reused to become a reusable force-controlled buffer device; in this way, there is no need to add an additional driving mechanism, which facilitates the lightweight design of the entire device.

[0030] 4) The buffer device in the present invention has a reasonable overall structure and a light weight, thereby realizing a lightweight design of the buffer device. Through the setting of the force amplification clamp and the piezoelectric driver, the force amplification principle is realized by mutual cooperation, and the buffer device is controlled under multiple constraints to realize energy transfer and energy consumption quickly and efficiently, thereby achieving smooth and slow landing. The whole device can also automatically complete multiple soft landing tasks.

[0031] 5) The buffer device in the present invention has good operating quality, reliable operation, and high degree of versatility. It can be applied to star probes, and expands the repeated soft landing buffer technology and functions of star probes to meet the future heavy tasks such as star probe exploration and lunar scientific research station construction. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The accompanying drawings in the specification, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0033] Figure 1The present invention is a schematic diagram of a friction force control buffer device based on piezoelectric drive for aircraft according to one or more embodiments of the present invention. Figure 1 .

[0034] Figure 2 The present invention is a schematic diagram of a friction force control buffer device based on piezoelectric drive for aircraft according to one or more embodiments of the present invention. Figure 2 .

[0035] Figure 3 It is an enlarged schematic diagram of the end of a piezoelectrically driven friction force control buffer device for an aircraft according to one or more embodiments of the present invention.

[0036] Figure 4 It is a schematic diagram of the interior of a piezoelectrically driven friction force control buffer device for an aircraft after the outer shell is removed according to one or more embodiments of the present invention.

[0037] Figure 5 It is an internal cross-sectional view of a piezoelectrically driven friction force control buffer device for an aircraft according to one or more embodiments of the present invention.

[0038] Figure 6 It is a schematic structural diagram of a force amplifying clamp in a piezoelectrically driven friction force control buffer device for an aircraft according to one or more embodiments of the present invention.

[0039] Figure 7 It is a schematic diagram of a limit block in a piezoelectrically driven friction force control buffer device for an aircraft according to one or more embodiments of the present invention.

[0040] In the figure: the distances or sizes between parts are exaggerated to show the positions of various parts, and the schematic diagram is for reference only.

[0041] Wherein: 1-end cover, 2-buffer mechanism body, 3-outer tube, 4-guide optical axis, 5-first buffer spring, 6-screw, 7-screw nut, 8-sliding bearing, 9-sliding bracket, 10-axial positioning end cover, 11-sliding guide bearing, 12-bearing fixing ring, 13-sliding push-pull rod, 14-foot end ball hinge, 15-ball hinge positioning bolt, 16-second buffer spring, 17-preload nut, 18-angular contact ball bearing, 19-friction wheel, 20-end cover fastening bolt, 21-limiting ring, 22-preload fine-tuning mechanism, 23-fastening screw, 24-limiting block, 25-friction block fastening bolt, 26-pressing friction block, 27-piezoelectric ceramic driver, 28-force amplification clamp, 29-clamp fastening bolt;

[0042] 2-1. Through groove, 24-1. Recessed part. DETAILED DESCRIPTION

[0043] It should be noted that the following detailed descriptions are illustrative and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used in the present invention have the same meanings as those commonly understood by those skilled in the art to which the present invention belongs.

[0044] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present invention. As used herein, unless otherwise explicitly stated in the present invention, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "include" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof;

[0045] As introduced in the background technology, the force of the buffer mechanism in the prior art cannot be accurately adjusted. In order to solve the above technical problem, the present invention proposes a piezoelectric-driven friction force control buffer device for aircraft.

