CN109533313B

CN109533313B - Many rotors support arm locking mechanical system

Info

Publication number: CN109533313B
Application number: CN201811354859.7A
Authority: CN
Inventors: 罗骏; 苏兵兵; 侯祥民; 王磊; 王子轩; 吴令华
Original assignee: Jiangxi Shenzhou Liuhe Helicopter Co ltd; China Helicopter Research and Development Institute
Current assignee: Jiangxi Shenzhou Liuhe Helicopter Co ltd; China Helicopter Research and Development Institute
Priority date: 2018-11-14
Filing date: 2018-11-14
Publication date: 2020-11-03
Anticipated expiration: 2038-11-14
Also published as: CN109533313A

Abstract

The application provides a concealed unmanned aerial vehicle fast dismounting mechanism, utilize one section to be fixed in inside tubulose support arm fixed knot of fuselage covering to construct the guide support arm or other microscler parts and install rapidly to the exact position, usable its longer support interval provides the high strength for support arm or other microscler parts and supports, and locking mechanical system and bearing structure are all inside the fuselage covering, so can not influence unmanned aerial vehicle appearance design completely, because utilize tubulose support arm fixed knot to construct to lead when the unmanned aerial vehicle support arm is installed, operating personnel can be very light place support arm or other microscler parts exact position and at the internal locking, the speed of support arm or other microscler parts has been guaranteed, convenient installation.

Description

Many rotors support arm locking mechanical system

Technical Field

This application belongs to unmanned aerial vehicle structural design, in particular to many rotor support arm locking mechanical system.

Background

A multi-rotor drone is a special unmanned rotorcraft with three and more upper rotor shafts.

To many rotor unmanned aerial vehicle's structural design, generally adopt following two kinds of structural design modes: one is the machine addition type of composite material section bar, its cost is lower, the apparatus is fixed conveniently, but the structural weight is large, the apparatus is exposed, the protective property is poor, the pneumatic performance is not good; the other type is formed by paving and pasting composite materials, the structural weight is light, equipment is protected by a closed machine body, the protection performance is high, the pneumatic performance is good, but the processing cost is high, and other structural parts of the machine body are difficult to fix due to the fact that the structure is closed.

The root of long parts such as support arms and the like or the switching structures thereof are directly arranged on the skin, and all forces are transmitted into the fuselage through the skin around the parts. The structure is characterized in that parts such as a support arm and the like are fixedly supported on a fuselage skin, the skin is required to bear the force transmitted by structures such as a blade and the like and also bear a huge moment formed by the force amplified by a long structure in the flying process, and the weight of the original structure is greatly increased by the necessary reinforcement of the structure in the practical engineering application because the skin structure is not suitable for transmitting the moment out of the plane of the skin structure; on the other hand, because the skin cannot be used as the dismounting mechanism, the structure is necessarily connected through another dismounting mechanism, which increases the weight of the structure and enables the long-shaped parts such as the support arm to only adopt shapes (mainly circular) which are easy to machine and fix as cross sections, thereby limiting the freedom degree of the structure design.

Disclosure of Invention

It is an object of the present application to provide a multi-rotor arm locking mechanism to solve any of the above problems.

The technical scheme of the application is as follows: the utility model provides a many rotor support arm locking mechanical system, its includes unmanned aerial vehicle support arm, fuselage covering, tubulose support arm fixed knot construct and locking mechanical system, tubulose support arm fixed knot construct pass through the inside rib of fuselage covering with the fuselage covering is fixed, just tubulose support arm fixed knot construct have with unmanned aerial vehicle support arm assorted cross-section configuration is used for leading just the unmanned aerial vehicle support arm, the unmanned aerial vehicle support arm is installed in tubulose support arm fixed knot constructs, locking mechanical system set up in the tip of unmanned aerial vehicle support arm, with tubulose support arm fixed knot constructs the cooperation locking the unmanned aerial vehicle support arm.

In the present application, the tubular arm fixing structure has one of a circular, diamond, or rectangular cross section.

The utility model provides a many rotor support arm locking mechanical system compare and play current combined material and spread shaping fuselage unmanned aerial vehicle, because the length of tubulose support arm fixed knot structure is longer, can stretch into the inside darker position of organism, and its independent fixed knot structure can be comparatively convenient fix the fuselage inside keep away from near the structure of support arm covering, just so make tubulose support arm fixed knot structure, fuselage structure and near covering form a structure that can high-efficient transmission moment together. The fixed mode of support arm root is by the solid structure change of single fulcrum for using the stand pipe both ends to be the simple structure of two fulcrums, under this kind of structure, each structure no longer bears moment, only bears the pulling force, and because the tubular structure is longer, the pulling force that each subassembly received is also lower, and the structure weight of this application can bear the structure of same load on the covering than the snap-on and a lot of lowly. Meanwhile, because the structure of the application does not need to utilize skin to transmit torque, a switching structure with a fixing and supporting function does not need to be designed, only basic support is needed, the shape of the opening of the fuselage is relatively random, and the limitation of the section shape of the support arm is also small.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic view of the mounting and dismounting structure of the support arm of the unmanned aerial vehicle.

