A vibration correction type propeller aircraft self-gravity positioning landing platform

Abstract

The present application relates to the technical field of aircraft landing platform manufacturing, in particular to a vibration correction type propeller aircraft self-gravity positioning landing platform. It comprises an aircraft and a parking platform. The bottom of the aircraft is provided with a landing positioning part. The parking platform is provided with a guide landing concave part corresponding to the landing positioning part. The concave cavity of the guide landing concave part is an inverted cone with an open upper end. The parking platform is provided with a vibration generator. It also comprises a detection control system. When the aircraft lands on the parking platform and deviates from the preset positioning position, the detection control system sends a start instruction to the vibration generator driver until the aircraft reaches the preset position. It can avoid the aircraft failing to position to the preset position after landing.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft landing platform manufacturing technology, in particular to a vibration correction type propeller aircraft self-gravity positioning landing platform. BACKGROUND

[0002] The existing propeller aircraft self-gravity positioning landing platform, such as the propeller aircraft landing positioning system disclosed in publication No. CN 204568057 U, guides the aircraft to land through a conical receiving surface, automatically positions and parks the aircraft after landing, allows the aircraft to be properly received and placed after landing, and further ensures the safety of the landing. After the aircraft lands at the designated position, it can immediately and automatically perform charging operations, achieving excellent efficiency and convenience of charging operations. In practice, the aircraft may deviate during landing and positioning due to factors such as aircraft deviation and friction, resulting in a failure to connect the charging circuit, especially when multiple charging connectors are provided on the aircraft, which requires higher accuracy for landing and positioning. SUMMARY

[0003] To overcome the shortcomings of the prior art, the present application provides a vibration correction type propeller aircraft self-gravity positioning landing platform that can avoid the problem of the aircraft failing to position to the preset position after landing.

[0004] To achieve the above-mentioned purpose, the present application is implemented by the following technical solutions:

[0005] A vibration correction type propeller aircraft self-gravity positioning landing platform, comprising an aircraft and a parking stand, the bottom of the aircraft being provided with a landing positioning part, and a guide landing concave part being provided on the parking stand corresponding to the landing positioning part, the concave cavity of the guide landing concave part being in the shape of an inverted cone with an open upper end, and a vibration generator being provided on the parking stand; further comprising a detection control system; when the aircraft lands on the parking stand and deviates from the preset positioning position, the detection control system sends a start instruction to the vibration generator driver until the aircraft reaches the preset position.

[0006] Based on the above-mentioned device, the vibration correction type propeller aircraft self-gravity positioning landing platform of the present application generates vibration by using a vibration generator to make the aircraft and the parking stand resonate synchronously. When the aircraft deviates from the preset position, the vibration of the aircraft and the parking stand and the guide landing function of the guide landing concave part play a correction role, thereby improving the positioning accuracy of the aircraft on the parking stand.

[0007] Further, the vibration deviation correction type propeller aircraft self-gravity positioning landing platform, the detection control system comprises at least a pair of first conductive connecting part and second conductive connecting part, the first conductive connecting part and the second conductive connecting part are arranged on the aircraft and the parking platform respectively;When the aircraft lands on the parking platform and is positioned to the preset position, the first conductive connecting part and the second conductive connecting part are electrically connected.As a preferred embodiment of the present application, the detection module of the detection control system can be the connecting connector of the aircraft charging circuit, so that it is not necessary to additionally arrange a sensor.

[0008] Further, the vibration deviation correction type propeller aircraft self-gravity positioning landing platform, the first conductive connecting part and the second conductive connecting part are arranged on the landing positioning part and the guide landing concave part respectively.

[0009] Further, the vibration deviation correction type propeller aircraft self-gravity positioning landing platform, the vibration generator is installed at the bottom of the parking platform.

[0010] Further, the vibration deviation correction type propeller aircraft self-gravity positioning landing platform, the parking platform is in the form of a shell.As a preferred embodiment of the present application, the parking platform is a thin shell part different from a block, which has the advantages of light weight and low manufacturing cost, and the parts corresponding to the parking platform are easy to stack and save space when mass produced.In addition, the shell-shaped parking platform is connected with the vibration generator, which has the advantage of good vibration effect.

[0011] Further, the vibration deviation correction type propeller aircraft self-gravity positioning landing platform, the second conductive connecting part comprises an integrated mounting plate and a contact platform, the contact platform is arranged on the mounting plate, the mounting plate is installed at the bottom of the parking platform corresponding to the bottom end position of the guide landing concave part, and the contact platform extends into the bottom of the concave cavity of the guide landing concave part.

