Take-off and landing vibration reduction frame and unmanned aerial vehicle

Abstract

The invention discloses a rising and falling vibration reduction frame which comprises a rising and falling vibration reduction frame assembly, a vibration reduction containing box, a driving mechanism and a central control system. The rising and falling damping frame assembly is used for providing damping and buffering supporting force during rising and falling and comprises symmetrically-arranged supporting transverse rods and supporting inclined vertical rods installed on the top faces of the supporting transverse rods correspondingly. The bottom of each vibration reduction containing box is in an opening shape, the vibration reduction containing boxes are fixed to the bottom faces of the supporting transverse rods respectively, a rolled vibration reduction air bag is arranged in one vibration reduction containing box, the free end of the vibration reduction air bag is connected with a pull rope, and the pull rope extends into the other vibration reduction containing box. The driving mechanism is arranged in the two vibration reduction containing boxes and used for expanding, unfolding, contracting and rolling up the vibration reduction air bag. The central control system comprises a PLC module, a rising and falling environment monitoring module and a rising and falling communication module. The damping device can adapt to various complex rising and falling scenes, and the damping effect is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, in particular to a landing vibration reduction frame and an unmanned aerial vehicle. Background Art

[0002] With the development of drone technology, unmanned aerial vehicles have been widely used in military, civil, scientific research and other fields. However, in the actual use of unmanned aerial vehicles, especially in the take-off and landing stages, there are many challenges. There may be many unfavorable factors during the take-off and landing process, such as uneven ground hardness, wind speed changes, extreme temperatures, etc. These factors may cause impacts on the aircraft and affect its stability and safety.

[0003] The landing and take-off vibration reduction systems of most unmanned aerial vehicles on the market currently have the following shortcomings: Most of the vibration reduction systems use a single vibration reduction method, such as simple springs or rubber pads, which cannot cope with the complex and changing landing and take-off environments. This single vibration reduction method is difficult to provide sufficient buffering effect, especially in extreme environments, the vibration reduction effect is limited. Summary of the invention

[0004] The object of the present invention is to provide a landing vibration reduction frame and an unmanned aerial vehicle to solve the problems raised in the background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a landing vibration reduction frame, comprising: a landing vibration reduction frame assembly, a vibration reduction accommodating box, a driving mechanism, and a central control system.

[0006] The landing vibration damping frame assembly is used to provide a shock-absorbing and buffering support force during landing and comprises symmetrically arranged support cross bars and support inclined vertical bars respectively installed on the top surfaces of the support cross bars;

[0007] The bottom of the vibration-damping accommodating box is open and is fixed to the bottom surface of each supporting cross bar, wherein one of the vibration-damping accommodating boxes has a rolled-up vibration-damping airbag bag, and a drawstring is connected to the free end of the vibration-damping airbag bag, and the drawstring extends to another vibration-damping accommodating box;

[0008] The driving mechanism is arranged in the two vibration-damping accommodating boxes and is used for the expansion and deployment and the contraction and rolling up of the vibration-damping airbag;

[0009] The central control system includes a PLC module, a take-off and landing environment monitoring module and a take-off and landing communication module.

[0010] Preferably, the landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit and a landing wind speed monitoring unit, and the communication module includes a Wi-Fi network unit.

[0011] Preferably, in this solution, the landing support point attribute recognition unit includes a recognition camera, and the recognition camera recognizes whether the attribute of the landing support point is loose or hard;

[0012] The landing temperature monitoring unit includes a temperature sensor, which monitors the temperature of the landing point and transmits the data to the PLC module through the communication module;

[0013] The take-off and landing wind speed monitoring unit includes a wind speed sensor, which monitors the wind speed at the take-off and landing points and transmits the data to the PLC module through the communication module.

[0014] In the preferred embodiment of the present invention, the driving mechanism comprises a reel installed in each vibration-damping accommodating box and a micro motor installed on the outer wall of the diagonally intersecting ends of the two vibration-damping accommodating boxes.

[0015] Preferably, the ends of the two vibration-damping accommodating boxes are also equipped with multi-directional anti-tilt vibration-damping components, which include lifting and falling front and rear anti-tilt vibration-damping parts respectively installed at the bottom of both ends of each vibration-damping accommodating box and lifting and falling side anti-tilt vibration-damping parts symmetrically installed at the lower part of the opposite side surfaces of the two vibration-damping accommodating boxes.

