阅读说明：本技术 一种可折叠筒式多旋翼无人机 (Many rotor unmanned aerial vehicle of collapsible cylinder ) 是由 陈文芳 李鹏飞 刘帅 王昂 罗伟 陈文超 于 2021-01-07 设计创作，主要内容包括：本发明公开一种可折叠筒式多旋翼无人机,包括底部支撑板和顶部支撑板,底部支撑板和顶部支撑板之间连接有多根圆柱杆体,顶部支撑板上安装有无人机航电系统,底部支撑板上安装有用于给无人机航电系统供电的电池,在底部支撑板和顶部支撑板之间设置有机臂动作组件,机臂动作组件上设置有多个无人机机臂,在无人机机臂上设置有与无人机航电系统电连接的无人机动力组件,机臂动作组件是自动收放机臂的收放机构或自动展开机臂的弹放机构；本发明可以使多旋翼无人机快速进入工作状态以及快速回收入箱保存,便于存放和携带；当通过发射机构将多旋翼无人机从发射筒内发射出去后,多旋翼无人机的机臂可以快速自动展开并锁紧,配合士兵作战。(The invention discloses a foldable barrel type multi-rotor unmanned aerial vehicle, which comprises a bottom supporting plate and a top supporting plate, wherein a plurality of cylindrical rod bodies are connected between the bottom supporting plate and the top supporting plate, an unmanned aerial vehicle avionic system is installed on the top supporting plate, a battery for supplying power to the unmanned aerial vehicle avionic system is installed on the bottom supporting plate, a horn action assembly is arranged between the bottom supporting plate and the top supporting plate, a plurality of unmanned aerial vehicle horns are arranged on the horn action assembly, an unmanned aerial vehicle power assembly electrically connected with the unmanned aerial vehicle avionic system is arranged on each unmanned aerial vehicle horn, and the horn action assembly is a retraction mechanism for automatically retracting or extending the horns or an ejection mechanism for automatically extending the horns; the invention can lead the multi-rotor unmanned aerial vehicle to rapidly enter the working state and to be rapidly recycled and stored in the box, thereby being convenient for storage and carrying; after launching many rotor unmanned aerial vehicle from the launching tube through launching mechanism, many rotor unmanned aerial vehicle's horn can expand fast automatically and lock, cooperates the soldier to fight.)

1. The utility model provides a many rotor unmanned aerial vehicle of collapsible cylinder which characterized in that: the unmanned aerial vehicle power assembly comprises a bottom supporting plate and a top supporting plate, wherein a plurality of cylindrical rod bodies are connected between the bottom supporting plate and the top supporting plate, the cylindrical rod bodies are circumferentially arranged, an unmanned aerial vehicle avionic system is installed on the top supporting plate, a battery for supplying power to the unmanned aerial vehicle avionic system is installed on the bottom supporting plate, an arm action assembly is arranged between the bottom supporting plate and the top supporting plate, the arm action assembly is fixedly connected with the cylindrical rod bodies, a plurality of unmanned aerial vehicle arms are arranged on the arm action assembly, an unmanned aerial vehicle power assembly electrically connected with the unmanned aerial vehicle avionic system is arranged on each unmanned aerial vehicle arm, the unmanned aerial vehicle power assembly comprises a driving motor, a motor base and a propeller, the driving motor is installed on each unmanned aerial vehicle arm through the motor base, and the propeller is installed on; the horn action assembly is a retraction mechanism for automatically retracting the horn or an ejection mechanism for automatically unfolding the horn.

2. A foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1, wherein the retracting mechanism of the automatic retracting arm comprises a lower support plate, an upper support plate, a motor, a lead screw and a connector; the lower supporting plate and the upper supporting plate are respectively provided with a plurality of mounting holes for connecting with a plurality of cylindrical rod bodies, and the lower supporting plate and the upper supporting plate are respectively connected with the cylindrical rod bodies through the mounting holes; the motor is installed at the top of the lower supporting plate, a hole is formed in the middle of the upper supporting plate, a plurality of rib plates are circumferentially arranged on the top of the upper supporting plate, the rib plates are vertically arranged, the tops of the rib plates are connected together, the lead screw is vertically arranged between the lower supporting plate and the upper supporting plate, the bottom end of the lead screw is in transmission connection with an output shaft of the motor, and the top end of the lead screw penetrates through the hole in the middle of the upper supporting plate and then is rotatably connected to the top connection position of the rib plates; the connector is in threaded connection with the lead screw, a plurality of first executing components are connected to the connector, the first executing components are arranged circumferentially, each first executing component comprises a hinge block, a rotating arm and a sleeve, the tail end of the hinge block is hinged to the connector, the head end of the hinge block is hinged to the tail end of the rotating arm, the head end of the rotating arm is rigidly connected with the outer circumferential surface of the sleeve, and the sleeve is hinged to the edge of the upper supporting plate towards the top of the end surface of the upper supporting plate; the sleeve pipe is kept away from the end connection unmanned aerial vehicle horn of last backup pad.

