CN113859575A - Composite wing/rotor wing unmanned aerial vehicle propeller safety locking device and locking method - Google Patents

Abstract

The invention discloses a composite wing/rotor wing unmanned aerial vehicle propeller safety locking device and a locking method, and particularly relates to the field of aviation design. Including transporting the fork and installing the locking mechanism on compound wing rotor unmanned aerial vehicle rotor roof beam, transport the fork including the wood fork that is "Y" font and install the mounting panel on the wood fork, locking mechanism includes U type frame, locating part and electric control lock, U type frame screw connection is on the mounting panel, the one end and the U type frame of locating part rotate to be connected, the other end and the U type frame of locating part peg graft jointly and have the bolt, be equipped with the stay cord on the bolt, electric control lock is connected with flight controller electricity, electric control lock sets up the one side relative with the bolt on U type frame, the lock core of electric control lock and the one end of locating part block mutually block and, compound wing rotor unmanned aerial vehicle's rotor roof beam is located between spacing and the U type frame. By adopting the technical scheme of the invention, the problem that the propeller is started by mistake due to program error before the unmanned aerial vehicle is debugged is solved, and the propeller can be locked before the unmanned aerial vehicle is debugged.

Description

Composite wing/rotor wing unmanned aerial vehicle propeller safety locking device and locking method

Technical Field

The invention relates to the field of aerometers, in particular to a composite wing/rotor wing unmanned aerial vehicle propeller safety locking device and a locking method.

Background

With the development of science and technology, unmanned aerial vehicles are widely applied in the fields of terrain surveying, circuit patrolling, military investigation and the like, so that various universities, scientific research institutions and enterprises strive for research, development and production of unmanned aerial vehicles. After a section unmanned aerial vehicle is accomplished in the design equipment, for the feasibility of verifying index such as its structure, power and flight control, the test of flying in the outfield is indispensable. However, when the compound wing/rotor unmanned aerial vehicle is debugged on the ground, a propeller may be started by mistake due to a flight control program error or a manual misoperation, and a safety accident is caused. Therefore, in order to guarantee the safety of debugging personnel, before the compound wing unmanned aerial vehicle/rotor unmanned aerial vehicle takes off, it is significant to lock the propeller at a certain position.

At present, be applied to screw safety locking device in the engineering reality still less, its difficult point lies in, and the device should be simple and easy practical, and the operational reliability is high, simultaneously, under the locking state, does not influence the artificial removal and the rotation to unmanned aerial vehicle.

Disclosure of Invention

The invention aims to provide a propeller safety locking device and a propeller safety locking method for a composite wing/rotor wing unmanned aerial vehicle, and solves the problem that the propeller is started by mistake due to program error before the unmanned aerial vehicle is debugged.

In order to achieve the above purpose, one technical solution of the present invention is as follows: the utility model provides a compound wing/rotor unmanned aerial vehicle screw safety locking device, is including transporting the fork and installing the locking mechanism on compound wing/rotor unmanned aerial vehicle rotor roof beam, transport the fork including the wood fork that is "Y" font and install the mounting panel on the wood fork, locking mechanism includes U type frame, locating part and electric control lock, U type frame screw connection is on the mounting panel, the one end and the U type frame of locating part rotate to be connected, the other end and the U type frame of locating part peg graft jointly and have the bolt, be equipped with the stay cord on the bolt, electric control lock is connected with flight controller electricity, electric control lock sets up the one side relative with the bolt on U type frame, the lock core of electric control lock and the one end of locating part block mutually block with, compound wing/rotor unmanned aerial vehicle's rotor roof beam is located between spacing frame and the U type frame.

Furthermore, a foam layer is filled in the U-shaped frame below the limiting piece.

The other technical scheme of the invention is as follows: a composite wing/rotor unmanned aerial vehicle propeller safety locking device comprises the following steps:

s1, before ground debugging, manually shifting the propeller to a position parallel to the rotor wing beam;

s2, a debugging person locks the limiting piece on the U-shaped frame by using the bolt, and at the moment, the pull rope on the bolt needs to be taken in the hand of the debugging person;

s3, moving the personnel to be debugged to a safe area, installing the locking mechanism on the conveying fork, conveying the locking mechanism to the bottom of the rotor wing beam by using the conveying fork, and slowly moving the locking mechanism upwards until the locking mechanism abuts against the rotor wing beam;

s4, pulling the pull rope to pull out the bolt, enabling the limiting piece to rotate anticlockwise under the action of gravity until the limiting piece is contacted with the end face of the rotor wing beam, powering off the electric control lock by using the flight controller, and enabling the lock core to be clamped with the limiting piece after being popped out to complete locking;

and S5, removing the conveying fork.

Compared with the prior art, the beneficial effect of this scheme:

1. if the propeller is started by mistake due to a flight control program or manual misoperation, hard collision can be reduced by the foam on the inner side of the locking mechanism, and the propeller can be protected to a certain extent.

2. This scheme can be at the dead/unblock screw of safe distance outer lock, and under the lock state of dying, does not influence the artificial removal and the rotation to unmanned aerial vehicle to convenient debugging.

3. The scheme adopts the electric control lock with the power-off lock cylinder retracted and the power-on lock cylinder ejected, has low power consumption and strong structural reliability, and can be repeatedly used.

4. When the scheme is unlocked, other operations are not needed, and the lock can fall off only by self gravity.

Drawings

FIG. 1 is an isometric view of the present embodiment in an unlocked state;

FIG. 2 is an isometric view of the deadlocking mechanism of the present embodiment in a deadlocked condition;

FIG. 3 is an isometric view of the deadlocking mechanism of the present embodiment in an unlocked condition;

fig. 4 is an isometric view of the transport fork of this embodiment.

