CN209921601U

CN209921601U - Solar energy VTOL unmanned aerial vehicle undercarriage

Info

Publication number: CN209921601U
Application number: CN201920756998.6U
Authority: CN
Inventors: 刘德山
Original assignee: Wing Wing Flying (tianjin) Technology Co Ltd
Current assignee: Wing Wing Flying (tianjin) Technology Co Ltd
Priority date: 2019-05-24
Filing date: 2019-05-24
Publication date: 2020-01-10
Anticipated expiration: 2029-05-24

Abstract

The utility model discloses a solar energy vertical take-off and landing unmanned aerial vehicle undercarriage, which comprises an installation box, wherein two ends of the installation box are welded with support plates which are symmetrically arranged along the vertical direction, one side above the installation box is provided with an installation port which is positioned on the side wall of one support plate, the inner wall of the installation port is provided with a motor which is arranged along the horizontal direction, the output end of the motor is connected with a rotating shaft which is arranged along the horizontal direction, the other end of the rotating shaft is rotatably connected with the side wall of the other support plate, the outer ring threads at two ends of the rotating shaft are connected with movable plates which are symmetrically arranged, the top ends of the movable plates are all connected with connecting rods which run through the support plates, one end of each connecting rod extending out of the support plate is welded with a positioning rod with an L-shaped structure, one end, and after falling, can play a rain-proof safeguard function to unmanned aerial vehicle.

Description

Solar energy VTOL unmanned aerial vehicle undercarriage

Technical Field

The utility model relates to an undercarriage technical field especially relates to a solar energy VTOL unmanned aerial vehicle undercarriage.

Background

Unmanned aerial vehicle's undercarriage is the structure that is used for unmanned aerial vehicle to fall to the ground to support, sets up the cushion at the supporting legs position of undercarriage usually, can take off or when descending and play the effect of damping between the ground. In the existing undercarriage, although the stability of fixing between the undercarriage and the landing gear can be guaranteed, the performance and the function of the undercarriage are still to be improved, and therefore the undercarriage of the solar vertical take-off and landing unmanned aerial vehicle is provided.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the shortcoming that exists among the prior art, and the unmanned aerial vehicle undercarriage of a solar energy VTOL.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a solar vertical take-off and landing unmanned aerial vehicle undercarriage comprises an installation box, wherein two ends of the installation box are welded with support plates which are symmetrically arranged along the vertical direction, one side above the installation box is provided with an installation opening which is positioned on one side wall of each support plate, the inner wall of the installation opening is provided with a motor which is horizontally arranged, the output end of the motor is connected with a rotating shaft which is horizontally arranged, the other end of the rotating shaft is rotatably connected with the side wall of the other support plate, the outer rings at the two ends of the rotating shaft are in threaded connection with symmetrically arranged movable plates, the top ends of the movable plates are both connected with connecting rods which penetrate through the support plates, one ends of the connecting rods, which extend out of the support plates, are welded with positioning rods of L-shaped structures, one ends of the positioning rods, which are far away from the connecting rods, are slidably connected with, the bottom inner wall of mounting groove has the elastic expansion device of symmetry setting along vertical direction welding, the top welding of elastic expansion device have along the horizontal direction set up and with mounting groove inner wall sliding connection's backing plate.

Preferably, solar panel is installed at the top of install bin, the internally mounted of install bin has the deposit battery, and deposit battery and solar panel electricity are connected, and the motor is connected with deposit battery electricity.

Preferably, a movable hole in the supporting plate is formed above the mounting opening, and the connecting rod is movably connected with the inner wall of the movable hole.

Preferably, the elastic expansion device comprises an expansion rod and a spring, the expansion rod is welded between the inner wall of the bottom of the mounting groove and the bottom of the backing plate, the spring is connected between the mounting groove and the backing plate, and the spring is sleeved outside the expansion rod.

Preferably, one end of the rotating shaft is provided with a forward thread, the other end of the rotating shaft is provided with a reverse thread, and the movable plate is in threaded connection with the rotating shaft.

Preferably, two the spout has been seted up along length direction to the one side that the baffle kept away from each other, and the one end of locating lever and the inner wall sliding connection of spout.

The utility model has the advantages that: through installing install bin, backup pad, electric solar panel, installing port, motor, pivot, fly leaf, connecting rod, locating lever, baffle, mounting groove, elastic expansion device, backing plate, under the cooperation of each part, can make unmanned aerial vehicle provide a buffer seat frame when descending, after falling moreover, can play a rain-proof safeguard function to unmanned aerial vehicle.

Drawings

Fig. 1 is a schematic view of a front view structure of a landing gear of a solar vertical take-off and landing unmanned aerial vehicle provided by the utility model;

fig. 2 is a schematic top view of the connection of the support plates in the landing gear of the solar vertical take-off and landing unmanned aerial vehicle according to the present invention;

fig. 3 is the utility model provides a structural schematic diagram is looked sideways at to backup pad in solar energy VTOL unmanned aerial vehicle undercarriage.