3. A foldable barrel type multi-rotor unmanned aerial vehicle according to claim 2, wherein the head end of the hinged block is a U-shaped structure, and the tail end of the rotating arm is hinged in the U-shaped structure at the head end of the hinged block.

4. The foldable barrel type multi-rotor unmanned aerial vehicle as claimed in claim 2, wherein the head end of the rotating arm is formed with two arms, ends of the two arms are respectively bent by 90 degrees and then rigidly connected to the outer circumference of the casing, and the bending directions of the ends of the two arms are the same.

5. A foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1, wherein the ejection mechanism of the automatic unfolding arm comprises a central disc, a plurality of mounting holes are formed on the central disc for connecting with a plurality of cylindrical rods, and the central disc is connected with the cylindrical rods through the mounting holes; a linear steering engine is arranged in the middle of the central disc, an execution end of the linear steering engine is vertically downward, and a clamping disc is arranged at the end part of the execution end of the linear steering engine; the central disc is provided with a plurality of second execution assemblies which are circumferentially arranged, each second execution assembly comprises a folding piece, a spring and a clamping piece, the folding piece is connected with the unmanned aerial vehicle arm, the clamping piece is fixedly sleeved on the outer circumferential surface of the head end of the folding piece, a connecting plate is formed on the outer circumferential surface of the folding piece, a fixing piece is arranged at the top of the central disc, one end of the spring is connected with the connecting plate, and the other end of the spring is connected with the fixing piece; the top of the end face of the tail end of the folding piece is provided with two positioning plates, the two positioning plates are hinged with the edge of the central disc through a rotating shaft, gaps for accommodating the two positioning plates are formed in the edge of the central disc, spring positioning pins are respectively arranged on the central discs on two sides of the two positioning plates and are oppositely arranged, moving grooves with arc structures are respectively formed on the outer side faces of the two positioning plates facing the two spring positioning pins, pin heads of the two spring positioning pins respectively slide in the moving grooves formed on the outer side faces of the two positioning plates, and a positioning groove is formed at the stroke tail end of each moving groove; when the spring pulls the folding piece to rotate to a horizontal position by taking the rotating shaft as a shaft, the pin heads of the two spring positioning pins are respectively inserted into the two positioning grooves.

6. The foldable barrel type multi-rotor unmanned aerial vehicle of claim 5, wherein the second actuating assembly comprises two springs, and the connecting plate on the folding member is connected with the fixing member through the two springs; the spring positioning pin is provided with a manual deflector rod; be provided with the intermediate lamella in screens dish below, the intermediate lamella is connected with many cylinder body of rod, is provided with the guide post at the intermediate lamella top, be formed with on the screens dish with guide post complex guiding hole.

7. A collapsible many rotor unmanned aerial vehicle of cylinder of claim 1, 2 or 5, characterized in that, still includes the fixed frame of battery, the fixed frame of battery is connected with many cylinder body, and the middle part of the fixed frame of battery is formed with the through-hole that passes the battery, and the fixed frame border of battery between two adjacent cylinder body has the groove structure who is used for holding the unmanned aerial vehicle horn.

8. A foldable barrel type multi-rotor unmanned aerial vehicle according to any one of claims 1, 2 or 5, wherein a barrel launching auxiliary device is arranged at the bottom of the bottom supporting plate and comprises a base, a plurality of supporting columns are vertically arranged at the top of the base and are circumferentially arranged, supporting frames are connected among the supporting columns, a conical body structure is formed at the top ends of the supporting columns, and the top ends of the supporting columns are movably contacted with the bottom ends of a plurality of cylindrical rod bodies on the bottom supporting plate.

9. A foldable barrel type multi-rotor unmanned aerial vehicle according to any one of claims 1, 2 or 5, wherein a four-point landing gear is attached to an outer circumferential surface of the bottom support plate.

10. A foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1, wherein a top fairing is mounted on the top support plate, an airframe fairing is sleeved around the plurality of cylindrical rods, and an opening for an unmanned aerial vehicle arm to pass through is formed in the airframe fairing.

Technical Field

The invention relates to a foldable barrel type multi-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.

