Pneumatic coupling vertical take-off and landing aircraft

Abstract

The utility model relates to the technical field of aircrafts, in particular to a pneumatic coupling vertical take-off and landing aircraft which comprises an aircraft body and a supporting frame arranged at the bottom of the aircraft body, motor bases are fixedly installed on the periphery of the outer side of the aircraft body, and differential motors are arranged at the tops of the motor bases. The output end of the differential motor is fixedly sleeved with a rotor wing, a convenient disassembly and assembly mechanism is arranged between the differential motor and the motor base, a connecting column is fixedly installed at the bottom of the aircraft body, the bottom end of the outer side of the supporting frame is sleeved with a buffer pad, and a connecting cylinder is rotationally arranged at the top end of the supporting frame. According to the pneumatic coupling vertical take-off and landing aircraft, by means of the structural design in the convenient disassembling and assembling mechanism, the purpose of rapidly disassembling or assembling the differential motor is achieved, and the requirements of maintenance personnel are met.

Description

TECHNICAL FIELD

[0001] The utility model relates to an aircraft technical field, concretely is a kind of aerodynamic coupling vertical take-off and landing aircraft. BACKGROUND

[0002] In the use of aircraft, distributed rotors are usually used to realize the vertical take-off and landing of the aircraft.

[0003] The motor in the aircraft of the aerodynamic coupling vertical take-off and landing aircraft currently used is mostly fixed by relying on bolts, which does not have the convenience of disassembly, so when replacing, it needs to consume a lot of time of maintenance personnel, thereby affecting the work efficiency of maintenance personnel, which is not conducive to the rapid completion of maintenance work, and the support frame in the aircraft mostly adopts an integrated design, so when the support frame is damaged, the entire aircraft shell needs to be replaced, thereby increasing the investment of use cost, which is not conducive to subsequent use.

[0004] In view of the above, the utility model solves the problems in the above background technology by designing an aerodynamic coupling vertical take-off and landing aircraft. UTILITY MODEL CONTENTS

[0005] The utility model aims at providing an aerodynamic coupling vertical take-off and landing aircraft to solve the problems in the above background technology.

[0006] To achieve the above object, the utility model provides the following technical scheme:

[0007] An aerodynamic coupling vertical take-off and landing aircraft, comprising an aircraft body and a support frame arranged at the bottom of the aircraft body, a motor seat is fixedly installed around the outside of the aircraft body, a differential motor is arranged at the top of the motor seat, a rotor is fixedly sleeved at the output end of the differential motor, a convenient disassembly and assembly mechanism is arranged between the differential motor and the motor seat, a connecting column is fixedly installed at the bottom of the aircraft body, a buffer pad is sleeved at the bottom end of the outside of the support frame, and a connecting barrel is rotatably arranged at the top end of the support frame.

[0008] The convenient disassembly and assembly mechanism comprises a mounting ring, a guide compression spring and a positioning groove, the mounting ring is fixedly sleeved at the outside surface of the differential motor, a positioning block is fixedly installed at the bottom of the mounting ring, a guide hole is formed in the outside surface of the mounting ring, the guide compression springs are fixedly installed at the left and right sides outside the motor seat respectively, a guide column is arranged on the inner wall of the guide compression spring, the positioning groove is formed in the inner bottom end of the motor seat, a supporting spring is arranged at the inner bottom end of the positioning groove, and a contact ring block is fixedly installed at the top of the supporting spring.

[0009] As a preferred scheme of the utility model, the orientations of the rotors are all vertical directions.

[0010] The buffer pad is made of silicone rubber material.

[0011] As the preferred scheme of the utility model, the connecting column is respectively located at the bottom end corner of the aircraft main body, the outer side surface of the connecting column is provided with external thread, and the inner wall of the connecting barrel is provided with internal thread matched with the external thread.

[0012] As the preferred scheme of the utility model, the outer side surface of the positioning block is embeddedly connected with the inner wall of the positioning groove.

[0013] As the preferred scheme of the utility model, the support spring is annularly equidistantly distributed about the inner wall of the positioning groove.

[0014] As the preferred scheme of the utility model, the opposite ends of the guide column penetrate the outer side surface of the motor base and extend inward, the guide column is inserted with the guide hole, and the vertical section shape of the guide column is T-shaped structure.