[0046] Embodiment 1

[0047] In a typical embodiment of the present invention, reference is made to Figure 1 , Figure 2 As shown, a piezoelectrically driven friction force control buffer device for aircraft includes a buffer mechanism: the buffer mechanism includes a shell, a screw nut pair is arranged in the shell, a friction wheel 19 is circumferentially arranged on the screw, a screw nut in the screw nut pair is connected with a sliding push-pull rod 13, the sliding push-pull rod 13 is arranged through the shell, a screw nut 7 in the screw nut pair can slide relative to the shell, so that the screw 6 rotates and then drives the friction wheel 19 to rotate, a force amplifying clamp is fixed to the shell and passes through the shell to clamp the friction wheel 19, a piezoelectric driver 27 is connected with a force amplifying clamp 28, and the piezoelectric driver 27 is connected with a controller;

[0048] The acceleration sensor is installed on the flight equipment. The acceleration sensor is used to obtain the reverse acceleration caused by the instantaneous impact force during the landing of the flight equipment. The acceleration sensor is connected to the controller. The controller adjusts the input voltage of the piezoelectric driver according to the information sent by the acceleration sensor to control the output force of the piezoelectric driver, and then adjusts the rotation speed of the screw through the friction force between the force amplifying clamp and the friction wheel to achieve gradual buffering control.

[0049] Specifically, the housing includes an end cover 1 and a buffer mechanism body 2, a friction wheel 19 is located in the buffer mechanism body, the end cover 1 is connected to the buffer mechanism body 2, the buffer mechanism body 2 is connected to the outer tube 3, a portion of the lead screw 6 is located inside the outer tube 3, the other end of the outer tube 3 away from the buffer mechanism body 2 is connected to the axial positioning end cover 10, and the guide optical axis 4 passes through the axial positioning end cover 10 and is fixedly connected to the axial positioning end cover 10;

[0050] The piezoelectric driver is a piezoelectric ceramic driver 27, and the controller is a PLC controller or other types of controllers. The controller may also be a control center of the flight equipment.

[0051] In this embodiment, the buffer mechanism body 2 and the end cover 1 are installed together by 6 sets of end cover fastening bolts 20 to form a sealed cavity structure; two angular contact ball bearings 18 are respectively installed in the bearing holes inside the buffer mechanism body 2 and the end cover 1, and the screw 6 passes through the two angular contact ball bearings 18 and is fixedly connected to the friction wheel 19 by a key connection. In order to ensure the axial limitation of the friction wheel 19, a limiting ring 21 is installed between the angular contact ball bearing 18 and the friction wheel 19.

[0052] Among them, the lead screw 6 is a large-lead lead screw, the lead screw is located in the outer tube 3 , one end of the outer tube 3 is connected to the axial positioning end cover 10 , and the other end is connected to the buffer mechanism body 2 , and the guide light axis 4 is located inside the outer tube 3 .

[0053] In this embodiment, one end of the guide light shaft 4 is fixedly connected to the buffer mechanism body 2 through a pre-tightening nut 17, two guide light shafts 4 are provided, the two guide light shafts 4 are symmetrically arranged about the lead screw 6, the length of the guide light shaft is shorter than the lead screw 6, the guide light shaft is hollow, and one end of the guide light shaft 4 is provided through the axial positioning end cover 10 and is connected to the axial positioning end cover 10;

[0054] refer to Figure 4 and Figure 5 As shown, the first buffer spring 5 is arranged through the screw 6, that is, the first buffer spring 5 is located in the circumferential direction of the screw 6, one end of the first buffer spring 5 is fixed to the buffer mechanism body 2, and the other end of the first buffer spring is fixed to the screw 6. The first buffer spring 5 is used to protect the internal motion mechanism so that it can be buffered, and the setting of the first buffer spring 5 is beneficial to the return of the screw nut 7.

[0055] It is easy to understand that the lead screw 6 cooperates with the lead screw nut 7, one end of the lead screw nut 7 is fixedly connected to the sliding bracket 9 by a bolt, openings are respectively arranged on both sides of the sliding bracket 9, and sliding bearings 8 are installed at the openings. The two sliding bearings 8 pass through the two guide light shafts 4 respectively, so as to realize the circumferential limit of the guide light shaft 4 on the lead screw nut 7, ensure that the lead screw nut 7 can only slide, and limit the rotational freedom of the lead screw nut 7;

[0056] In addition, the sliding guide bearing 11 is fixed to the axial positioning end cover 10 through the bearing fixing ring 12, and the sliding push-pull rod 13 is set through the sliding guide bearing 11 and the bearing fixing ring 12. One end of the sliding push-pull rod 13 passes through the sliding guide bearing 11 and is fixed to the sliding bracket 9 through a threaded structure, and the other end of the sliding push-pull rod is located on the outside of the axial positioning end cover 10. One end of the sliding push-pull rod 13 is fixedly connected to the foot end ball joint 14 through a ball joint positioning bolt 15 to ensure that when the foot end ball joint 14 is stressed, the sliding push-pull rod 13 can slide linearly along the sliding guide bearing 11.