Background

The existing multi-rotor unmanned aerial vehicle occupies a large space during storage and is inconvenient to carry, and the retraction and extension arms are realized manually, so that great inconvenience is brought to a user, and time and labor are consumed; when the multi-rotor unmanned aerial vehicle is used, the multi-rotor unmanned aerial vehicle can enter a working state only by manually taking out the multi-rotor unmanned aerial vehicle from the storage box, manually unfolding the horn and fastening the horn, and consuming time and labor; after the use, the machine arm needs to be manually contracted and then can be placed in the storage box, which is extremely inconvenient; particularly, when an army acts on a battle, the multi-rotor unmanned aerial vehicle needs to be deployed quickly, so that the multi-rotor unmanned aerial vehicle can enter a working state quickly and cooperate with soldiers to act on the battle; but current many rotor unmanned aerial vehicle can't satisfy this kind of operation requirement.

Disclosure of Invention

The invention aims to solve the problems in the prior art, and provides a foldable cylinder type multi-rotor unmanned aerial vehicle, which is a multi-rotor unmanned aerial vehicle body with a cylinder structure, wherein a bottom support plate, a top support plate and a plurality of cylindrical rod bodies form the multi-rotor unmanned aerial vehicle body; the retraction mechanism can enable the multi-rotor unmanned aerial vehicle to automatically unfold and retract the arms, so that the multi-rotor unmanned aerial vehicle can quickly enter a working state and be quickly retracted into a box for storage, manual intervention is not needed, and the retraction mechanism is very convenient and fast; the multi-rotor unmanned aerial vehicle can be stored in a long straight cylinder after the arm is retracted, and is convenient to store and carry; the catapult mechanism can fold, shrink and restrain the arms of the multi-rotor unmanned aerial vehicle, so that the multi-rotor unmanned aerial vehicle is conveniently arranged in the launcher, the occupied space is small, and the multi-rotor unmanned aerial vehicle is convenient to carry; after launching many rotor unmanned aerial vehicle from the launching tube through launching mechanism, many rotor unmanned aerial vehicle's horn can quick automatic expansion and locking to realize many rotor unmanned aerial vehicle and can enter into operating condition fast, cooperate soldier to fight, need deploy many rotor unmanned aerial vehicle's operation requirement fast when satisfying army's fight.

In order to achieve the above object, the present invention adopts the following technical solutions:

a foldable barrel type multi-rotor unmanned aerial vehicle comprises a bottom supporting plate and a top supporting plate, wherein a plurality of cylindrical rod bodies are connected between the bottom supporting plate and the top supporting plate and are circumferentially arranged, an unmanned aerial vehicle avionics system is arranged on the top supporting plate, a battery for supplying power to the unmanned aerial vehicle avionics system is arranged on the bottom supporting plate, a horn action component is arranged between the bottom supporting plate and the top supporting plate, the horn action component is fixedly connected with the plurality of cylindrical rod bodies, a plurality of unmanned aerial vehicle horns are arranged on the horn action component, an unmanned aerial vehicle power assembly electrically connected with an avionic system of the unmanned aerial vehicle is arranged on the arm of the unmanned aerial vehicle, the unmanned aerial vehicle power assembly comprises a driving motor, a motor base and a propeller, the driving motor is installed on an unmanned aerial vehicle arm through a motor base, and the propeller is installed on an output shaft of the driving motor; the horn action assembly is a retraction mechanism for automatically retracting the horn or an ejection mechanism for automatically unfolding the horn.

As a further preferred aspect of the present invention, the retracting mechanism of the automatic retracting and releasing arm includes a lower support plate, an upper support plate, a motor, a lead screw, and a connector; the lower supporting plate and the upper supporting plate are respectively provided with a plurality of mounting holes for connecting with a plurality of cylindrical rod bodies, and the lower supporting plate and the upper supporting plate are respectively connected with the cylindrical rod bodies through the mounting holes; the motor is installed at the top of the lower supporting plate, a hole is formed in the middle of the upper supporting plate, a plurality of rib plates are circumferentially arranged on the top of the upper supporting plate, the rib plates are vertically arranged, the tops of the rib plates are connected together, the lead screw is vertically arranged between the lower supporting plate and the upper supporting plate, the bottom end of the lead screw is in transmission connection with an output shaft of the motor, and the top end of the lead screw penetrates through the hole in the middle of the upper supporting plate and then is rotatably connected to the top connection position of the rib plates; the connector is in threaded connection with the lead screw, a plurality of first executing components are connected to the connector, the first executing components are arranged circumferentially, each first executing component comprises a hinge block, a rotating arm and a sleeve, the tail end of the hinge block is hinged to the connector, the head end of the hinge block is hinged to the tail end of the rotating arm, the head end of the rotating arm is rigidly connected with the outer circumferential surface of the sleeve, and the sleeve is hinged to the edge of the upper supporting plate towards the top of the end surface of the upper supporting plate; the sleeve pipe is kept away from the end connection unmanned aerial vehicle horn of last backup pad.