[0015] Compared with the prior art, the utility model has the beneficial effects that:

[0016] 1. In the utility model, the convenient dismounting mechanism is used, the positioning block and the positioning groove are embedded, the motor base and the differential motor are quickly positioned, the guide column and the guide hole are contacted under the combination of the wire compression spring and the guide column, the bottom of the positioning block is pre-pressed under the elastic support of the contact ring block of the support spring, the installation ring and the inner wall of the motor base are stably contacted, the differential motor is quickly dismounted or installed, and the needs of maintenance personnel are met.

[0017] 2. In the utility model, the connecting barrel and the connecting column are used, the internal thread and the external thread are combined, the connection between the connecting barrel and the connecting column is realized, the support frame is individually replaced, and the use cost is effectively reduced. DRAWINGS

[0018] Figure 1 It is the whole structure schematic view of the utility model;

[0019] Figure 2 It is the exploded structure schematic view of the connecting barrel and the connecting column of the utility model;

[0020] Figure 3 It is the exploded structure schematic view of the convenient dismounting mechanism of the utility model.

[0021] In the figure: 1, aircraft body; 2, support frame; 201, cushion; 202, connecting cylinder; 3, motor seat; 4, differential motor; 401, rotor; 5, convenient dismounting mechanism; 501, mounting ring; 502, guide compression spring; 503, positioning groove; 504, positioning block; 505, guide hole; 506, guide column; 507, supporting spring; 508, contact ring block; 6, connecting column. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0023] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the related drawings, and several embodiments of the present application are given. However, the present application can be realized in many different forms, and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present application more thorough and comprehensive.

[0024] It should be noted that when an element is referred to as being "fixedly attached" to another element, it can be directly on the other element or there can be intervening elements. When an element is referred to as being "connected" or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements can be present. As used herein the terms "vertical", "horizontal", "left", "right", and the like are used for explanation purposes only.

[0025] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the application herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0026] Embodiments, please see Figures 1-3 The present application provides a technical solution:

[0027] The utility model provides a kind of aerodynamic coupling vertical take-off and landing aircraft, including aircraft body 1 and support frame 2 being arranged at the bottom of aircraft body 1, motor seat 3 is fixedly installed on the outside of aircraft body 1, differential motor 4 is provided at the top of motor seat 3, differential motor 4 is fixedly covered with rotor 401 at the output end, convenient dismounting mechanism 5 is arranged between differential motor 4 and motor seat 3, connecting column 6 is fixedly installed at the bottom of aircraft body 1, buffer pad 201 is covered with at the bottom end of the outside of support frame 2, connecting cylinder 202 is rotationally arranged at the top of support frame 2;

[0028] Specifically, the direction of the rotor 401 is vertical.

[0029] In this embodiment, the differential motor 4 is mainly used to start the rotor 401. With the vertical arrangement of the rotor 401, the vertical take-off and landing of the aircraft can be realized.

[0030] Specifically, the buffer pad 201 is made of silicone rubber material, the connecting column 6 is located at the bottom corner of the aircraft body 1, and the outer surface of the connecting column 6 is provided with external threads, and the inner wall of the connecting cylinder 202 is provided with internal threads matching the external threads.

[0031] In this embodiment, the buffer pad 201 is mainly used to absorb the impact energy at the moment of landing of the aircraft, so as to protect the aircraft. By matching the external threads with the internal threads, the connecting cylinder 202 and the connecting column 6 are tightened, so as to facilitate the replacement of the support frame 2.

[0032] In this embodiment, please refer to Figure 1 and Figure 3 The convenient dismounting mechanism 5 includes a mounting ring 501, guide compression springs 502 and positioning grooves 503. The mounting ring 501 is fixedly covered on the outer surface of the differential motor 4, the bottom of the mounting ring 501 is fixedly installed with positioning blocks 504, the outer surface of the mounting ring 501 is provided with guide holes 505, the guide compression springs 502 are fixedly installed on the left and right sides of the outer side of the motor seat 3, the inner wall of the guide compression spring 502 is provided with guide columns 506, the positioning groove 503 is opened in the inner bottom end of the motor seat 3, the inner bottom end of the positioning groove 503 is provided with supporting springs 507, and the top of the supporting spring 507 is fixedly installed with contact ring blocks 508.

[0033] Specifically, the outer surface of the positioning block 504 is embeddedly connected with the inner wall of the positioning groove 503, the supporting springs 507 are annularly and equidistantly distributed about the inner wall of the positioning groove 503, the opposite ends of the guide columns 506 penetrate through the outer surface of the motor seat 3 and extend inward, the guide columns 506 are inserted with the guide holes 505, and the vertical section shape of the guide column 506 is T-shaped structure.