[0016] Preferably, in this solution, one end of the two lifting and landing side anti-tilt vibration damping members away from the vibration damping accommodating box is tilted upward, so that the back side of the lifting and landing side anti-tilt vibration damping members has an arc-shaped curved surface structure.

[0017] Preferably, each of the anti-tilt and vibration damping parts before and after rising and falling is provided with a wave vibration damping portion at one end close to the vibration damping accommodating box, and is provided with an arc-shaped upturned end at one end away from the vibration damping accommodating box.

[0018] Preferably, the bottom surface of each of the vibration-damping accommodating boxes is bonded with a rubber vibration-damping bottom frame, which can provide basic buffering and vibration reduction when rising and falling, and rope holes for the pull rope to pass through are symmetrically provided on opposite sides of the two rubber vibration-damping bottom frames.

[0019] Preferably, the top end of each of the supporting tilting uprights is connected to a hydraulic damping rod, an outer cover of the hydraulic damping rod is provided with a U-shaped mounting plate, second air springs are installed on the inner walls on both sides of the U-shaped mounting plate, and the opposite ends of the two second air springs are fixedly connected to the outer wall of the hydraulic damping rod.

[0020] An unmanned aerial vehicle comprises a bottom box, an upper cover installed on the top of the bottom box, and a landing vibration-damping frame installed on the bottom surface of the bottom box.

[0021] Compared with the prior art, the technical effects and advantages of the present invention are as follows:

[0022] The landing vibration damping frame and the unmanned aerial vehicle form an all-round vibration damping system through a variety of vibration damping structures, including vibration damping airbags, hydraulic damping rods, rubber vibration damping bottom frames, front and rear anti-tilt vibration damping parts for landing and take-off, and side anti-tilt vibration damping parts for landing, which can effectively absorb impact forces from all directions and improve the vibration damping effect.

[0023] The temperature sensor, wind speed sensor and recognition camera monitor the landing environment in real time, and the central control system can automatically adjust the vibration reduction strategy according to different environmental conditions. This intelligent control method makes the vibration reduction system more flexible and can adapt to various complex landing and take-off scenarios. The PLC module makes accurate decisions based on the sensor data and controls the drive mechanism to unfold or retract the vibration reduction airbag to ensure the maximum vibration reduction effect.

[0024] The design of the front and rear anti-tilt dampers and the side anti-tilt dampers effectively prevents the aircraft from tilting forward, backward or rolling over during takeoff and landing, and improves the overall stability. The front and rear anti-tilt dampers are designed with arc-shaped upturned ends and wave damping parts, which provide stability and vibration reduction functions in the front and rear directions during takeoff and landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 It is a structural schematic diagram of the present invention;

[0027] Figure 2 It is a schematic diagram of the installation structure of the bottom box of the present invention;

[0028] Figure 3 It is a schematic structural diagram of the multi-directional anti-tilt and vibration reduction assembly of the present invention;

[0029] Figure 4 It is a schematic structural diagram of the vibration-damping container box of the present invention;

[0030] Figure 5 For the present invention Figure 1 A schematic diagram of the enlarged structure at A in the middle;

[0031] Figure 6 For the present invention Figure 1 A schematic diagram of the enlarged structure at B in the middle;

[0032] Figure 7 It is a schematic diagram of the installation structure of the wind speed sensor of the present invention;

[0033] Figure 8 It is a schematic diagram of the installation structure of the second air spring of the present invention;

[0034] Fig. 9 This is an electrical connection block diagram of the central control system of the present invention.