As a further preferred aspect of the present invention, the head end of the hinged block is a U-shaped structure, and the tail end of the rotating arm is hinged in the U-shaped structure at the head end of the hinged block; the tail end of the rotating arm is connected with the head end of the hinged block in a better rotating mode.

As a further preferred aspect of the present invention, two arms are formed at the head end of the rotating arm, the end portions of the two arms are respectively bent by 90 degrees and then rigidly connected to the outer circumferential surface of the sleeve, and the bending directions of the end portions of the two arms are the same; the head end of the rotating arm of being convenient for and sheathed tube outer periphery rigid connection improve the turned angle when contracting unmanned aerial vehicle horn simultaneously.

As a further preferred aspect of the present invention, the ejection mechanism of the automatic unfolding machine arm includes a central disc, the central disc is formed with a plurality of mounting holes for connecting with a plurality of cylindrical rod bodies, and the central disc is connected with the cylindrical rod bodies through the mounting holes; a linear steering engine is arranged in the middle of the central disc, an execution end of the linear steering engine is vertically downward, and a clamping disc is arranged at the end part of the execution end of the linear steering engine; the central disc is provided with a plurality of second execution assemblies which are circumferentially arranged, each second execution assembly comprises a folding piece, a spring and a clamping piece, the folding piece is connected with the unmanned aerial vehicle arm, the clamping piece is fixedly sleeved on the outer circumferential surface of the head end of the folding piece, a connecting plate is formed on the outer circumferential surface of the folding piece, a fixing piece is arranged at the top of the central disc, one end of the spring is connected with the connecting plate, and the other end of the spring is connected with the fixing piece; the top of the end face of the tail end of the folding piece is provided with two positioning plates, the two positioning plates are hinged with the edge of the central disc through a rotating shaft, gaps for accommodating the two positioning plates are formed in the edge of the central disc, spring positioning pins are respectively arranged on the central discs on two sides of the two positioning plates and are oppositely arranged, moving grooves with arc structures are respectively formed on the outer side faces of the two positioning plates facing the two spring positioning pins, pin heads of the two spring positioning pins respectively slide in the moving grooves formed on the outer side faces of the two positioning plates, and a positioning groove is formed at the stroke tail end of each moving groove; when the spring pulls the folding piece to rotate to a horizontal position by taking the rotating shaft as a shaft, the pin heads of the two spring positioning pins are respectively inserted into the two positioning grooves.

As a further preferred aspect of the present invention, the second actuating assembly includes two springs, and the connecting plate on the folding member is connected to the fixing member through the two springs; the spring positioning pin is provided with a manual deflector rod; an intermediate plate is arranged below the clamping disc and connected with a plurality of cylindrical rod bodies, a guide post is arranged at the top of the intermediate plate, and a guide hole matched with the guide post is formed in the clamping disc; the intermediate lamella can improve the connection stability between the many cylindrical rod bodies, and the guide post plays the guide effect to the screens dish.

As further optimization of the invention, the unmanned aerial vehicle further comprises a battery fixing frame, wherein the battery fixing frame is connected with a plurality of cylindrical rod bodies, a through hole for a battery to pass through is formed in the middle of the battery fixing frame, and a groove structure for accommodating an unmanned aerial vehicle arm is arranged at the edge of the battery fixing frame between every two adjacent cylindrical rod bodies; the battery fixing frame is used for connecting the battery and the plurality of cylindrical rod bodies, so that the structural stability of the battery after installation is improved; the groove structure at the edge of the battery fixing frame is used for limiting the arm of the unmanned aerial vehicle in a contraction state.

As a further preferred aspect of the present invention, a gun barrel launching auxiliary device is arranged at the bottom of the bottom supporting plate, the gun barrel launching auxiliary device comprises a base, a plurality of supporting columns are vertically arranged at the top of the base, the plurality of supporting columns are circumferentially arranged, supporting frames are connected between the plurality of supporting columns, conical body structures are formed at the top ends of the supporting columns, and the top ends of the plurality of supporting columns are in movable contact with the bottom ends of a plurality of cylindrical rod bodies on the bottom supporting plate; the gun barrel launching auxiliary device is used for bearing the instantaneous overload force of gun barrel launching, and after launching, the gun barrel launching auxiliary device automatically falls off.