Detailed Description

The present invention will be described in further detail below by way of specific embodiments:

reference numerals in the drawings of the specification include: the device comprises a conveying fork 1, a locking mechanism 2, a rotary wing beam 3, a limiting piece 4, a U-shaped frame 5, a propeller 6, a foam layer 7, a bolt 8, an electric control lock 9, a wooden fork 10 and a mounting plate 11.

Examples

As shown in figures 1 to 4: a composite wing/rotor unmanned aerial vehicle propeller safety locking device comprises a conveying fork 1 and a locking mechanism 2 installed on a composite wing/rotor unmanned aerial vehicle rotor beam 3. The conveying fork 1 comprises a Y-shaped wooden fork 10 and a mounting plate 11 which is connected to the wooden fork 10 through bolts, four thread clearance holes are symmetrically formed in the mounting plate 11, and the four thread clearance holes are fixedly connected with the U-shaped frame 5 through self-tapping screws and the four screw clearance holes. The locking mechanism 2 comprises a U-shaped frame 5, a limiting part 4 and an electric control lock 9, and four threaded holes matched with the threaded clearance holes are formed in the top of the U-shaped frame 5. The cross section of locating part 4 is the several font of shape, and the right-hand member of locating part 4 is connected through the round pin axle rotation with the right side of U type frame 5, and open the right side of U type frame 5 has the recess the same with locating part 4 thickness, and the left end of locating part 4 and the right side of U type frame 5 are pegged graft jointly and are had bolt 8, have tied up the stay cord on bolt 8. Electric control lock 9 is connected with the flight controller electricity, and electric control lock 9 is installed in the left side of U type frame 5, and electric control lock 9's lock core and the left end of locating part 4 block mutually and, and compound wing/rotor unmanned aerial vehicle's rotor 3 is located between spacing and the U type frame 5. The U-shaped frame 5 below the limiting piece 4 is filled with the foam layer 7, the propeller 6 can be started by mistake due to flight control program errors or manual misoperation on the basis of the foam layer 7, hard collision can be reduced through foam on the inner side of the locking mechanism 2, and the propeller 6 can be protected to a certain degree.

In this embodiment, the locking method of the safety locking device includes the following steps:

s1, before ground debugging, manually shifting the propeller 6 to a position parallel to the rotor wing beam 3;

s2, electrifying the electric control lock 9 by using the flight controller, retracting the lock cylinder of the electric control lock 9, clockwise rotating the limiting piece 490 degrees, locking the limiting piece 4 on the U-shaped frame 5 by using the bolt 8, and taking the pull rope on the bolt 8 in the hands of debugging personnel;

s3, moving the personnel to be debugged to a safe area, installing the locking mechanism 2 on the conveying fork 1, conveying the locking mechanism 2 to the bottom of the rotor wing beam 3 by using the conveying fork 1, and slowly moving the locking mechanism 2 upwards until the locking mechanism 2 abuts against the rotor wing beam 3;

s4, pulling the pull rope to pull out the bolt 8, enabling the limiting piece 4 to rotate anticlockwise under the action of gravity until the limiting piece contacts with the end face of the rotor wing beam 3, powering off the electric control lock 9 by using the flight controller, and limiting the movement of the limiting piece 4 after the lock core is popped out to form a closed frame, so that the locking mechanism 2 is tightly held on the rotor wing beam 3, and then the left vertical beam and the right vertical beam are used for limiting the rotation of the propeller 6 to complete locking;

and S5, removing the conveying fork 1.

The unlocking process of the embodiment includes the following steps:

electrifying the electric control lock 9 by using the flight controller, and retracting the lock cylinder of the electric control lock 9 at the moment; the locking mechanism 2 will fall automatically under the action of gravity to complete unlocking.

The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.

Claims (3)

1. The utility model provides a device is died to compound wing rotor unmanned aerial vehicle screw safety lock which characterized in that: including transporting the fork and installing the locking mechanism on compound wing rotor unmanned aerial vehicle rotor roof beam, transport the fork including the wood fork that is "Y" font and install the mounting panel on the wood fork, locking mechanism includes U type frame, locating part and electric control lock, U type frame screw connection is on the mounting panel, the one end and the U type frame of locating part rotate to be connected, the other end and the common grafting of U type frame of locating part have the bolt, be equipped with the stay cord on the bolt, the electric control lock is connected with flight controller electricity, the electric control lock sets up the one side relative with the bolt on U type frame, the lock core of electric control lock and the one end of locating part block mutually block with, compound wing rotor unmanned aerial vehicle's rotor roof beam is located between spacing and the U type frame.

2. The composite wing/rotor drone propeller safety deadlocking device of claim 1, wherein: and a foam layer is filled in the U-shaped frame below the limiting part.

3. A composite wing/rotor drone propeller safety deadlocking device according to any one of claims 1 or 2, characterized in that: the locking method of the safety locking device comprises the following steps:

s1, before ground debugging, manually shifting the propeller to a position parallel to the rotor wing beam;

s2, a debugging person locks the limiting piece on the U-shaped frame by using the bolt, and at the moment, the pull rope on the bolt needs to be taken in the hand of the debugging person;

s3, moving the personnel to be debugged to a safe area, installing the locking mechanism on the conveying fork, conveying the locking mechanism to the bottom of the rotor wing beam by using the conveying fork, and slowly moving the locking mechanism upwards until the locking mechanism abuts against the rotor wing beam;

s4, pulling the pull rope to pull out the bolt, enabling the limiting piece to rotate anticlockwise under the action of gravity until the limiting piece is contacted with the end face of the rotor wing beam, powering off the electric control lock by using the flight controller, and enabling the lock core to be clamped with the limiting piece after being popped out to complete locking;

and S5, removing the conveying fork.

Images