[0012] Further, the vibration deviation correction type propeller aircraft self-gravity positioning landing platform, the mounting plate is provided with a connecting hole.As a preferred embodiment of the present application, the mounting plate is connected to the parking platform through the connecting hole by a screw, and the wire can be fixed on the screw, so that the second conductive connecting part is electrically connected with the external circuit, and thus the connecting hole facilitates the fixation of the mounting plate and the connection of the wire.

[0013] The above technical solutions can achieve the following beneficial effects:

[0014] The application provides a vibration deviation correction type propeller aircraft self-gravity positioning landing platform, which adopts a vibration generator to generate vibration to make the aircraft and the parking platform synchronously resonate, when the aircraft deviates from the preset position, the vibration of the aircraft and the parking platform and the guiding and landing function of the guiding and landing concave part play the deviation correction role, so that the positioning accuracy of the aircraft on the parking platform is improved. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 Fig. 1 is a structural schematic view of a vibration deviation correction type propeller aircraft self-gravity positioning landing platform according to the application;

[0016] Figure 2 Fig. 2 is an exploded schematic view of a vibration deviation correction type propeller aircraft self-gravity positioning landing platform according to the application;

[0017] Figure 3 Fig. 3 is a position schematic view of a first conductive connecting part and a second conductive connecting part;

[0018] Figure 4 Fig. 4 is a structural schematic view of the parking platform in the upward direction;

[0019] Figure 5 Fig. 5 is a structural schematic view of the second conductive connecting part.

[0020] In the drawing: 1-aircraft; 11-landing positioning part; 111-leg; 112-first conductive connecting part;

[0021] 2-parking platform; 21-guiding and landing concave part; 22-second conductive connecting part; 221-mounting plate; 2211-connecting perforation; 222-contact platform; 23-air inlet;

[0022] 3-radiating fan;

[0023] 4-base; 41-supporting rod;

[0024] 5-vibration generator. DETAILED DESCRIPTION

[0025] EMBODIMENT

[0026] COMBINATION Figures 1 to 4The illustrated vibration correction type propeller aircraft self-gravity positioning landing platform includes an aircraft 1 and a parking platform 2, the bottom of the aircraft 1 is provided with a landing positioning part 11, corresponding to the landing positioning part 11, the parking platform 2 is provided with a guide landing concave part 21, the concave cavity of the guide landing concave part 21 is a whole inverted cone with an open upper end, the parking platform 2 is provided with a vibration generator 5; it also includes a detection control system; when the aircraft 1 lands on the parking platform 2 and deviates from the preset positioning position, the detection control system sends a start command to the vibration generator 5 driver until the aircraft 1 reaches the preset position.

[0027] Based on the above device, the vibration correction type propeller aircraft self-gravity positioning landing platform of the application generates vibration by using the vibration generator 5 to make the aircraft 1 and the parking platform 2 synchronous resonance, when the aircraft 1 deviates from the preset position, through the vibration of the aircraft 1 and the parking platform 2 and the guide landing function of the guide landing concave part 21, the deviation is corrected, thereby improving the positioning accuracy of the aircraft 1 on the parking platform 2. Specifically, the vibration generator 5 is a vibration motor. It should be noted that the detection device for detecting whether the aircraft lands on the parking platform can be the existing detection system of the aircraft itself, and the specific detection method can be that the aircraft does not move in the vertical direction during the descent process, that is, it can be judged that the landing is completed.

[0028] In combination Figures 2 to 4 In the embodiment, the detection control system includes at least one pair of first and second conductive connection parts 112 and 22, the first and second conductive connection parts 112 and 22 are respectively arranged on the aircraft 1 and the parking platform 2; when the aircraft 1 lands on the parking platform 2 and is positioned to the preset position, the first and second conductive connection parts 112 and 22 are electrically connected. Specifically, the first and second conductive connection parts 112 and 22 are respectively arranged on the landing positioning part 11 and the guide landing concave part 21. The detection module of the detection control system can be the connection joint of the charging circuit of the aircraft 1, therefore, it is not necessary to additionally arrange a sensor.

[0029] The existing propeller aircraft self-gravity positioning device, such as the propeller aircraft landing positioning system disclosed in the publication number CN 204568057 U, guides the aircraft to land through a conical bearing surface, automatically positions and parks after landing, allows the aircraft to be properly received and placed after landing, and further ensures the safety of the landing. It can immediately and automatically charge after positioning and landing, achieving excellent efficiency and convenience of charging operation. The disadvantage is that the conical chassis is arranged at the bottom of the aircraft and cannot be temporarily landed on a flat surface. In addition, the existing charging contact points at the end of the aircraft are usually multi-point connections. If the charging connection points are multi-point connections, the multiple charging connection points at the end of the unmanned aerial vehicle and the power receptacle at the end of the landing platform are prone to misalignment, so the circumferential positioning of the unmanned aerial vehicle has strict requirements. The above technical solution cannot guarantee the accuracy of the circumferential positioning on the one hand, and the charging connection points are centrally arranged in a multi-point connection and are prone to misalignment, especially when the charging connection points and the power receptacle are connected in the form of male and female cooperation. When misaligned, a certain resistance will be generated, thereby affecting the return of the aircraft to the preset position by gravity.

