An aircraft take-off and landing platform

Abstract

The present invention discloses an aircraft take-off and landing platform, including an aircraft and a take-off and landing platform. The aircraft includes a flight body and a landing gear assembly. The take-off and landing platform can fix the aircraft on the platform during turbulence, and can always maintain the adsorption force. When the aircraft is required to be released, multiple adsorption points can be released at the same time. The return accuracy of existing aircraft has tolerances. The landing troughs at three angles of the take-off and landing platform can guide the return deviation with a certain error. The existing mechanical fixed take-off and landing platform is very large in size, and it takes time to release the locking structure, and the simultaneity is extremely poor. The present invention has excellent simultaneity in releasing the aircraft. When taking off and releasing, the release time of multiple fixed positions is more synchronized; the aircraft can even be started first, and then released synchronously, which improves the mission efficiency.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to a take-off and landing platform. Background Art

[0002] The take-off and landing platform is a key auxiliary equipment for aircraft, mainly used in some environments without basic take-off and landing conditions, such as at sea, in the air, and in vehicle driving. Or some scenes that require precise take-off and landing positions in order to achieve automatic charging, automatic execution of tasks, etc. Some of the publicly available take-off and landing platforms with mechanical structure locking are heavy, have high manufacturing costs, and are difficult to manufacture; and because it is difficult for the mechanical structure to achieve the unity of multiple locking points, it is necessary to release the locking mechanism before taking off; there is a certain risk of taking off, and flight accidents may occur. Some existing magnetic take-off and landing platforms do not take into account that the suction force of the magnet cannot resist the large torque and shear force, and the aircraft is very easy to fall off when it is tilted or bumped; some existing magnetic take-off and landing platforms use electromagnets that are demagnetized by power failure; the electromagnets need to be powered separately for a long time, and once the power is insufficient, the aircraft will fall off; most of the existing take-off and landing platforms for vertical take-off and landing aircraft do not take into account the position deviation and heading angle deviation of the return accuracy of existing aircraft, and have not been well handled. Summary of the invention

[0003] The purpose of the present invention is to overcome the above problems and provide a take-off and landing platform.

[0004] In order to achieve the above-mentioned purpose, the method adopted by the present invention is: an aircraft take-off and landing platform, including an aircraft and a take-off and landing platform; the aircraft includes an aircraft body and a landing gear assembly; the landing gear assembly includes a landing gear adapter, a supporting cantilever, a take-off and landing slider, a landing gear adsorption module, and a demagnetization control assembly; the take-off and landing platform includes a platform base, a guiding and positioning assembly, a platform adsorption module, and a floating shock-absorbing module. The aircraft lands above the take-off and landing platform; the landing gear assembly is installed below the aircraft body; the take-off and landing slider is installed in the middle section of the supporting cantilever; one end of the supporting cantilever is fixedly connected to the landing gear adapter; the other end is fixedly connected to the landing gear adsorption module; at least three supporting cantilevers, three take-off and landing sliders, and three landing gear adsorption modules are evenly distributed around the landing gear adapter; and a platform adsorption module is installed on the take-off and landing platform at a position corresponding to the location of the landing gear adsorption module; at least three groups of the guiding and positioning assemblies are fixedly installed on the platform base, and the number of groups is the same as the number of landing gears on the aircraft. The lowering and descending sliders are equal; and are evenly distributed 360 degrees around the center of the take-off and landing platform; the guide positioning component is in the shape of an inverted triangular groove with a larger top opening and a smooth surface, and the take-off and landing slider can slide freely in the groove of the guide positioning component; the adsorption surface of one end of the platform adsorption module correspondingly installed on the platform base passes through the upper surface of the take-off and landing platform, and faces the aircraft and is parallel to the platform upper surface of the take-off and landing platform; the other end of the platform adsorption module is fixedly connected to one end of the floating shock-absorbing module, and the other end of the floating shock-absorbing module is fixedly connected to the lower surface of the take-off and landing platform; the platform adsorption module is controlled to be disconnected by the power supply control component;