[0035] Description of reference numerals:

[0036] In the figure: 1. Landing vibration damping frame assembly; 2. Support cross bar; 3. Support tilting vertical bar; 4. Vibration damping accommodating box; 5. Pull rope; 6. Rubber vibration damping bottom frame; 7. Driving mechanism; 8. Vibration damping airbag bag; 9. Bottom box; 10. Upper cover; 11. Temperature sensor; 12. Rotor member; 13. Hydraulic damping rod; 14. Anti-tilt vibration damping member before and after landing; 15. Arc-shaped upturned end; 16. Wave vibration damping part; 17. Landing side anti-tilt vibration damping member; 18. Multi-directional anti-tilt vibration damping assembly; 19. Winding shaft; 20. Bearing; 21. Micro motor; 22. Rope threading hole; 23. Identification camera; 24. Install upper plate; 25. First air spring; 26. Install lower plate; 27. Rubber vibration damping sleeve; 28. U-shaped mounting plate; 29. ​​Second air spring; 30. Pump body component; 31. Wind speed sensor. DETAILED DESCRIPTION

[0037] In the following description, a large number of specific details are provided to provide a more thorough understanding of the present invention. However, it is apparent to those skilled in the art that the present invention can be implemented without one or more of these details. In other examples, in order to avoid confusion with the present invention, some technical features well known in the art are not described.

[0038] Unless otherwise defined, the up, down, left, right, front, back, inside and outside directions involved in this document are based on the up, down, left, right, front, back, inside and outside directions in the figures shown in the present invention, and are explained here together.

[0039] This embodiment provides Figures 1 to 9 The landing vibration damping frame shown includes: a landing vibration damping frame assembly 1, a vibration damping accommodating box 4, a driving mechanism 7, and a central control system.

[0040] In this embodiment, the landing vibration damping frame assembly 1 is used to provide shock-absorbing and buffering support force during landing and includes symmetrically arranged support cross bars 2 and support inclined vertical bars 3 respectively installed on the top surfaces of the support cross bars 2; the support inclined vertical bars 3 serve as vertical support structures, connecting the support cross bars 2 and the vibration damping accommodating box 4, and providing necessary vibration damping effect in the vertical direction during the landing and lifting process.

[0041] In this embodiment, the bottom of the vibration-damping container 4 is open and fixed to the bottom surface of each supporting crossbar 2. One vibration-damping container 4 contains a rolled-up vibration-damping airbag 8, and the free end of the vibration-damping airbag 8 is connected to a drawstring 5, which extends to another vibration-damping container 4. The vibration-damping container 4 serves as a carrier for the vibration-damping airbag 8 and other mechanical components, protects the internal components from the external environment, and provides an installation position for the driving mechanism 7. The vibration-damping airbag 8 provides additional vibration-damping effect by inflating, and can absorb more impact energy during takeoff and landing, reducing the vibration of the fuselage.

[0042] In this embodiment, the driving mechanism 7 is disposed in the two vibration-damping accommodating boxes 4 and is used for the expansion and deployment and the contraction and rolling up of the vibration-damping airbag 8 .

[0043] In this embodiment, the central control system includes a PLC module, a landing environment monitoring module, and a landing communication module. When the landing environment monitoring module detects that the vibration-damping airbag 8 needs to be inflated and expanded during landing, the landing environment monitoring module sends a signal to the PLC module through the landing communication module. After receiving the signal, the PLC module controls the driving mechanism 7 to expand and expand the vibration-damping airbag 8 to support the two containing boxes to reduce vibration and buffer, so that the vibration-damping airbag 8 elastically buffers landing.

[0044] In this embodiment, the landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit and a landing wind speed monitoring unit, and the communication module includes a Wi-Fi network unit.

[0045] In this embodiment, the landing support point attribute recognition unit includes a recognition camera 23, and the recognition camera 23 recognizes whether the attribute of the landing support point is loose or hard;

[0046] In this embodiment, the take-off and landing temperature monitoring unit includes a temperature sensor 11, which monitors the temperature of the take-off and landing points and transmits the data to the PLC module through the communication module;