[0057] The sliding push-pull rod 13 is hollow, the foot end ball joint 14 is an existing structural component used for connection with other components, and the bearing fixing ring 12 is an annular structural component.

[0058] In addition, the second buffer spring 16 is located in the outer tube 3 and is sleeved on the circumferential direction of the lead screw 6 . One end of the second buffer spring 16 is fixed to the inner side of the axial positioning end cover 10 .

[0059] refer to Figure 6 As shown, the material of the force amplifying clamp 28 is aluminum alloy or titanium alloy, and the force amplifying clamp 28 includes a positioning plate 28-3, and the positioning plate 28-3 is provided with a through hole 28-4. The clamp fastening bolt 29 passes through the through hole 28-4 to fix the positioning plate to one side of the buffer mechanism body 2, and the two sides of the positioning plate 28-3 are respectively connected to the connecting plate 28-2 through a bridge hinge, and a clamping plate 28-1 is set at one end of the connecting plate 28-2. The clamping plate 28-1 is an arc-shaped plate, and the clamping plate 28-1 is in contact with the friction wheel. The inner surface of the clamping plate can fit with the outer surface of the friction wheel, and the piezoelectric ceramic driver is supported by the other end of the connecting plate 28-2. The distance between the positioning plate 28-3 and the clamping plate 28-1 is greater than the distance between the positioning plate and the piezoelectric driver, that is, the positioning plate is set close to the piezoelectric driver.

[0060] It should be noted that a clamping friction block 26 is arranged in the middle of the piezoelectric ceramic driver 27. The clamping friction block 26 presses the piezoelectric ceramic driver 27 to the force amplifying clamp 28. The clamping friction block 26 is fixed to the force amplifying clamp 18 by the friction block fastening bolt 25. The limit block 24 is connected to the amplifying clamp 28 by the fastening screw 23. The setting of the limit block 24 prevents the piezoelectric ceramic driver 27 from circumferential rotation. The piezoelectric ceramic driver 27 is connected to the controller, and the action of the piezoelectric ceramic driver 27 is controlled by the controller.

[0061] Specifically, a limit end 28-7 is set at one end of the connecting plate on one side, and a connecting end 28-6 is set at one end of the connecting plate on the other side. The connecting end 28-6 is a semi-ring, and the outer side of the connecting end is fixedly connected to the mounting ring 28-5. One end of the piezoelectric ceramic driver is connected to the limit end 28-7 through a threaded structure, and the other end of the piezoelectric ceramic driver passes through the connecting end 28-6 and the mounting ring 28-5 and is inserted into the limit block 24. The friction block 26 is clamped and connected to the connecting end 28-6 through the friction block fastening bolt 25.

[0062] refer to Figure 7 As shown, the limit block 24 is provided with a recess 24-1, the shape of which is adapted to the piezoelectric ceramic driver, one end of the piezoelectric ceramic driver enters the recess 24-1, the limit block 24 is provided with a threaded hole on the side of the recess, the fastening screw 23 passes through the threaded hole to connect the limit block 24 with the mounting ring 28-5, and the preload fine-tuning mechanism 22 passes through the end of the limit block and contacts the end of the piezoelectric ceramic driver 27.

[0063] It is easy to understand that reference Figure 3 As shown, the buffer mechanism body 2 is provided with a slot 2-1, the width of which is greater than the width of the connecting plate, so that the connecting plate drives the clamping plate 28-1 to extend into the slot of the buffer mechanism body 2 to contact the friction wheel.