As a further preferred aspect of the present invention, a four-point type undercarriage is attached to the outer circumferential surface of the bottom support plate; when the unmanned aerial vehicle takes off on the ground, the unmanned aerial vehicle can take off on the ground independently.

As a further preferred aspect of the invention, a top fairing is mounted on the top support plate, a machine body fairing is sleeved outside the plurality of cylindrical rods, and an opening for allowing the unmanned aerial vehicle arm to pass through is formed on the machine body fairing; the top fairing and the engine body fairing enable the appearance of the unmanned aerial vehicle to meet the aerodynamic design, and air resistance when the unmanned aerial vehicle flies is reduced.

The invention has the advantages that:

the multi-rotor unmanned aerial vehicle body is of a cylindrical structure and is composed of a bottom supporting plate, a top supporting plate and a plurality of cylindrical rod bodies, and a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body and is a retraction mechanism for automatically retracting a horn or an ejection mechanism for automatically expanding the horn; the retraction mechanism can enable the multi-rotor unmanned aerial vehicle to automatically unfold and retract the arms, so that the multi-rotor unmanned aerial vehicle can quickly enter a working state and be quickly retracted into a box for storage, manual intervention is not needed, and the retraction mechanism is very convenient and fast; the multi-rotor unmanned aerial vehicle can be stored in a long straight cylinder after the arm is retracted, and is convenient to store and carry; the catapult mechanism can fold, shrink and restrain the arms of the multi-rotor unmanned aerial vehicle, so that the multi-rotor unmanned aerial vehicle is conveniently arranged in the launcher, the occupied space is small, and the multi-rotor unmanned aerial vehicle is convenient to carry; after launching many rotor unmanned aerial vehicle from the launching tube through launching mechanism, many rotor unmanned aerial vehicle's horn can quick automatic expansion and locking to realize many rotor unmanned aerial vehicle and can enter into operating condition fast, cooperate soldier to fight, need deploy many rotor unmanned aerial vehicle's operation requirement fast when satisfying army's fight.

Drawings

Fig. 1 is a schematic perspective view of a first embodiment of the present invention;

fig. 2 is a schematic perspective view of a retraction/extension mechanism for unfolding an arm of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 3 is a schematic perspective view illustrating a retraction mechanism retracting an arm of an unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 4 is an exploded view of a pick and place mechanism according to an embodiment of the present invention;

FIG. 5 is a schematic view of the attachment of the bottom support plate to the four-point landing gear of the present invention;

FIG. 6 is a schematic structural diagram of a second embodiment of the present invention;

fig. 7 is a schematic perspective view of a second ejection mechanism according to an embodiment of the present invention when an unmanned aerial vehicle arm is deployed;

FIG. 8 is an enlarged view of a portion of FIG. 7;

fig. 9 is a schematic perspective view of a second ejection mechanism according to an embodiment of the present invention when retracting an arm of an unmanned aerial vehicle;

FIG. 10 is an enlarged view of a portion of FIG. 9;

FIG. 11 is a schematic view of a second embodiment of the present invention with the fairing removed;

FIG. 12 is a schematic view of the bottom support plate and the top support plate connected to four cylindrical rods according to the second embodiment of the present invention;

FIG. 13 is a schematic view of the structure of the auxiliary device for barrel firing according to the present invention;

the reference numerals in the figures have the following meanings:

1-bottom support plate, 2-top support plate, 3-cylindrical rod body, 4-top fairing, 5-body fairing, 6-battery, 7-unmanned aerial vehicle power component, 8-unmanned aerial vehicle horn, 9-unmanned aerial vehicle avionics system, 10-battery retainer, 101-radio mechanism, 11-motor, 12-lead screw, 13-connector, 14-hinge block, 15-rotating arm, 16-sleeve, 17-rib plate, 18-lower support plate, 19-upper support plate, 201-radio mechanism, 21-linear steering engine, 22-catch plate, 23-folder, 24-positioning plate, 25-motion groove, 26-positioning groove, 27-connecting plate, 28-spring, 29-fixing piece, 211-center plate, 212-rotating shaft, 213-clamping piece, 214-guide hole, 215-spring positioning pin, 216-manual deflector rod, 31-mounting hole, 41-base, 42-pillar, 43-support frame, 51-intermediate plate, 52-guide pillar and 61-four-point landing gear.

Detailed Description

The invention is described in detail below with reference to the figures and the embodiments.