[0047] In this embodiment, the take-off and landing wind speed monitoring unit includes a wind speed sensor 31, which monitors the wind speed at the take-off and landing points and transmits the data to the PLC module through the communication module. When the recognition camera 23 recognizes that the property of the landing support point is loose soil or concrete, the recognition result data is sent to the PLC module through the Wi-Fi network unit. When the PLC module determines that it is a concrete hard ground after analysis, the PLC module synchronously controls to open the pump body component 30 and the two micro motors 21, so that the two micro motors 21 deploy the vibration-damping airbags 8, and the pump body component 30 inflates and expands the vibration-damping airbags 8, so that the landing and vibration damping frame assembly 1 is lifted and lowered by the inflated and expanded vibration-damping airbags 8 and the hydraulic damping rod 13 and the second air spring 29 for buffering and vibration reduction. When the recognition camera 23 recognizes that the property of the landing and lifting support point is loose soil, the recognition result data is sent to the PLC module through the Wi-Fi network unit. When the PLC module determines that it is a concrete hard ground after analysis, the PLC module does not open the micro motor 21 and the pump body component 30, and the PLC module is closed, but directly performs direct vibration reduction through the front and rear anti-tilt vibration damping parts 14 and the side anti-tilt vibration damping parts 17 of the landing and lifting and the rubber vibration damping bottom frame 6. When the temperature sensor 11 detects extremely high temperature or extremely low temperature and the wind speed sensor 31 detects extreme wind force, the detected data are sent to the PLC module through the Wi-Fi network unit. The PLC module synchronously controls the pump body component 30 and the two micro motors 21 to open the vibration-damping airbag 8. The pump body component 30 inflates and expands the vibration-damping airbag 8, so that the vibration-damping airbag 8, the hydraulic damping rod 13 and the second air spring 29 are used for buffering and vibration reduction when the landing vibration-damping frame assembly 1 is lifted and lowered. When there is no extremely high temperature or extremely low temperature and no extreme wind force, the PLC module is closed, and the vibration reduction is directly performed through the front and rear anti-tilt vibration-damping parts 14 and the side anti-tilt vibration-damping parts 17 of the landing and the rubber vibration-damping bottom frame 6. The pump body component 30 includes an air pump and a vacuum pump, which are used to control the inflation and exhaust of the vibration-damping airbag 8 to achieve its deployment and reeling.

[0048] In this embodiment, the driving mechanism 7 includes a reel 19 rotatably installed in each vibration-damping container 4 and a micro motor 21 installed on the outer wall of the diagonal intersection of the two vibration-damping containers 4. When the vibration-damping airbag 8 needs to be unfolded, one of the micro motors 21 rotates in the reverse direction to release the vibration-damping airbag 8 rolled up by the reel 19, while the other micro motor 21 rotates in the forward direction to pull the vibration-damping airbag 8 through the pull rope 5, thereby completing the unfolding of the vibration-damping airbag 8, and vice versa, the reeling of the vibration-damping airbag 8 is completed; both ends of the two reel shafts 19 are connected to the vibration-damping container 4 through bearings 20. A pump body component 30 is provided in the inner cavity of the vibration-damping container 4 for rolling up the vibration-damping airbag 8, and the pump body component 30 includes an air pump for inflating and unfolding the vibration-damping airbag 8 and a vacuum pump for evacuating and rolling up the vibration-damping airbag 8.

[0049] In this embodiment, a multi-directional anti-tilt vibration reduction assembly 18 is also installed at the ends of the two vibration reduction accommodating boxes 4. The multi-directional anti-tilt vibration reduction assembly 18 includes a front and rear anti-tilt vibration reduction member 14 installed at the bottom of each end of each vibration reduction accommodating box 4 and a side anti-tilt vibration reduction member 17 installed symmetrically at the lower part of the opposite side of the two vibration reduction accommodating boxes 4. Both ends of each support cross bar 2 are sleeved with a rubber vibration reduction sleeve 27, which is pressed down and abutted against the top surface of the vibration reduction accommodating box 4. The vibration reduction accommodating box 4 is connected to the support cross bar 2 by screws. The multi-directional anti-tilt vibration reduction assembly 18 combines the functions of multiple anti-tilt vibration reduction members to provide a full range of anti-tilt vibration reduction effects.

[0050] In this embodiment, the ends of the two lifting and landing side anti-tilt vibration damping members 17 away from the vibration damping accommodating box 4 are tilted upward, so that the back of the lifting and landing side anti-tilt vibration damping members 17 is an arc-shaped curved surface structure. The lifting and landing side anti-tilt vibration damping members 17 can provide lateral buffering and vibration damping support for the supporting cross bar 2 and the vibration damping accommodating box 4 during lifting and landing.