[0005] As a preferred embodiment of the present invention, the platform adsorption module is an electromagnet for power-off demagnetization, and its shape is cylindrical; the outermost layer is a metal protective shell, the middle layer is an enameled wire winding coil, and the inner layer is a strong magnetic magnet; power is supplied to the positive and negative poles of the platform adsorption module, and a magnetic field that cancels out the inner magnet can be formed to achieve the purpose of eliminating magnetism; the landing gear adsorption module is an alloy material that is magnetically conductive and electrically conductive and not easily magnetized; the positive pole of the demagnetization control component is connected to a landing gear adsorption module (temporarily referred to as the positive landing gear adsorption module), and the negative pole is connected to another landing gear adsorption module (temporarily referred to as the negative landing gear adsorption module); the positive pole wires of all the platform adsorption modules on the take-off and landing platform are connected to the conductive shell of the platform adsorption module corresponding to the positive landing gear adsorption module; the negative pole wires of all the platform adsorption modules on the take-off and landing platform are connected to the conductive shell of the platform adsorption module corresponding to the negative landing gear adsorption module; through the above connection, after the aircraft is started, the demagnetization control component can power on and demagnetize the platform adsorption module through the contact point between the platform adsorption module and the landing gear adsorption module;

[0006] As a preferred embodiment of the present invention, the floating shock absorbing module is a steel wire shock absorbing ball or a silicone damping shock absorbing ball; the floating shock absorbing module eliminates small displacements and deformations in 6 degrees of freedom; when the platform bumps and vibrates, the floating shock absorbing module reduces the impact force at the connection between the platform adsorption module and the landing gear adsorption module; and eliminates the influence of uneven contact points and uneven force;

[0007] As a preferred embodiment of the present invention, the platform adsorption module and the landing gear adsorption module may be, but are not limited to, one of the following five configurations:

[0008] a. Platform adsorption module: electromagnet with controllable demagnetization; landing gear adsorption module: magnetic conductor;

[0009] b. Platform adsorption module: electromagnet with controllable demagnetization; landing gear adsorption module: magnet;

[0010] c. Platform adsorption module: can control the demagnetization of the electromagnet; landing gear adsorption module: can control the demagnetization of the electromagnet;

[0011] d. Platform adsorption module: magnetic conductor; landing gear adsorption module: electromagnet with controllable demagnetization;

[0012] e. Platform adsorption module: magnet; landing gear adsorption module: electromagnet with controllable demagnetization;

[0013] As a preferred embodiment of the present invention, the degaussing control component can also be installed in the take-off and landing platform to directly control the platform adsorption component; the degaussing control component can be a radio remote control device or a simple power switch;

[0014] As a preferred embodiment of the present invention, the aircraft take-off and landing platform is applied to a vehicle-mounted UAV or a ship-mounted take-off and landing platform;

[0015] As a preferred embodiment of the present invention, the aircraft may be, but is not limited to, a multi-rotor aircraft, a coaxial twin-rotor aircraft, a single-propeller helicopter, a vertical take-off and landing fixed-wing aircraft, and a launch vehicle.

[0016] Beneficial effects:

[0017] Compared with many mechanical take-off and landing platforms, the present invention greatly simplifies the manufacturing and processing difficulties of the platform, reduces the material cost and maintenance difficulty, and the simple structure provides greater safety protection for the aircraft. Compared with many electromagnet-adsorbed take-off and landing platforms, the landing guide assembly of the present invention can allow the flight to return, with a certain limit of heading angle deflection and horizontal position offset, and can accurately land at the take-off position. Compared with many electromagnet take-off and landing platforms, the present invention does not need to maintain power supply, only needs to be demagnetized, and a short time of power supply is required to complete the release of the aircraft; and no power supply and control components are required on the take-off and landing platform, and the aircraft is completely powered and controlled autonomously; compared with most magnetic take-off and landing platforms, the present invention can handle high-frequency and large-scale bumps and shocks to protect the aircraft from falling off. The present invention has excellent simultaneity in releasing the aircraft. When taking off and releasing, the release time of multiple fixed positions is more synchronized; even the aircraft can be started first and then released synchronously, which improves the mission efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall effect of the present invention;