Example one

As shown in fig. 1-5, the present embodiment is a foldable barrel-type multi-rotor unmanned aerial vehicle, which includes a bottom support plate 1 and a top support plate 2, four cylindrical rods 3 are connected between the bottom support plate 1 and the top support plate 2, the four cylindrical rods 3 are circumferentially arranged, and in practical application, a plurality of cylindrical rods 3 may also be connected between the bottom support plate 1 and the top support plate 2; an unmanned aerial vehicle avionics system 9 is mounted on the top supporting plate 2, a battery 6 for supplying power to the unmanned aerial vehicle avionics system 9 is mounted on the bottom supporting plate 1, a horn action assembly is arranged between the bottom supporting plate 1 and the top supporting plate 2, the horn action assembly is fixedly connected with the four cylindrical rod bodies 3, four unmanned aerial vehicle horns 8 are arranged on the horn action assembly, an unmanned aerial vehicle power assembly 7 electrically connected with the unmanned aerial vehicle avionics system 9 is arranged on the unmanned aerial vehicle horn 8, the unmanned aerial vehicle power assembly 7 comprises a driving motor, a motor base and a propeller, the driving motor is mounted on the unmanned aerial vehicle horn 8 through the motor base, and the propeller is mounted on an output shaft of the driving motor; the arm action component is a retraction mechanism 101 for automatically retracting and releasing the arm; when in actual use, also can set up a plurality of unmanned aerial vehicle horn 8 on the horn action subassembly, as long as can with many cylindrical rod body 3 cooperations can.

The retracting mechanism 101 of the automatic retracting arm in this embodiment includes a lower support plate 18, an upper support plate 19, a motor 11, a lead screw 12 and a connector 13; four mounting holes 31 used for being connected with four cylindrical rod bodies 3 are respectively formed on the lower supporting plate 18 and the upper supporting plate 19, and the lower supporting plate 18 and the upper supporting plate 19 are respectively connected with the cylindrical rod bodies 3 through the mounting holes 31; the motor 11 is arranged at the top of the lower supporting plate 18, a hole is formed in the middle of the upper supporting plate 19, four rib plates 17 are circumferentially arranged at the top of the upper supporting plate 19, the four rib plates 17 are vertically arranged, and the tops of the four rib plates 17 are connected together; in practical application, a plurality of rib plates 17 can be circumferentially arranged on the top of the upper supporting plate 19; the screw 12 is vertically arranged between the lower supporting plate 18 and the upper supporting plate 19, the bottom end of the screw 12 is in transmission connection with an output shaft of the motor 11, and the top end of the screw 12 penetrates through a hole in the middle of the upper supporting plate 19 and then is rotatably connected to the top connection parts of the four rib plates 17; the connector 13 is in threaded connection with the screw rod 12, the connector 13 is connected with four first execution components, the four first execution components are arranged circumferentially, the first execution components comprise a hinge block 14, a rotating arm 15 and a sleeve 16, the tail end of the hinge block 14 is hinged to the connector 13, the head end of the hinge block 14 is hinged to the tail end of the rotating arm 15, the head end of the rotating arm 15 is rigidly connected with the outer circumferential surface of the sleeve 16, and the sleeve 16 is hinged to the edge of the upper support plate 19 towards the top of the end surface of the upper support plate 19; the end part of the sleeve 16 far away from the upper supporting plate 19 is connected with the unmanned aerial vehicle arm 8; one end of the unmanned aerial vehicle horn 8 is inserted in the sleeve 16 and fixedly connected with the sleeve 16, and the other end of the unmanned aerial vehicle horn 8 is used for installing the unmanned aerial vehicle power assembly 7.

In this embodiment, the head end of the hinge block 14 is a U-shaped structure, and the tail end of the rotating arm 15 is hinged in the U-shaped structure at the head end of the hinge block 14; the tail end of the rotating arm 15 is better connected with the head end of the hinge block 14 in a rotating way; two arm bodies are formed at the head end of the rotating arm 15, the end parts of the two arm bodies are respectively bent by 90 degrees and then are rigidly connected with the outer circumferential surface of the sleeve 16, and the bending directions of the end parts of the two arm bodies are consistent; the head end of the rotating arm 15 and the outer circumferential surface of the sleeve 16 are connected rigidly, and the rotating angle of the unmanned aerial vehicle arm 8 is improved when the unmanned aerial vehicle arm is retracted.

The unmanned aerial vehicle arm fixing frame comprises a battery fixing frame 10, wherein the battery fixing frame 10 is connected with four cylindrical rod bodies 3, a through hole for a battery 6 to penetrate through is formed in the middle of the battery fixing frame 10, and a groove structure for accommodating an unmanned aerial vehicle arm 8 is formed in the edge of the battery fixing frame 10 between every two adjacent cylindrical rod bodies 3; the battery fixing frame 10 is used for connecting the battery 6 with the four cylindrical rod bodies 3, so that the structural stability of the battery 6 after installation is improved; the groove structure at the edge of the battery fixing frame 10 is used for limiting the unmanned aerial vehicle arm 8 in a contraction state.