[0064] It is easy to understand that the force amplifying clamp 28 clamps the friction wheel 19 through the clamping plates 28 - 1 on both sides, and the preload fine-tuning mechanism 22 is fixedly connected to the limit block 24 to limit the axial movement of the piezoelectric ceramic driver 27. The preload fine-tuning mechanism 22 adjusts the preload force between the force amplifying clamp 28 and the friction wheel 19.

[0065] It should be noted that the clamper fastening bolts 29 and the friction block fastening bolts 25 are both fastening bolts; the compression friction block 26 is provided with a recess, and the shape of the recess matches the shape of the compression friction block 26 .

[0066] The preload fine-tuning mechanism 22 includes an adjusting bolt, which is arranged through the limiting block 24 , and one end of the adjusting bolt can contact the piezoelectric ceramic driver 27 .

[0067] Embodiment 2

[0068] This embodiment provides an application of a piezoelectric-driven friction force control buffer device for an aircraft, which is applied to a star-chart detector.

[0069] Embodiment 3

[0070] This embodiment provides a working method of a piezoelectrically driven friction force control buffer device for an aircraft, including the following contents:

[0071] The preload fine-tuning mechanism 22 is adjusted to ensure that the force amplifying clamp 28 can clamp the friction wheel 19, and the device is in an initial static state. When the buffering operation is required, the piezoelectric ceramic driver 27 starts to supply power;

[0072] When the foot-end ball joint 14 is subjected to an axial impact force, the sliding push-pull rod 13 starts to push the sliding bracket 9 along the sliding guide bearing 11 to drive the lead screw nut 7 to move. Since the sliding bracket 9 is limited circumferentially by the two guide optical axes 4, the lead screw 6 rotates, thereby driving the friction wheel 19 to rotate; the acceleration sensor is used to obtain the reverse acceleration generated by the instantaneous impact force during the landing of the flight equipment. The acceleration sensor feeds back the information it obtains to the controller, adjusts the input voltage of the piezoelectric ceramic driver 27, controls the output force of the piezoelectric ceramic driver 27, and then adjusts the rotation speed of the lead screw 6 through the friction force between the force amplifying clamp 28 and the friction wheel 19, thereby realizing gradual buffering control. During this movement, the first buffer spring 5 is compressed, which also plays a role of auxiliary buffering, thereby controlling the buffering process of the control device and completing a smooth buffering landing task;

[0073] If repeatable landing is required, after the star probe flies away from the surface of the planet, the piezoelectric ceramic driver 27 is powered off because the foot-end ball joint 14 is no longer under pressure, ensuring that the device returns to the initial preload state. At this time, the first buffer spring 5 will gradually push the lead screw nut 7 along the direction of the two guide light axes 4 due to compression, until it moves to the force balance position of the first buffer spring 5 and the second buffer spring 16, completing the reset movement, ensuring that the piezoelectric-controlled buffer device can better improve the repeatable landing smooth buffer control.

[0074] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A piezoelectrically driven friction force control buffer device for an aircraft, characterized in that: include: Buffer mechanism: The buffer mechanism includes a housing, a screw nut pair is arranged in the housing, a friction wheel is arranged in the circumferential direction of the screw, the screw nut in the screw nut pair is connected with a sliding push-pull rod, the sliding push-pull rod is arranged through the housing, the screw nut in the screw nut pair can slide relative to the housing, so that the screw rotates and then drives the friction wheel to rotate, the force amplifying clamp is fixed to the housing and the force amplifying clamp passes through the housing to clamp the friction wheel, the piezoelectric driver is connected to the force amplifying clamp, and the piezoelectric driver is connected to the controller; The acceleration sensor is used to obtain the reverse acceleration caused by the instantaneous impact force during the landing of the flight equipment. The acceleration sensor is connected to the controller. The controller adjusts the input voltage of the piezoelectric driver according to the information sent by the acceleration sensor to control the output force of the piezoelectric driver, and then adjusts the rotation speed of the screw through the friction force between the force amplifying clamp and the friction wheel to achieve gradual buffering control.