[0030] To solve the above problems, in combination with Figures 1 to 4 In the present embodiment, the landing positioning part 11 includes a set of downwardly extending legs 111, the number of legs 111 is at least 3, and the bottom end of at least one leg 111 is provided with a first conductive connection part 112 electrically connected with the built-in circuit of the aircraft 1; the guide landing concave part 21 corresponds to a set of legs 111 one by one, and the concave cavity bottom of the guide landing concave part 21 is provided with a second conductive connection part 22.

[0031] Based on the above structure, the principle of the self-gravity positioning landing platform of the vibration correction type propeller aircraft is that the concave cavity of the guide landing recess 21 is inverted conical, wherein the bottom of the guide landing recess 21 corresponds to the tip of the cone, and the second conductive connection part 22 is arranged at the bottom of the guide landing recess 21. When the aircraft 1 lands on the parking platform 2, the bottom of the support leg 111 is in sliding contact with the conical side surface of the corresponding guide landing recess 21. Due to the gravity of the aircraft 1 itself and the conical slope surface of the guide landing recess 21, the support leg 111 will slide to the bottom of the guide landing recess 21 and be positioned to the horizontal position corresponding to the tip of the cone at the bottom of the guide landing recess 21, until the first conductive connection part 112 and the second conductive connection part 22 are electrically connected. The support leg 111 can ensure the stability of the aircraft 1 when temporarily landing on other planes. And it can ensure the accuracy of the circumferential positioning of the aircraft 1. In addition, when the number of first conductive connection parts 112 is greater than 1, the first conductive connection parts 112 are dispersedly arranged at the bottom of each support leg 111, which is different from the first conductive connection parts 112 being concentratedly arranged at the bottom of the aircraft 1 body. It can ensure that each conductive connection part does not dislocate, thereby avoiding the influence of the resistance caused by the dislocation of the conductive connection part on the self-gravity homing of the aircraft to the preset position.

[0032] Specifically, the number of support legs 111 is 4, and each support leg 111 has a first conductive connection part 112 at the bottom. The first conductive connection part 112 is a conductive probe. Correspondingly, the number of guide landing recesses 21 is 4, and each guide landing recess 21 has a second conductive connection part 22 at the bottom. The second conductive connection part 22 is a plug-in interface. The four first conductive connection parts 112 correspond to the positive and negative poles of the charging circuit, the power detection circuit and the on-off control circuit of the aircraft 1 respectively. Specifically, at least one of the charging circuit, the power detection circuit and the on-off control circuit is selected as a detection module of the detection control system. When the aircraft 1 lands on the parking platform 2, the corresponding circuit of the detection module is not in a pass-through state, that is, it is judged that the aircraft 1 deviates from the preset position, and the vibration generator 5 is started until the circuit is in the pass-through state.

[0033] As shown in the combination Figure 4 In the embodiment, the vibration generator 5 is installed at the bottom of the parking platform 2. The parking platform 2 is in the form of a shell. That is, the parking platform 2 is a thin shell part different from a block, which has the advantages of light weight and low manufacturing cost, and when mass production, the parts of the parking platform 2 have the advantage of easy stacking to save space. In addition, the shell-shaped parking platform 2 is connected with the vibration generator 5, which has the advantage of good vibration effect.

[0034] As shown in the combination Figures 1 to 2As shown, in the embodiment, a heat dissipation fan 3 is arranged below the parking platform 2, and an air outlet of the heat dissipation fan 3 is communicated with the parking end of the parking platform 2. The heat dissipation fan 3 has an effect of dissipating heat for the parking platform 2 and the aircraft 1 parked on the parking platform 2. The parking platform 2 is provided with an air inlet 23 extending vertically therethrough, the air inlet 23 is directed to the bottom of the landing position of the aircraft 1, and the air outlet of the heat dissipation fan 3 is communicated with the air inlet 23. Specifically, the heat dissipation fan 3 is a centrifugal blower.