In the present embodiment, a four-point undercarriage 61 is attached to the outer circumferential surface of the bottom support plate 1; when the unmanned aerial vehicle takes off on the ground, the unmanned aerial vehicle can take off on the ground independently.

In practical application of the present embodiment, an auxiliary device for barrel launching may also be disposed at the bottom of the bottom support plate 1, as shown in fig. 13, the auxiliary device for barrel launching includes a base 41, a plurality of pillars 42 are vertically disposed at the top of the base 41, the plurality of pillars 42 are circumferentially arranged, a support frame 43 is connected between the plurality of pillars 42, a conical structure is formed at the top end of the pillars 42, and the top ends of the plurality of pillars 42 are in movable contact with the bottom ends of the plurality of cylindrical rod bodies 3 on the bottom support plate 1; the gun barrel launching auxiliary device is used for bearing the instantaneous overload force of gun barrel launching, and after launching, the gun barrel launching auxiliary device automatically falls off.

In the present embodiment, a top fairing 4 is mounted on the top support plate 2; in practical application, the machine body fairing 5 can be sleeved on the periphery of the four cylindrical rod bodies 3, and an opening for the unmanned aerial vehicle arm 8 to pass through is formed in the machine body fairing 5; top radome fairing 4 and organism radome fairing 5 make the unmanned aerial vehicle appearance accord with the aerodynamic design, the air resistance when reducing unmanned aerial vehicle flight.

The working principle of the embodiment is as follows:

the multi-rotor unmanned aerial vehicle body is of a cylindrical structure and is composed of a bottom supporting plate 1, a top supporting plate 2 and four cylindrical rod bodies 3, and a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body and is a retraction mechanism 101 for automatically retracting and releasing a horn; the battery 6 supplies power to the unmanned aerial vehicle avionics system 9, the unmanned aerial vehicle avionics system 9 controls the action of the release mechanism 101, and meanwhile, the unmanned aerial vehicle avionics system 9 also controls the unmanned aerial vehicle power assembly 7 to work; when the unmanned aerial vehicle power assembly 7 works, the multi-rotor unmanned aerial vehicle body is driven to fly, and a task load is mounted on the bottom supporting plate 1; when the unmanned aerial vehicle arm 8 is unfolded, the unmanned aerial vehicle avionics system 9 controls a motor 11 of a retraction mechanism 101 to drive a screw rod 12 to rotate, so that a connector 13 on the screw rod 12 moves downwards along the axial direction of the screw rod 12, and the connector 13 drives the unmanned aerial vehicle arm 8 to rotate upwards along the axial direction of the edge of a supporting plate 19 above the unmanned aerial vehicle arm 8 through a hinge block 14, a rotating arm 15 and a sleeve 16, so that the unmanned aerial vehicle arm 8 is automatically unfolded; when the unmanned aerial vehicle arm 8 is retracted, the unmanned aerial vehicle avionics system 9 controls a motor 11 of a retraction mechanism 101 to drive a screw rod 12 to rotate, so that a connector 13 on the screw rod 12 moves upwards along the axial direction of the screw rod 12, the connector 13 drives the unmanned aerial vehicle arm 8 to rotate downwards along the axial direction of the edge of a supporting plate 19 above the unmanned aerial vehicle arm 8 through a hinge block 14, a rotating arm 15 and a sleeve 16, and automatic retraction of the unmanned aerial vehicle arm 8 is realized; during the retraction of the unmanned aerial vehicle arm 8, the hinge block 14 and the rotating arm 15 penetrate through the upper support plate 19 from the hole of the upper support plate 19; therefore, the multi-rotor unmanned aerial vehicle can automatically expand and contract the arms, can quickly enter a working state and be quickly recovered and stored in a box, does not need manual intervention, and is very convenient; the multi-rotor unmanned aerial vehicle can be stored in a long straight cylinder after the arm is retracted, and is convenient to store and carry; the retraction mechanism is controlled by an avionic system of the multi-rotor unmanned aerial vehicle to work, and action tasks are completed independently.