[0051] In this embodiment, each anti-tilt damper 14 before and after lifting and falling is provided with a wave damping portion 16 at one end close to the damping accommodating box 4, and each anti-tilt damper 14 before and after lifting and falling is provided with an arc-shaped upturned end portion 15 at one end away from the damping accommodating box 4. When the supporting cross bar 2 is lifted and lowered, the arc-shaped upturned end portion 15 of the anti-tilt damper 14 before and after lifting and falling can not only prevent the problem of forward or backward tilting, but also play a buffering and vibration reduction effect through the elastic resin material of the anti-tilt damper 14 before and after lifting and falling. In addition, the wave-shaped wave damping portion 16 is in line contact with the supporting object at the lifting and landing point during lifting and falling, which can avoid the large vibration amplitude caused by surface contact and the problem of unstable support caused by point contact. The anti-tilt damper 14 before and after lifting and falling is designed with an arc-shaped upturned end portion 15 and a wave damping portion 16, which provides stability and vibration reduction function in the front and rear directions during lifting and falling. The arc-shaped upturned end portion 15 helps to reduce the risk of forward or backward tilting during lifting and falling, and increases stability. The wave vibration reduction part 16 is in linear contact with the ground during landing, which reduces the vibration amplitude and enhances the vibration reduction effect. The landing side anti-tilt vibration reduction part 17 provides lateral stability during landing to prevent rollover.

[0052] In this embodiment, a rubber vibration-damping bottom frame 6 is bonded to the bottom surface of each vibration-damping housing box 4. The rubber vibration-damping bottom frame 6 can provide basic buffering and vibration reduction when taking off and landing. The two rubber vibration-damping bottom frames 6 are symmetrically provided with rope holes 22 for the pull rope 5 to pass through on opposite sides. The rubber vibration-damping bottom frame 6 is located at the bottom of the vibration-damping housing box 4, providing preliminary ground contact buffering and reducing damage caused by direct impact.

[0053] In this embodiment, the top of each supporting tilting upright pole 3 is connected to a hydraulic damping rod 13, and the outer cover of the hydraulic damping rod 13 is provided with a U-shaped mounting plate 28. The inner walls on both sides of the U-shaped mounting plate 28 are both installed with second air springs 29, and the opposite ends of the two second air springs 29 are fixedly connected to the outer wall of the hydraulic damping rod 13. The hydraulic damping rod 13 and the supporting tilting upright pole 3 are provided with lateral movement buffering and shock absorption, while the hydraulic damping rod 13 is provided with longitudinal buffering and shock absorption of the supporting tilting upright pole 3. The hydraulic damping rod 13 provides the damping effect required for vibration reduction, absorbs the impact energy through the flow of liquid, and reduces the vibration of the fuselage. The second air spring 29 provides a lateral vibration reduction effect, and is used in conjunction with the hydraulic damping rod 13 to improve the overall vibration reduction performance of the system.

[0054] An unmanned aerial vehicle, comprising a bottom box 9, an upper cover 10 mounted on the top of the bottom box 9, and a landing vibration damping frame mounted on the bottom surface of the bottom box 9, a hydraulic damping rod 13 of the landing vibration damping frame being hinged to the bottom surface of the bottom box 9, a U-shaped mounting plate 28 being fixed to the bottom surface of the bottom box 9, an identification camera 23 being mounted on the outer wall of the bottom box 9 in the forward direction, a temperature sensor 11 and a wind speed sensor 31 being mounted on the top surface of the upper cover 10 through a vibration damping connector; the vibration damping connector comprising a mounting lower plate 26 embedded in the upper cover 10, a first air spring 25 mounted on the top surface of the mounting lower plate 26, and a mounting upper plate 24 mounted on the top of the first air spring 25, the temperature sensor 11 and the wind speed sensor 31 being mounted on the top surface of the mounting upper plate 24; the first air spring 25 provides an elastic support to assist the vibration damping effect. Four rotor members 12 are symmetrically mounted on the periphery of the bottom box 9.

[0055] Working principle:

[0056] The landing vibration damping frame and the unmanned aerial vehicle, the PLC module is used to receive and process information from the environmental monitoring module, and control the action of the actuator accordingly. The landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit, and a landing wind speed monitoring unit. The landing communication module is responsible for transmitting data between the environmental monitoring module and the PLC module, including a Wi-Fi network unit.