[0035] In the embodiment, a base 4 is arranged below the parking platform 2, the heat dissipation fan 3 is arranged between the parking platform 2 and the base 4, and the parking platform 2 is installed on the base 4. Specifically, the heat dissipation fan 3 is installed on the base 4. In addition, the base 4 is provided with a group of vertical support rods 41, and the parking platform 2 is installed on the support rods 41. The support rods 41 support the parking platform 2 as a whole, so that a cavity for arranging the heat dissipation fan 3 is left between the parking platform 2 and the base 4.

[0036] In combination with Figure 4 and 5 As shown, in the embodiment, the second conductive connection part 22 includes an integrated mounting plate 221 and a contact platform 222, the contact platform 222 is arranged on the mounting plate 221, the mounting plate 221 is installed at the bottom of the parking platform 2 corresponding to the bottom end position of the landing recess 21, and the contact platform 222 extends into the bottom of the recess cavity of the landing recess 21. Specifically, the contact platform 222 is provided with a plug-in interface at an end away from the mounting plate 221. In addition, the mounting plate 221 is provided with a connecting hole 2211. The mounting plate 221 is connected to the parking platform 2 by a screw passing through the connecting hole 2211, and a wire can be fixed on the screw, so that the second conductive connection part 22 is electrically connected with an external circuit, and therefore the connecting hole 2211 facilitates the fixation of the mounting plate 221 and the connection of the wire.

[0037] The technical principles of the present application are described above in combination with specific embodiments, and these descriptions are only for explaining the principles of the present application, and cannot be explained as limitations on the protection scope of the present application in any way. Based on the explanations herein, other specific embodiments of the present application can be conceived by those skilled in the art without creative labor, and these embodiments will fall within the protection scope of the present application.

Claims

1. A self-gravity positioning landing platform for a vibration rectification type propeller aircraft, comprising an aircraft (1) and a parking platform (2), the bottom of the aircraft (1) being provided with a landing positioning portion (11), and corresponding to the landing positioning portion (11), the parking platform (2) being provided with a guide landing concave portion (21), the concave cavity of the guide landing concave portion (21) being in the shape of an inverted cone with an open upper end, characterized in that: The parking stand (2) is provided with a vibration generator (5); further comprising a detection control system; when the aircraft (1) lands on the parking stand (2) and deviates from the preset position, the detection control system sends a start instruction to the vibration generator (5) driver until the aircraft (1) reaches the preset position. The detection control system comprises at least one pair of first conductive connection part (112) and second conductive connection part (22), the first conductive connection part (112) and the second conductive connection part (22) are arranged on the aircraft (1) and the parking stand (2) respectively; when the aircraft (1) lands on the parking stand (2) and is positioned to the preset position, the first conductive connection part (112) and the second conductive connection part (22) are electrically connected; the first conductive connection part (112) and the second conductive connection part (22) are arranged on the landing positioning part (11) and the guide landing concave part (21) respectively; The landing positioning part (11) comprises a group of downwardly extending legs (111), the number of the legs (111) is 4, the bottom end of each leg (111) is provided with a first conductive connection part (112), the first conductive connection part (112) is a conductive probe, correspondingly, the number of the guide landing concave part (21) is 4, the bottom of each guide landing concave part (21) is provided with a second conductive connection part (22), the second conductive connection part (22) is a plug-in interface; the four first conductive connection parts (112) correspond to the positive and negative poles of the charging circuit, the power detection circuit and the switching control circuit of the aircraft (1) respectively; at least one circuit in the charging circuit, the power detection circuit and the switching control circuit is used as a detection module of the detection control system, when the aircraft (1) lands on the parking stand (2), the corresponding circuit of the detection module is not connected, that is, it is judged that the aircraft (1) deviates from the preset position, the vibration generator (5) is started until the circuit is connected.

2. A self-gravitational positioning and landing platform for a vibratory deviation-correction propeller aircraft according to claim 1, characterized in that: The vibration generator (5) is installed at the bottom of the parking stand (2).

3. A self-gravitational positioning landing platform for a vibratory deviation correction type propeller aircraft as claimed in claim 1, characterized in that: The parking stand (2) is in the shape of a shell as a whole.

4. A self-gravitational positioning landing platform for a vibratory deviation correction type propeller aircraft according to claim 1, characterized in that: The second conductive connection part (22) comprises an integrated mounting plate (221) and a contact platform (222), the contact platform (222) is arranged on the mounting plate (221), the mounting plate (221) is installed at the bottom of the parking stand (2) corresponding to the bottom end position of the guide landing concave part (21), and the contact platform (222) extends into the bottom of the concave cavity of the guide landing concave part (21).

5. A self-gravitational positioning landing platform for a vibratory deviation correction type propeller aircraft as claimed in claim 4, characterized in that: The mounting plate (221) is provided with a connecting hole (2211).

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