2. A piezoelectrically driven friction force control buffer device for aircraft according to claim 1, characterized in that: The force amplifying clamp is fixed to the shell, and the shell is provided with a hollow portion. The force amplifying clamp contacts the friction wheel through the hollow portion of the shell.

3. The piezoelectrically driven friction force control buffer device for aircraft according to claim 1, characterized in that: One end of the piezoelectric driver is detachably connected to the force amplifying clamp, and the other end of the piezoelectric driver passes through a limit block, which is connected to the force amplifying clamp, and a clamping friction block is detachably connected to the force amplifying clamp to clamp the piezoelectric driver.

4. The piezoelectrically driven friction force control buffer device for aircraft according to claim 3, characterized in that: A pre-tightening fine-adjusting mechanism is arranged at the limit block, which passes through the limit block and is connected to the piezoelectric driver. The pre-tightening fine-adjusting mechanism limits the axial movement of the piezoelectric driver and adjusts the pre-tightening force between the force amplifying clamp and the friction wheel.

5. The piezoelectrically driven friction force control buffer device for aircraft according to claim 1, characterized in that: The force amplifying clamp includes a positioning plate, which is used to connect to the shell. The two sides of the positioning plate are respectively connected to the connecting plate through hinges. A clamping plate is set at one end of the connecting plate. The clamping plates on both sides are in contact with the friction wheel to clamp the friction wheel. The piezoelectric driver is supported by the other end of the connecting plate. The distance between the positioning plate and the clamping plate is greater than the distance between the positioning plate and the piezoelectric driver.

6. The piezoelectrically driven friction force control buffer device for aircraft according to claim 1, characterized in that: Guide optical axes are arranged on both sides of the lead screw nut, the guide optical axes are arranged in the housing, one end of the lead screw nut is connected to the sliding bracket, openings are arranged on both sides of the sliding bracket, sliding bearings are arranged at the openings, and the sliding bearings all pass through the corresponding guide optical axes, and the lead screw nut is circumferentially limited by the guide optical axes; The lead screw is provided with a first buffer spring in an annular direction, and one end of the first buffer spring close to the friction wheel is fixed.

7. The piezoelectrically driven friction force control buffer device for aircraft according to claim 6, characterized in that: One end of the sliding bracket away from the friction wheel is connected to the sliding push-pull rod, part of the sliding push-pull rod is located in the circumferential direction of the lead screw, and one end of the sliding push-pull rod passes through the shell and is hinged to the foot end; A second buffer spring is arranged in the annular direction of the part of the sliding push-pull rod located in the shell, and one end of the second buffer spring close to the foot end ball joint is fixed.

8. The piezoelectrically driven friction force control buffer device for aircraft according to claim 6, characterized in that: The shell includes an end cover and a buffer mechanism body, the friction wheel is located in the buffer mechanism body, the end cover is connected to the buffer mechanism body, the buffer mechanism body is connected to the outer tube, part of the lead screw is located inside the outer tube, the other end of the outer tube away from the buffer mechanism body is connected to the axial positioning end cover, and the guide light axis passes through the axial positioning end cover and is fixedly connected to the axial positioning end cover.

9. Application of a piezoelectrically driven friction force control buffer device for aircraft according to any one of claims 1 to 8, characterized in that: Used in star catalog detectors.

10. A working method of a piezoelectrically driven friction force control buffer device for an aircraft according to any one of claims 1 to 8, characterized in that: It includes the following: When the sliding push-pull rod is subjected to axial impact force, it drives the lead screw nut to move linearly relative to the housing. Due to the setting of the lead screw nut nut pair, the lead screw is driven to rotate relative to the housing, and the friction wheel is driven to rotate; The acceleration sensor is used to obtain the reverse acceleration caused by the instantaneous impact force during the landing of the flight equipment. The controller adjusts the input voltage of the piezoelectric driver according to the information sent by the acceleration sensor to control the output force of the piezoelectric driver, and then adjusts the rotation speed of the screw through the friction force between the force amplifying clamp and the friction wheel to achieve gradual buffering control.

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