[0019] Figure 2 This is a functional structure diagram of the take-off and landing platform of the present invention;

[0020] Figure 3 It is a schematic diagram of the structure of the present invention;

[0021] Figure 4 This is a schematic diagram of the axonometric view of the landing positioning of the aircraft of the present invention;

[0022] Figure 5 A schematic top view of the landing position of the aircraft of the present invention;

[0023] The components in the figure are 1. aircraft, 2. take-off and landing platform;

[0024] The aircraft 1 comprises: 1a, a flight body, 1b, a landing gear assembly;

[0025] The take-off and landing platform 2 includes: 2a, a platform base, 2b, a guide positioning component, 2c, a platform adsorption module, and 2d, a floating shock absorption module;

[0026] The landing gear assembly 1b includes: 1b1, a supporting cantilever, 1b2, a landing gear adsorption module, 1b3, a take-off and landing slider, 1b4, a landing gear adapter, and 2d, a demagnetization control assembly. DETAILED DESCRIPTION

[0027] The present invention is further explained below in conjunction with the accompanying drawings and specific embodiments. The embodiments are implemented based on the technical solution of the present invention. It should be understood that these embodiments are only used to illustrate the present invention and are not used to limit the scope of the present invention.

[0028] Embodiment 1:

[0029] like Figure 1 An aircraft take-off and landing platform, wherein the aircraft 1 lands on the take-off and landing platform 2, and the landing gear assembly 1b is installed under the aircraft body 1a.

[0030] like Figure 2 , 3 The landing gear assembly 1b is installed under the flight body 1a; the take-off and landing slider 1b3 is installed in the middle section of the supporting cantilever 1b1; one end of the supporting cantilever 1b1 is fixedly connected to the landing gear adapter 1b4; the other end is fixedly connected to the landing gear adsorption module 1b1; three supporting cantilevers 1b1, three take-off and landing sliders 1b3, and three landing gear adsorption modules 1b1 are evenly distributed around the landing gear adapter 1b4; and a platform adsorption module 2c is installed on the take-off and landing platform 2 at the position corresponding to the landing gear adsorption module 1b1; three sets of guiding and positioning components 2b are fixedly installed on the platform base 2a; and are evenly distributed 360 degrees around the center of the take-off and landing platform 2. cloth; the guiding and positioning component 2b is in the shape of an inverted triangular groove with a larger top opening and a smooth surface; the adsorption surface at one end of the platform adsorption module 2c installed on the platform base 2a corresponding to the landing gear adsorption module 1b1 passes through the circular hole on the upper surface of the take-off and landing platform 2, facing the direction of the aircraft 1 and the adsorption surface is parallel to the platform upper surface of the take-off and landing platform 2; the other end of the platform adsorption module 2c is fixedly connected to one end of the floating shock-absorbing module 2d, and the other end of the floating shock-absorbing module 2d is fixedly connected to the bottom of the take-off and landing platform 2; the multi-degree-of-freedom shock-absorbing buffer of the floating shock-absorbing module 2d prevents the aircraft 1 from falling off due to the impact force of excessive vibration exceeding the adsorption force of the adsorption module.

[0031] like Figure 4 As shown, when the aircraft is landing, there is a heading deviation. When the aircraft is displaced horizontally, during the landing process, the take-off and landing slider 1b3 can slide in the groove of the guide positioning component 2b; when the aircraft 1 is landing, if the position deviation and heading deviation do not exceed the groove range of the guide positioning component 2b, the take-off and landing slider 1b3 can slide in the groove to the accurate position so that the landing gear adsorption module 1b1 is aligned with the platform adsorption module 2c;