[0034] In the embodiment, the positioning block 504 is mainly used to contact with the positioning groove 503 to ensure the positioning between the motor base 3 and the differential motor 4, the guide compression spring 502 is mainly used to provide locking force to the guide column 506 to make the guide column 506 tightly contact with the guide hole 505, and the supporting spring 507 is mainly used to elastically support the contact ring block 508 to make the contact ring block 508 form extrusion contact with the positioning block 504, thereby ensuring the stability of the differential motor 4 and facilitating the subsequent disassembly of the differential motor 4.

[0035] The working process of the utility model is as follows: when the pneumatic coupling vertical take-off and landing aircraft is used, the support frame 2 is moved to drive the connecting cylinder 202 to be close to the connecting column 6, the connecting cylinder and the connecting column 6 are tightened through the screw groove and the internal thread, the support frame 2 is installed, subsequent replacement is facilitated, the differential motor 4 is controlled, the differential motor 4 drives the rotor 401 to rotate, the vertical take-off and landing of the aircraft main body 1 is realized under the rotation of the rotor 401, further, when the differential motor 4 needs to be disassembled and maintained, the guide column 506 is stretched and the guide compression spring 502 is stretched by applying a traction force to the guide column 506, until the guide column 506 is separated from the guide hole 505, the supporting spring 507 in the compressed state can apply upward pre-pressure to the bottom of the positioning block 504 through the contact ring block 508, the positioning block 504 and the positioning groove 503 are gradually separated, the differential motor 4 is quickly disassembled, maintenance personnel can perform maintenance work, and the practical effect of the aircraft is improved.

[0036] Although the embodiments of the utility model have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and modifications can be made to the embodiments without departing from the principles and spirits of the utility model, the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. A vertical take-off and landing aircraft with pneumatic coupling, comprising an aircraft body (1) and a support frame (2) arranged at the bottom of the aircraft body (1), characterized in that: The outer side of the aircraft body (1) is fixedly installed with a motor seat (3), the top of the motor seat (3) is provided with a differential motor (4), the output end of the differential motor (4) is fixedly sleeved with a rotor (401), a convenient dismounting mechanism (5) is arranged between the differential motor (4) and the motor seat (3), the bottom of the aircraft body (1) is fixedly installed with a connecting column (6), the outer bottom end of the support frame (2) is sleeved with a buffer pad (201), and the top end of the support frame (2) is rotatably provided with a connecting barrel (202). The convenient dismounting mechanism (5) comprises a mounting ring (501), a guide compression spring (502) and a positioning groove (503), the mounting ring (501) is fixedly sleeved on the outer surface of the differential motor (4), the bottom of the mounting ring (501) is fixedly installed with a positioning block (504), the outer surface of the mounting ring (501) is provided with a guide hole (505), the guide compression springs (502) are fixedly installed on the left and right sides of the outer side of the motor seat (3), respectively, the inner wall of the guide compression spring (502) is provided with a guide column (506), the positioning groove (503) is formed in the inner bottom end of the motor seat (3), and the inner bottom end of the positioning groove (503) is provided with a supporting spring (507), and the top of the supporting spring (507) is fixedly installed with a contact ring block (508).

2. A gas-dynamically coupled vertical take-off and landing aircraft according to claim 1, characterized in that: The direction of the rotor (401) is vertical.

3. A gas-dynamically coupled vertical takeoff and landing aircraft according to claim 1, characterized in that: The buffer pad (201) is made of silicone rubber material.

4. A gas-dynamically coupled vertical takeoff and landing aircraft according to claim 1, characterized in that: The connecting column (6) is located at the bottom end corner of the aircraft body (1), respectively, the outer surface of the connecting column (6) is provided with an external thread, and the inner wall of the connecting barrel (202) is provided with an internal thread matched with the external thread.

5. A gas-dynamically coupled vertical takeoff and landing aircraft according to claim 1, characterized in that: The outer surface of the positioning block (504) is embeddedly connected with the inner wall of the positioning groove (503).

6. A gas-dynamically coupled vertical takeoff and landing aircraft according to claim 1, characterized in that: The supporting spring (507) is annularly and equidistantly distributed about the inner wall of the positioning groove (503).

7. A gas-dynamically coupled vertical takeoff and landing aircraft according to claim 1, characterized in that: The opposite ends of the guide column (506) penetrate through the outer surface of the motor seat (3) and extend inwardly, the guide column (506) is inserted into the guide hole (505), and the vertical section shape of the guide column (506) is in T-shaped structure.

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