In the figure: the solar energy-saving device comprises an installation box 1, a support plate 2, a solar panel 3, an installation opening 4, a motor 5, a rotating shaft 6, a movable plate 7, a connecting rod 8, a positioning rod 9, a baffle 10, an installation groove 11, an elastic expansion device 12 and a backing plate 13.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

Referring to fig. 1-3, a solar vertical take-off and landing unmanned aerial vehicle undercarriage comprises an installation box 1, wherein two ends of the installation box 1 are welded with support plates 2 which are symmetrically arranged along a vertical direction, one side above the installation box 1 is provided with an installation port 4 which is positioned on the side wall of one support plate 2, the inner wall of the installation port 4 is provided with a motor 5 which is horizontally arranged, the output end of the motor 5 is connected with a rotating shaft 6 which is horizontally arranged, the other end of the rotating shaft 6 is rotatably connected with the side wall of the other support plate 2, the outer rings at two ends of the rotating shaft 6 are in threaded connection with symmetrically arranged movable plates 7, the top ends of the movable plates 7 are all connected with connecting rods 8 which penetrate through the support plates 2, one ends of the connecting rods 8, which extend out of the support plates 2, are welded with positioning rods 9 which are in L-shaped, two backup pads 2 are close to one side top each other and offer the mounting groove 11 that the symmetry set up, and the welding of the bottom inner wall of mounting groove 11 has the elastic expansion device 12 that the symmetry set up along vertical direction, and the welding of the top of elastic expansion device 12 has the backing plate 13 that sets up along the horizontal direction and with mounting groove 11 inner wall sliding connection.

Solar panel 3 is installed at the top of install bin 1, the internally mounted of install bin 1 has savings battery, and savings battery is connected with solar panel 3 electricity, and motor 5 is connected with savings battery electricity, the movable hole on backup pad 2 has been seted up to installing port 4's top, and the inner wall swing joint of connecting rod 8 and movable hole, elastic expansion device 12 includes the telescopic link, a spring, the telescopic link welding is between 11 bottom inner walls of mounting groove and backing plate 13 bottoms, spring coupling is respectively between mounting groove 11 and backing plate 13, and the spring housing is established in the outside of telescopic link, forward screw thread has been seted up to the one end of pivot 6, reverse screw thread has been seted up to the other end, and

fly leaf

7 and 6 threaded connection of pivot, the spout has been seted up along length direction to one side that two baffles 10 kept away from each other, and the inner.

In this embodiment, during landing, the unmanned aerial vehicle can land on the backing plate 13, so that under the action of the elastic expansion device 12, the impact force during landing can be buffered to meet the requirement, and after landing, the electric energy converted by the solar panel 3 can provide electric energy for the motor 5 through the storage battery, so that the motor 5 can drive the rotating shaft 6 to rotate, and the positive and negative threads on the rotating shaft 6 drive the two movable plates 7 to approach each other, so that the connecting rods 8 approach each other along the movable holes, so that the positioning rods 9 extrude the baffle plates 10, and simultaneously one end of the positioning rods 9 slides along the sliding grooves above the baffle plates 10, so that the two baffle plates 10 are mutually butted, so as to provide a landing gear with rainproof and protection capabilities for the unmanned aerial vehicle after landing, in the utility model, under the cooperation of each component, the unmanned aerial vehicle can provide a buffer seat frame during landing and, can play a rain-proof safeguard function to unmanned aerial vehicle.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a solar energy VTOL unmanned aerial vehicle undercarriage, includes install bin (1), its characterized in that, the both ends of install bin (1) have backup pad (2) that the symmetry set up along the welding of vertical direction, one side of install bin (1) top is seted up and is located one installing port (4) on the backup pad (2) lateral wall, motor (5) that set up along the horizontal direction is installed to the inner wall of installing port (4), the output of motor (5) is connected with pivot (6) that set up along the horizontal direction, and the other end of pivot (6) rotates to be connected in another the lateral wall of backup pad (2), the outer lane threaded connection at pivot (6) both ends has the fly leaf (7) of symmetry setting, the top of fly leaf (7) all is connected with connecting rod (8) that run through backup pad (2), the one end welding that connecting rod (8) stretches out backup pad (2) has locating lever (9) of L type, the one end sliding connection that connecting rod (8) were kept away from in locating lever (9) has baffle (10), and the bottom of baffle (10) articulates in one side at backup pad (2) top, two backup pad (2) are close to one side top each other and set up mounting groove (11) that the symmetry set up, the bottom inner wall of mounting groove (11) has elastic expansion device (12) that the symmetry set up along vertical direction welding, the top welding of elastic expansion device (12) have along the horizontal direction set up and with mounting groove (11) inner wall sliding connection's backing plate (13).

2. The landing gear of the solar VTOL Unmanned Aerial Vehicle (UAV) of claim 1, wherein a solar panel (3) is installed on the top of the installation box (1), a storage battery is installed inside the installation box (1) and is electrically connected with the solar panel (3), and an electric motor (5) is electrically connected with the storage battery.

3. The landing gear of the solar vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, wherein a movable hole in the support plate (2) is formed above the mounting opening (4), and the connecting rod (8) is movably connected with the inner wall of the movable hole.

4. The landing gear of claim 1, wherein the elastic telescopic device (12) comprises a telescopic rod and a spring, the telescopic rod is welded between the inner wall of the bottom of the installation groove (11) and the bottom of the backing plate (13), the spring is connected between the installation groove (11) and the backing plate (13), and the spring is sleeved outside the telescopic rod.

5. The landing gear of the solar vertical take-off and landing unmanned aerial vehicle according to claim 1, wherein one end of the rotating shaft (6) is provided with a forward thread, the other end of the rotating shaft is provided with a reverse thread, and the movable plate (7) is in threaded connection with the rotating shaft (6).

6. The landing gear of the solar vertical take-off and landing unmanned aerial vehicle as claimed in claim 1, wherein one side, away from each other, of the two baffles (10) is provided with a sliding groove along the length direction, and one end of the positioning rod (9) is slidably connected with the inner wall of the sliding groove.