Reference numerals:

the unmanned aerial vehicle comprises 1-an unmanned aerial vehicle support arm, 2-a fuselage skin, 3-a tubular support arm fixing structure and 4-a locking mechanism.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In the description of the present application, the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like refer to orientations or positional relationships illustrated in the drawings, which are used for convenience in describing the present application and to simplify the description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the scope of the present application.

The utility model provides an interior concealed quick assembly disassembly structure, it is shown to participate in figure 1, and 1 is unmanned aerial vehicle support arm structure or other microscler parts in the figure, and 2 is the fuselage covering, and 3 is for being fixed in the tubular structure fixed knot who is used for leading and provides the installation on the fuselage, and its one end connects on fuselage covering 2, and the other end connects on the fuselage through a special bearing structure, and 4 are the locking mechanical system who fixes at the support arm. When installing, adjust locking mechanical system 4 on the support arm to open position earlier, insert unmanned aerial vehicle support arm 1 into tubular support arm fixed knot construct 3's opening part, tubular support arm fixed knot construct 3 can lead unmanned aerial vehicle support arm 1 to correct mounted position, until locking mechanical system 4 on the unmanned aerial vehicle support arm 1 exposes from the inboard of fuselage skin, the operator alright lock locking mechanical system in fuselage skin to accomplish the installation.

The utility model provides a concealed unmanned aerial vehicle quick assembly disassembly mechanism utilizes one section to be fixed in the inside tubular support arm fixed knot of fuselage covering to construct the guide support arm or other microscler parts and install rapidly to the exact position, and operating personnel can operate the final locking action of completion in the built-in, and tubular structure utilizes its longer support interval to provide the high strength support for support arm or other microscler parts after the equipment finishes. The utility model provides a locking mechanical system and bearing structure are all inside the fuselage covering, so can not influence unmanned aerial vehicle appearance design completely, have guaranteed that the unmanned aerial vehicle appearance is neat and artistic. This application is owing to utilize tubulose support arm fixed knot to construct to lead when the installation of unmanned aerial vehicle support arm, and operating personnel can be very light place support arm or other microscler parts correct position and in-machine locking, guaranteed quick, the convenient installation of support arm or other microscler parts. This application is owing to utilize the tubulose support arm fixed knot who possesses certain length to support unmanned aerial vehicle support arm or other microscler parts after the installation is accomplished, under the circumstances that guarantees that other structures possess basic strength, higher service torque can be born in this application, has guaranteed unmanned aerial vehicle overall structure's high strength and high rigidity. Because the structure of the application does not need to utilize the skin to transmit the moment, the switching structure with the fixing and supporting functions does not need to be designed, only basic support is needed, the shape of the opening of the fuselage is relatively random, the limitation of the section shape of the fixing structure of the tubular support arm is much smaller, and the fixing structure can be designed into a round shape, a rectangular shape, a rhombic shape or other shapes.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A multi-rotor boom locking mechanism comprising:

the unmanned aerial vehicle comprises an unmanned aerial vehicle support arm (1), a fuselage skin (2), a tubular support arm fixing structure (3) and a locking mechanism (4);

the tubular support arm fixing structure (3) is arranged inside the fuselage skin (2), and the tubular support arm fixing structure (3) is fixed with the fuselage skin (2) through ribs inside the fuselage skin (2), wherein the tubular support arm fixing structure (3) has a cross-section configuration matched with the unmanned aerial vehicle support arm (1) and is used for guiding and supporting the unmanned aerial vehicle support arm (1) to transfer support arm moment;

locking mechanical system (4) set up in the tip of unmanned aerial vehicle support arm (1), work as unmanned aerial vehicle support arm (1) is installed in tubulose support arm fixed knot constructs (3), and when the inboard of locking structure follow fuselage skin on the unmanned aerial vehicle support arm exposes, locking mechanical system (4) with tubulose support arm fixed knot constructs (3) cooperation locking unmanned aerial vehicle support arm (1).

2. The multi-rotor arm locking mechanism according to claim 1, wherein the tubular arm securing structure (3) is one of circular, diamond-shaped, or rectangular in cross-section.