CN216734777U

CN216734777U - Missile-carrying multi-rotor unmanned aerial vehicle

Info

Publication number: CN216734777U
Application number: CN202220013890.XU
Authority: CN
Inventors: 龚帮民; 艾剑良
Original assignee: Fudan University
Current assignee: Fudan University
Priority date: 2022-01-04
Filing date: 2022-01-04
Publication date: 2022-06-14
Anticipated expiration: 2032-01-04

Abstract

The utility model discloses a missile-carrying multi-rotor unmanned aerial vehicle, which belongs to the field of unmanned aerial vehicles and comprises a vehicle body, a plurality of arms connected with the vehicle body and power components arranged on each arm, wherein one side of the bottom surface of the vehicle body is fixedly provided with a clamping mechanism for clamping a cannonball; fixture includes casing, motor, transmission shaft and clamping jaw, casing fixed mounting be in bottom surface one side of fuselage, the transmission shaft is parallel and be provided with two relatively, two the transmission shaft is all rotatable to be connected on the casing, every all install on the transmission shaft the clamping jaw, motor fixed mounting be in on the casing, just the motor is through driving two the reverse synchronous rotation of transmission shaft changes two the switching degree of clamping jaw. The mounting device is simple in structure and reasonable in design, and can be suitable for mounting shells of various sizes, so that the task diversity capability of the multi-rotor unmanned aerial vehicle is improved.

Description

Can carry many rotor unmanned aerial vehicle of bullet

Technical Field

The utility model relates to the field of unmanned aerial vehicles, in particular to a missile-carrying multi-rotor unmanned aerial vehicle.

Background

The military unmanned aerial vehicle has the characteristics of exquisite structure, strong concealment, convenient use, low manufacturing cost, flexible performance and the like, is mainly used for battlefield reconnaissance, electronic interference, carrying of clustered bombs, guided missiles and other weapons to execute aggressive missions, and is used as an aerial communication relay platform, a nuclear test sampler, a nuclear explosion and nuclear radiation reconnaissance plane and the like. And many rotor unmanned aerial vehicle have that the nature controlled is strong, can VTOL and hover the characteristics, consequently be applicable to low latitude, low-speed, have the task type of VTOL and hover the requirement. With the development of modern war forms, the multi-rotor unmanned aerial vehicle is more and more applied to modern war by virtue of self advantages, wherein urban street fighting and reconnaissance are the most typical.

The multi-rotor unmanned aerial vehicle can carry various accurate attack weapons to attack ground and offshore targets or carry out air combat with air-to-air missiles and also can carry out reverse guidance interception. The unmanned aerial vehicle for battle carries the unit for battle, finds important targets to attack in real time, realizes 'check and tie', can reduce casualties and improve the attack ability of troops.

But the stores pylon that many rotor unmanned aerial vehicle carried the shell at present is mostly single type and can not change the size, and the shell kind of carrying is single to influence the war demand.

SUMMERY OF THE UTILITY MODEL

Aiming at the problems that the type of a hanging rack for carrying shells of a multi-rotor unmanned aerial vehicle is single and the size of the hanging rack cannot be changed in the prior art, the utility model aims to provide the multi-rotor unmanned aerial vehicle capable of carrying the shells.

In order to realize the purpose, the technical scheme of the utility model is as follows:

a missile-carrying multi-rotor unmanned aerial vehicle comprises a fuselage, a plurality of arms connected with the fuselage and a power assembly arranged on each arm, wherein a clamping mechanism for clamping a missile is fixedly arranged on one side of the bottom surface of the fuselage; fixture includes casing, motor, transmission shaft and clamping jaw, casing fixed mounting be in bottom surface one side of fuselage, the transmission shaft is parallel and be provided with two relatively, two the transmission shaft is all rotatable to be connected on the casing, every all install on the transmission shaft the clamping jaw, motor fixed mounting be in on the casing, just the motor is through driving two the reverse synchronous rotation of transmission shaft changes two the switching degree of clamping jaw.

Preferably, the transmission shafts are connected through a synchronous gear, and an output shaft of the motor is connected with any one of the transmission shafts.

Preferably, an output shaft of the motor is provided with a driving gear, and any one of the transmission shafts is provided with a driven gear engaged with the driving gear.