[0057] The recognition camera 23 takes photos or videos of the landing area, and identifies the properties of the support points (such as hard ground or loose soil) through image processing analysis. The temperature sensor 11 detects the temperature of the landing area, and the wind speed sensor 31 detects the wind speed in the landing area. The temperature sensor 11 and the wind speed sensor 31 continuously monitor the temperature and wind speed conditions of the landing area, and the recognition camera 23 identifies the properties of the landing support points (such as hard ground or loose soil). The monitored data is transmitted to the PLC module in the central control system through the Wi-Fi network unit. The PLC module receives data from the landing environment monitoring module and analyzes and judges it. Based on the analysis results, the PLC module decides whether it is necessary to deploy the vibration-damping airbag 8 and what vibration-damping measures to take.

[0058] The recognition camera 23 takes photos or videos of the landing area. The collected images are preprocessed, including operations such as scaling, cropping, graying, and noise removal to improve image quality and facilitate subsequent processing. Useful features are extracted from the image using image processing algorithms (such as edge detection, texture analysis, color space conversion, etc.). These features can be color distribution, texture pattern, or other features related to ground properties. The extracted features are compared with known standard feature libraries to find the most similar features. These standard feature libraries can be pre-trained models that contain features of different ground types (such as hard ground, grass, sand, etc.). The extracted features are classified using machine learning algorithms (such as support vector machines SVM, neural networks, deep learning, etc.) to determine the type of ground. For example, if the feature matching results show that the ground has a high hardness and flatness, the system will identify it as a hard ground; if the features show that the ground is relatively soft or uneven, it is identified as loose soil. The recognition results are sent to the PLC module through the Wi-Fi network unit for subsequent vibration reduction strategy decisions.

[0059] If the take-off and landing point is concrete (hard ground), the shock-absorbing airbag 8 needs to be deployed, and the PLC module controls the micro motor 21 to start, releases the shock-absorbing airbag 8 through the reel 19, and deploys it through the pull rope 5, and the pump body component 30 starts to inflate the shock-absorbing airbag 8 to make it expand and deploy to provide shock-absorbing buffering. At the same time, the hydraulic damping rod 13 provides a lateral shock-absorbing effect with the assistance of the second air spring 29. The hydraulic damping rod 13 itself also provides a longitudinal shock-absorbing function to absorb impact energy through internal fluid movement.

[0060] If the landing site is loose soil, there is no need to open the airbag. The PLC module controls the micro motor 21 to reverse, roll up the shock-absorbing airbag 8 through the reel 19, and evacuate it using the vacuum pump in the pump body part 30. The anti-tilt damper 14 provides vibration reduction and support in the front and rear directions through its wave damping part 16 and the arc-shaped upturned end 15. The arc-shaped surface design of the side anti-tilt damper 17 helps to provide vibration reduction effect on the side to prevent the aircraft from rolling over. The rubber damping bottom frame 6 is the bottom damping device, providing basic buffering effect to reduce direct impact during landing and takeoff. The rubber damping sleeve 27 is sleeved on the support crossbar 2 to provide additional vibration reduction effect. The hydraulic damping rod 13 provides lateral vibration reduction effect with the assistance of the second air spring 29. The hydraulic damping rod 13 itself also provides longitudinal vibration reduction function, absorbing impact energy through internal fluid movement.

[0061] The supporting cross bar 2 and the supporting inclined vertical bar 3 together constitute the skeleton of the lifting and lowering vibration damping frame assembly 1, providing a stable structural support. The vibration damping accommodating box 4 is connected to the supporting cross bar 2 by screws to ensure a firm connection between the various components. The hydraulic damping rod 13 is hinged to the bottom surface of the bottom box 9, and the U-shaped mounting plate 28 is fixed to the bottom surface of the bottom box 9. The identification camera 23 is installed on the outer wall of the bottom box 9 in the forward direction. The temperature sensor 11 and the wind speed sensor 31 are installed on the top surface of the upper cover 10 through the vibration damping connector.

[0062] The central control system comprehensively manages all vibration reduction operations to ensure that the aircraft can land or take off smoothly and safely during the entire take-off and landing process.

[0063] It should be noted that, in this article, relational terms such as one and two are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions. The sentence "includes an element defined by ... does not exclude the existence of other identical elements in the process, method, article or device including the element".