[0032] The platform adsorption module 2c is an electromagnet for power-off demagnetization, and its shape is cylindrical; the outermost layer is a metal protective shell, the middle layer is an enameled wire winding coil, and the inner layer is a strong magnetic magnet; when the positive and negative poles of the platform adsorption module 2c are energized, a magnetic field that cancels out the inner magnet is formed to eliminate the magnetism of the inner strong magnet; the landing gear adsorption module 1b1 is an alloy material that is magnetically conductive and electrically conductive and not easily magnetized (such as silicon steel); the positive pole of the demagnetization control component 2d is connected to one landing gear adsorption module 1b1 (temporarily referred to as the positive pole landing gear adsorption module 1b1), and the negative pole is connected to another landing gear adsorption module 1b1 (temporarily referred to as the negative pole Landing gear adsorption module 1b1); the positive wires of all platform adsorption modules 2c on the take-off and landing platform 2 are connected to the conductive shell of the platform adsorption module 2c corresponding to the positive landing gear adsorption module 1b1; the negative wires of all platform adsorption modules 2c on the take-off and landing platform 2 are connected to the conductive shell of the platform adsorption module 2c corresponding to the negative landing gear adsorption module 1b1; through the above connection, after the aircraft 1 is started, the demagnetization control component 2d on the landing gear assembly 1b can perform power-on demagnetization control on all platform adsorption modules 2c through the contact point between the platform adsorption module 2c and the landing gear adsorption module 1b1;

[0033] The floating shock absorbing module 2d is a steel wire shock absorbing ball; the floating shock absorbing module 2d eliminates tiny displacements and deformations in 6 degrees of freedom; when the take-off and landing platform 2 is bumpy and vibrated, the floating shock absorbing module 2d absorbs and reduces the impact force at the connection between the platform adsorption module 2c and the landing gear adsorption module 1b1, and eliminates the effects of uneven contact points and uneven force caused by manufacturing tolerances, assembly tolerances, and force deformation of the landing gear assembly 1b.

[0034] The platform adsorption module 2c and the landing gear adsorption module 1b1 can be, but are not limited to, one of the following five configurations:

[0035] 1. Platform adsorption module 2c: controllable demagnetization electromagnet; landing gear adsorption module 1b1: magnetic conductor;

[0036] 2. Platform adsorption module 2c: electromagnet with controllable demagnetization; landing gear adsorption module 1b1: magnet;

[0037] 3. Platform adsorption module 2c: an electromagnet capable of controlling demagnetization; landing gear adsorption module 1b1: an electromagnet capable of controlling demagnetization;

[0038] 4. Platform adsorption module 2c: magnetic conductor; landing gear adsorption module 1b1: electromagnet with controllable demagnetization;

[0039] 5. Platform adsorption module 2c: magnet; landing gear adsorption module 1b1: electromagnet with controllable demagnetization.

[0040] Embodiment 2:

[0041] The present embodiment is different from the first embodiment in that the degaussing control component 2d is installed in the take-off and landing platform 2 to directly control the platform adsorption component; in this case, the degaussing control component 2d can be a radio remote control device or a simple power switch.

[0042] The aircraft 1 take-off and landing platform 2 is applied to a vehicle-mounted UAV or a ship-mounted take-off and landing platform;

[0043] The aircraft 1 may be, but is not limited to, a multi-rotor aircraft, a coaxial twin-rotor aircraft, a single-propeller helicopter, a vertical take-off and landing fixed-wing aircraft, or a launch vehicle.

[0044] The technical means disclosed in the scheme of the present invention are not limited to the technical means disclosed in the above technical means, but also include technical schemes composed of any combination of the above technical features. The above is a specific implementation of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications are also regarded as the protection scope of the present invention.