Preferably, the clamping jaw is the arc, the clamping jaw includes fixed segmental arc and activity segmental arc, fixed segmental arc is used for fixed connection in on the transmission shaft, but activity segmental arc sliding connection be in on the fixed segmental arc, just the activity segmental arc with be provided with locking structure between the fixed segmental arc.

Preferably, the locking structure comprises a locking screw fixedly connected to the movable arc section and a locking nut screwed on the locking screw, wherein the fixed arc section is provided with a through groove for the locking screw to move, and the free end of the locking screw penetrates through the through groove and then is connected with the locking nut.

Furthermore, an ultrasonic detector is fixedly mounted on one side of the bottom surface of the machine body.

Furthermore, a rack is fixedly mounted on one side of the bottom surface of the machine body, and an elastic shock pad is mounted at the bottom of the rack.

Furthermore, a positioning module is fixedly installed on one side of the top surface of the machine body.

Preferably, two clamping mechanisms are symmetrically arranged on one side of the bottom surface of the machine body.

By adopting the technical scheme, the utility model has the beneficial effects that: due to the clamping mechanism and the arrangement of the motor, the transmission shaft and the clamping jaws, the motor can drive the two transmission shafts to synchronously and reversely rotate after acting, the opening and closing degrees between the two corresponding clamping jaws are changed, so that the shell can be clamped, and for the carrying requirements of shells with different diameters, the opening and closing degrees of the clamping jaws only need to be changed, and the shells with different diameters can be clamped and fixed by virtue of the arc-shaped structures of the clamping jaws; when the cannonball needs to be released, the motor is correspondingly reversed.

Drawings

FIG. 1 is a front view of the present invention;

FIG. 2 is a side view of the present invention;

FIG. 3 is a schematic view of the interior of the housing of the clamping mechanism of the present invention

Fig. 4 is a schematic structural view of a clamping jaw in the second embodiment of the utility model.

In the figure, 1-machine body, 2-machine arm, 3-power assembly, 4-machine shell, 5-motor, 50-synchronous gear, 51-driving gear, 52-driven gear, 6-transmission shaft, 7-clamping jaw, 71-fixed arc section, 72-movable arc section, 73-locking screw, 74-locking nut, 8-ultrasonic detector, 9-machine frame, 10-elastic shock pad, 11-positioning module and 12-cannonball.

Detailed Description

The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

It should be noted that in the description of the present invention, the terms "upper", "lower", "left", "right", "front", "rear", and the like indicate orientations or positional relationships based on structures shown in the drawings, and are only used for convenience in describing the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

In the technical scheme, the terms "first" and "second" are only used for referring to the same or similar structures or corresponding structures with similar functions, and are not used for ranking the importance of the structures, or comparing the sizes or other meanings.

In addition, unless expressly stated or limited otherwise, the terms "mounted" and "connected" are to be construed broadly, e.g., the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; the two structures can be directly connected or indirectly connected through an intermediate medium, and the two structures can be communicated with each other. To those skilled in the art, the specific meanings of the above terms in the present invention can be understood in light of the present general concepts, in connection with the specific context of the scheme.

Example one

A missile-loadable multi-rotor unmanned aerial vehicle is shown in figures 1-3 and comprises a vehicle body 1, a plurality of arms 2 connected with the vehicle body 1 and a power assembly 3 arranged on each arm 2. Wherein, a clamping mechanism for clamping the cannonball is fixedly arranged on one side of the bottom surface of the machine body 1. The clamping mechanism comprises a machine shell 4, a motor 5, a transmission shaft 6 and a clamping jaw 7. Casing 4 fixed mounting is in bottom surface one side of fuselage 1, and transmission shaft 6 is parallel and be provided with two relatively, and two transmission shafts 6 all can rotate to be connected on casing 4, all installs clamping jaw 7 on every transmission shaft 6, and motor 5 is then fixed mounting on casing 4, and motor 5 is through driving the 6 reverse synchronous rotation of two transmission shafts and change the switching degree of two clamping jaws 7.