[0064] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A landing vibration reduction frame, characterized in that: include: A landing vibration damping frame assembly (1) is used to provide a shock-absorbing and buffering support force during landing and comprises symmetrically arranged support cross bars (2) and support inclined vertical bars (3) respectively installed on the top surfaces of the support cross bars (2); A vibration-damping accommodating box (4) having an open bottom and fixed to the bottom surface of each supporting crossbar (2), wherein one of the vibration-damping accommodating boxes (4) has a rolled-up vibration-damping airbag (8), a free end of the vibration-damping airbag (8) is connected to a drawstring (5), and the drawstring (5) extends to another vibration-damping accommodating box (4); A driving mechanism (7) is arranged in the two vibration-damping accommodating boxes (4) and is used for expanding and unfolding and shrinking and rolling up the vibration-damping airbag (8); The central control system includes a PLC module, a take-off and landing environment monitoring module, and a take-off and landing communication module.

2. The landing vibration damping frame according to claim 1, characterized in that: The landing environment monitoring module includes a landing support point attribute identification unit, a landing temperature monitoring unit and a landing wind speed monitoring unit, and the communication module includes a Wi-Fi network unit.

3. The landing vibration damping frame according to claim 2, characterized in that: The landing support point attribute recognition unit comprises a recognition camera (23), and the recognition camera (23) recognizes whether the attribute of the landing support point is loose or hard; The landing temperature monitoring unit comprises a temperature sensor (11), which monitors the temperature of the landing point and transmits the data to the PLC module through the communication module; The take-off and landing wind speed monitoring unit comprises a wind speed sensor (31), and the wind speed sensor (31) monitors the wind speed at the take-off and landing points and transmits the data to the PLC module through the communication module.

4. The landing vibration damping frame according to claim 3, characterized in that: The driving mechanism (7) comprises a reel (19) rotatably mounted in each vibration-damping accommodating box (4) and a micro motor (21) mounted on the outer walls of the diagonally intersecting ends of the two vibration-damping accommodating boxes (4).

5. The landing vibration reduction frame according to claim 4, characterized in that: The ends of the two vibration-damping accommodating boxes (4) are also provided with a multi-directional anti-tilt vibration-damping assembly (18), which comprises a lifting and lowering front and rear anti-tilt vibration-damping member (14) respectively installed at the bottom of both ends of each vibration-damping accommodating box (4) and a lifting and lowering side anti-tilt vibration-damping member (17) symmetrically installed at the lower part of the opposite side surfaces of the two vibration-damping accommodating boxes (4).

6. The landing vibration damping frame according to claim 5, characterized in that: One end of the two lifting and landing side anti-tilting vibration damping members (17) away from the vibration damping accommodating box (4) is tilted upward, so that the back surface of the lifting and landing side anti-tilting vibration damping members (17) is an arc-shaped curved surface structure.

7. The landing vibration damping frame according to claim 6, characterized in that: Each of the front and rear anti-tilt vibration damping members (14) is provided with a wave vibration damping portion (16) at one end close to the vibration damping accommodating box (4), and each of the front and rear anti-tilt vibration damping members (14) is provided with an arc-shaped upwardly tilted end portion (15) at one end away from the vibration damping accommodating box (4).

8. The landing vibration damping frame according to claim 7, characterized in that: A rubber vibration-damping bottom frame (6) is bonded to the bottom surface of each vibration-damping housing box (4). The rubber vibration-damping bottom frame (6) can provide basic buffering and vibration reduction when the vehicle is rising or falling. Rope holes (22) for the pull rope (5) to pass through are symmetrically provided on opposite sides of the two rubber vibration-damping bottom frames (6).

9. The landing vibration damping frame according to claim 8, characterized in that: The top end of each supporting tilting upright rod (3) is connected to a hydraulic damping rod (13), the outer cover of the hydraulic damping rod (13) is provided with a U-shaped mounting plate (28), the inner walls on both sides of the U-shaped mounting plate (28) are both installed with second air springs (29), and the opposite ends of the two second air springs (29) are fixedly connected to the outer wall of the hydraulic damping rod (13).

10. An unmanned aerial vehicle, characterized in that: The unmanned aerial vehicle comprises a bottom box (9), an upper cover (10) mounted on the top of the bottom box (9), and a landing vibration reduction frame mounted on the bottom surface of the bottom box (9) and according to any one of claims 1 to 9.

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