Claims

1. An aircraft take-off and landing platform, characterized in that: It includes an aircraft and a take-off and landing platform; the aircraft includes a flight body and a landing gear assembly; the landing gear assembly includes a landing gear adapter, a support cantilever, a take-off and landing slider, a landing gear adsorption module, and a demagnetization control assembly; the take-off and landing platform includes a platform base, a guide positioning assembly, a platform adsorption module, and a floating shock absorption module; The aircraft lands above the take-off and landing platform; the landing gear assembly is installed under the aircraft body; the take-off and landing slider is installed in the middle section of the supporting cantilever; one end of the supporting cantilever is fixedly connected to the landing gear adapter; the other end is fixedly connected to the landing gear adsorption module; at least three supporting cantilevers, three take-off and landing sliders, and three landing gear adsorption modules are evenly distributed around the landing gear adapter; and a platform adsorption module is installed at the position corresponding to the landing gear adsorption module on the take-off and landing platform; at least three groups of the guiding and positioning components are fixedly installed on the platform base, and the combination thereof The number of the guide and positioning components is equal to that of the take-off and landing sliders on the aircraft; and they are evenly distributed 360 degrees around the center of the take-off and landing platform; the top opening of the guide and positioning component is in the shape of an inverted triangular groove and has a smooth surface, and the take-off and landing slider slides freely in the groove of the guide and positioning component; the adsorption surface of one end of the platform adsorption module correspondingly installed on the platform base passes through the upper surface of the take-off and landing platform, and faces the aircraft and is parallel to the platform upper surface of the take-off and landing platform; the other end of the platform adsorption module is fixedly connected to one end of the floating shock-absorbing module, and the other end of the floating shock-absorbing module is fixedly connected to the lower surface of the take-off and landing platform; the platform adsorption module is an electric demagnetization module that is powered off. The magnet is cylindrical in shape; the outermost layer is a metal protective shell, the middle layer is an enameled wire winding coil, and the inner layer is a strong magnetic magnet; power is supplied to the positive and negative poles of the platform adsorption module to form a magnetic field that cancels out the inner magnet to achieve the purpose of eliminating magnetism; the landing gear adsorption module is an alloy material that is magnetically conductive and electrically conductive and not easily magnetized; the positive pole of the demagnetization control component is connected to one landing gear adsorption module, and the negative pole is connected to another landing gear adsorption module; the positive pole wires of all the platform adsorption modules on the take-off and landing platform are connected to the conductive shell of the platform adsorption module corresponding to the positive landing gear adsorption module; all the platform adsorption modules on the take-off and landing platform are connected to the conductive shell of the platform adsorption module corresponding to the positive landing gear adsorption module The negative wires of the platform adsorption module are all connected to the conductive shell of the platform adsorption module corresponding to the negative landing gear adsorption module; after the aircraft is started, the demagnetization control component energizes and demagnetizes the platform adsorption module through the contact point between the platform adsorption module and the landing gear adsorption module; the floating shock-absorbing module is a kind of steel wire shock-absorbing ball or silicone damping shock-absorbing ball; the floating shock-absorbing module eliminates small displacements and deformations in 6 degrees of freedom; when the platform is bumpy and vibrated, the floating shock-absorbing module reduces the impact force at the connection between the platform adsorption module and the landing gear adsorption module; and eliminates the influence of uneven contact points and uneven force.

2. The aircraft take-off and landing platform according to claim 1, characterized in that: The platform adsorption module and the The landing gear adsorption module includes one of the following five configurations: Platform adsorption module: electromagnet with controllable demagnetization; landing gear adsorption module: magnetic conductor; Platform adsorption module: electromagnet with controllable demagnetization; landing gear adsorption module: magnet; Platform adsorption module: controllable demagnetization electromagnet; landing gear adsorption module: controllable demagnetization electromagnet; Platform adsorption module: magnetic conductor; landing gear adsorption module: electromagnet with controllable demagnetization; Platform adsorption module: magnet; landing gear adsorption module: electromagnet with controllable demagnetization.

3. The aircraft take-off and landing platform according to claim 1, characterized in that: The degaussing control component is installed in the take-off and landing platform to directly control the platform adsorption component; the degaussing control component is wireless Electrical remote control equipment or power switch.

4. The aircraft take-off and landing platform according to claim 1, characterized in that: The aircraft take-off and landing platform is applied to a vehicle-mounted unmanned aerial vehicle or a ship-mounted take-off and landing platform.

5. The aircraft take-off and landing platform according to claim 1, characterized in that: The aircraft includes a multi-rotor aircraft, a coaxial twin-rotor aircraft, a single-propeller helicopter, a vertical take-off and landing fixed-wing aircraft, and a launch vehicle.

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