In the present embodiment, the body 1 has a shell-like configuration, and a battery for supplying power and an airplane control system for controlling flight are disposed therein. Four horn 2 are arranged, the horn 2 is of a hollow tubular configuration, and the horn 2 is integrally formed at four peripheral corners of the body 1. The power assembly 3 comprises a motor fixedly arranged at the tip of the horn 2 and a blade arranged at the output end of the motor.

The casing 4 is configured to be a rectangular housing structure, and the casing 4 is fixedly connected to one side of the bottom surface of the body 1 by screws. Two bearing mounting holes are respectively arranged on two opposite side walls of the machine shell 4, and bearings are installed at two ends of the transmission shaft 6 correspondingly, so that two ends of the transmission shaft 6 are connected to the two side walls of the machine shell 4 through the bearings, and two ends of the transmission shaft 6 are arranged to extend out of the machine shell 4. Inside the housing 4, the two transmission shafts 6 are connected by a synchronizing gear 50, thereby ensuring that the two shafts can rotate in opposite directions in synchronization. The motor 5 is fixedly installed inside the housing 4, and an output shaft of the motor 5 is connected to any one of the transmission shafts 6, for example, a driving gear 51 is installed on the output shaft of the motor 5, and a driven gear 52 engaged with the driving gear 51 is correspondingly installed on the transmission shaft 6 connected to the motor 5. The arrangement is such that after the motor 5 rotates, one of the transmission shafts 6 is driven to rotate by the meshing of the driving gear 51 and the driven gear 52, and the two transmission shafts 6 realize synchronous reverse rotation by means of the synchronizing gear 50.

In the present embodiment, the clamping jaw 7 has an overall arc-shaped configuration, for example, an arc-shaped plate-like configuration. Both sides of the upper end of the clamping jaw 7 are respectively provided with a connecting lug, and the two connecting lugs are respectively provided with a shaft hole matched with the transmission shaft 6, so that the clamping jaw 7 is fixedly connected with the transmission shaft 6 through a key. It will be appreciated that in order to reduce weight, the jaws 7 will typically be provided with lightening holes, so that the jaws 7 as a whole are again formed in a frame-like configuration.

When the shell 12 needs to be clamped, the motor 5 works, one of the transmission shafts 6 is driven to rotate through the meshing of the driving gear 51 and the driven gear 52, the two transmission shafts 6 synchronously rotate in opposite directions under the action of the synchronizing gear 50, and the two corresponding clamping jaws 7 synchronously rotate in opposite directions, so that the two clamping jaws 7 approach each other as a result of the rotation, and the shell 12 is clamped between the two clamping jaws 7 and is fixed by virtue of the arc-shaped structures of the clamping jaws 7 and the tendency that the two clamping jaws 7 are close to each other. Conversely, when the shell 12 needs to be released, the motor 5 works reversely. The many rotor unmanned aerial vehicle who has above-mentioned fixture that this embodiment provided when carrying out the task, to the shell 12 of the different diameters that need carry, only need change between two clamping jaws 7 degree (switching degree) of drawing close each other can, when the skilled person in the art uses in practice, according to the diameter variation range rational configuration clamping jaw 7 of shell 12 radian and diameter can.

It will be appreciated that in some preferred embodiments, a double-ended steering engine may be used instead of the components of the clamping mechanism described above other than the clamping jaws 7. The double-ended steering engine has two outputs parallel to each other for replacing the two transmission shafts 6.

In some preferred embodiments, an ultrasonic detector 8 is further fixedly mounted on one side of the bottom surface of the fuselage 1, and the ultrasonic detector 8 is electrically connected with flight control equipment inside the fuselage 1 through a conducting wire, so that the multi-rotor unmanned aerial vehicle can avoid obstacles when vertically landing.

In some preferred embodiments, a frame 9 is further fixedly mounted on one side of the bottom surface of the body 1, the frame 9 is configured as four mutually independent legs, each leg is fixedly connected to the bottom surface of the body 1 through a screw, a cross rod is connected between every two legs, and an elastic shock-absorbing pad 10, such as a gasket made of rubber material, is sleeved on the cross rod. And the length of the legs is typically greater than the diameter of the projectile 12 to ensure that the projectile 12 does not contact the ground when the drone is dropped.

In some preferred embodiments, a positioning module 11, for example, a GPS locator, is fixedly installed on one side of the top surface of the fuselage 1, and is connected with the flight control device inside the fuselage 1 through a data line, so that the flight control device can fly according to the position indicated by the GPS locator and transmit the position of the unmanned aerial vehicle to the ground command station during the flight of the unmanned aerial vehicle.

In some preferred embodiments, two of the above-mentioned clamping mechanisms are symmetrically installed on one side of the bottom surface of the body 1. And two fixture symmetric arrangement are in the both sides of unmanned aerial vehicle bottom surface.

Example two

The difference from the first embodiment is that: in this embodiment, as shown in fig. 4, the clamping jaw 7 includes a fixed arc section 71 and a movable arc section 72, the two sides of the upper end of the fixed arc section 71 are correspondingly provided with the above-mentioned engaging lugs, so that the fixed arc section 71 is fixedly connected to the transmission shaft 6, the movable arc section 72 is slidably connected to the fixed arc section 71, and a locking structure is arranged between the movable arc section 72 and the fixed arc section 71.

In this embodiment, a sliding groove is disposed on the back surface of the fixed arc section 71, and a sliding block used in cooperation with the sliding groove is disposed at the upper end of the movable arc section 72. The locking structure comprises a locking screw 73 fixedly connected to one side of the back face of the movable arc section 72, a through groove for the locking screw 73 to move in is formed in the movable arc section 72, and the free end of the locking screw 73 penetrates through the through groove, extends out of one side of the back face of the movable arc section 72 and is screwed with a locking nut 74. The arrangement is such that the overall length of the jaws 7 can be adjusted by the locking arrangement for projectiles of different diameters, for example small diameter projectiles, the length of the jaws 7 can be shortened, and for large diameter projectiles the length of the jaws 7 can be extended.

The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, and the scope of protection is still within the scope of the utility model.

Claims

1. The utility model provides a but many rotor unmanned aerial vehicle of bomb carrying, including fuselage, a plurality of with the horn that the fuselage is connected and install every power component on the horn, its characterized in that: a clamping mechanism for clamping a shell is fixedly arranged on one side of the bottom surface of the machine body; fixture includes casing, motor, transmission shaft and clamping jaw, casing fixed mounting be in bottom surface one side of fuselage, the transmission shaft is parallel and be provided with two relatively, two the transmission shaft is all rotatable to be connected on the casing, every all install on the transmission shaft the clamping jaw, motor fixed mounting be in on the casing, just the motor is through driving two the reverse synchronous rotation of transmission shaft changes two the switching degree of clamping jaw.

2. The missile-loadable multi-rotor drone of claim 1, wherein: the transmission shafts are connected through synchronous gears, and an output shaft of the motor is connected with any one of the transmission shafts.

3. The missile-loadable multi-rotor drone of claim 1, wherein: and a driving gear is arranged on an output shaft of the motor, and a driven gear meshed with the driving gear is arranged on any one of the transmission shafts.

4. The missile-loadable multi-rotor drone of claim 1, wherein: the clamping jaw is the arc, the clamping jaw includes fixed segmental arc and activity segmental arc, fixed segmental arc is used for fixed connection to be in on the transmission shaft, but activity segmental arc sliding connection be in on the fixed segmental arc, just the activity segmental arc with be provided with locking structure between the fixed segmental arc.

5. The missile-loadable multi-rotor drone of claim 4, wherein: the locking structure comprises a locking screw fixedly connected to the movable arc section and a locking nut screwed on the locking screw, wherein a through groove for the locking screw to move is formed in the fixed arc section, and the free end of the locking screw penetrates through the through groove and then is connected with the locking nut.

6. The missile-loadable multi-rotor drone of claim 1, wherein: and an ultrasonic detector is fixedly arranged on one side of the bottom surface of the machine body.

7. The missile-loadable multi-rotor drone of claim 1, wherein: the bottom surface one side of fuselage still fixed mounting has the frame, the bottom of frame is installed the elasticity shock pad.

8. The missile-loadable multi-rotor drone of claim 1, wherein: and a positioning module is fixedly arranged on one side of the top surface of the machine body.

9. The missile-loadable multi-rotor drone of claim 1, wherein: two clamping mechanisms are symmetrically arranged on one side of the bottom surface of the machine body.