Example two

As shown in fig. 6-13, the present embodiment is a foldable barrel-type multi-rotor unmanned aerial vehicle, which includes a bottom support plate 1 and a top support plate 2, wherein four cylindrical rods 3 are connected between the bottom support plate 1 and the top support plate 2, the four cylindrical rods 3 are circumferentially arranged, and in practical application, a plurality of cylindrical rods 3 may also be connected between the bottom support plate 1 and the top support plate 2; an unmanned aerial vehicle avionics system 9 is mounted on the top supporting plate 2, a battery 6 for supplying power to the unmanned aerial vehicle avionics system 9 is mounted on the bottom supporting plate 1, a horn action assembly is arranged between the bottom supporting plate 1 and the top supporting plate 2, the horn action assembly is fixedly connected with the four cylindrical rod bodies 3, four unmanned aerial vehicle horns 8 are arranged on the horn action assembly, an unmanned aerial vehicle power assembly 7 electrically connected with the unmanned aerial vehicle avionics system 9 is arranged on the unmanned aerial vehicle horn 8, the unmanned aerial vehicle power assembly 7 comprises a driving motor, a motor base and a propeller, the driving motor is mounted on the unmanned aerial vehicle horn 8 through the motor base, and the propeller is mounted on an output shaft of the driving motor; the arm action assembly is a pop-up mechanism 201 which automatically unfolds the arm; when in actual use, also can set up a plurality of unmanned aerial vehicle horn 8 on the horn action subassembly, as long as can with many cylindrical rod body 3 cooperations can.

In this embodiment, the ejection mechanism 201 of the automatic unfolding arm includes a central disc 211, four mounting holes 31 for connecting with four cylindrical rod bodies 3 are formed on the central disc 211, and the central disc 211 is connected with the cylindrical rod bodies 3 through the mounting holes 31; a linear steering engine 21 is arranged in the middle of the central disc 211, the execution end of the linear steering engine 21 is vertically downward, and a clamping disc 22 is arranged at the end part of the execution end of the linear steering engine 21; the central disc 211 is provided with four second executing assemblies which are circumferentially arranged, each second executing assembly comprises a folding piece 23, a spring 28 and a clamping piece 213, the folding piece 23 is connected with the unmanned aerial vehicle arm 8, the clamping piece 213 is fixedly sleeved on the outer circumferential surface of the head end of the folding piece 23, a connecting plate 27 is formed on the outer circumferential surface of the folding piece 23, the top of the central disc 211 is provided with a fixing piece 29, one end of the spring 28 is connected with the connecting plate 27, and the other end of the spring 28 is connected with the fixing piece 29; two positioning plates 24 are formed at the top of the end face of the tail end of the folding piece 23, the two positioning plates 24 are hinged with the edge of the central disc 211 through a rotating shaft 212, notches for accommodating the two positioning plates 24 are formed at the edge of the central disc 211, spring positioning pins 215 are respectively arranged on the central discs 211 at two sides of the two positioning plates 24, the two spring positioning pins 215 are oppositely arranged, moving grooves 25 with arc structures are respectively formed on the outer side faces of the two positioning plates 24 facing the two spring positioning pins 215, the pin heads of the two spring positioning pins 215 respectively slide in the moving grooves 25 formed on the outer side faces of the two positioning plates 24, and a positioning groove 26 is formed at the stroke end of each moving groove 25; when the spring 28 pulls the folding member 23 to rotate to the horizontal position around the rotating shaft 212, the pin heads of the two spring positioning pins 215 are inserted into the two positioning grooves 26, respectively.

The second actuating assembly of the embodiment comprises two springs 28, and the connecting plate 27 on the folding member 23 is connected with a fixed member 29 through the two springs 28; spring positioning pin 215 has a manual lever 216; an intermediate plate 51 is arranged below the clamping disc 22, the intermediate plate 51 is connected with the four cylindrical rod bodies 3, a guide post 52 is arranged at the top of the intermediate plate 51, and a guide hole 214 matched with the guide post 52 is formed in the clamping disc 22; the middle plate 51 can improve the connection stability between the plurality of cylindrical rod bodies 3, and the guide columns 52 play a role in guiding the clamping disc 22.

The unmanned aerial vehicle arm fixing frame comprises a battery fixing frame 10, wherein the battery fixing frame 10 is connected with four cylindrical rod bodies 3, a through hole for a battery 6 to penetrate through is formed in the middle of the battery fixing frame 10, and a groove structure for accommodating an unmanned aerial vehicle arm 8 is formed in the edge of the battery fixing frame 10 between every two adjacent cylindrical rod bodies 3; the battery fixing frame 10 is used for connecting the battery 6 with the four cylindrical rod bodies 3, so that the structural stability of the battery 6 after installation is improved; the groove structure at the edge of the battery fixing frame 10 is used for limiting the unmanned aerial vehicle arm 8 in a contraction state.

In the embodiment, the gun barrel launching auxiliary device is arranged at the bottom of the bottom supporting plate 1 and comprises a base 41, four supporting columns 42 are vertically arranged at the top of the base 41, the four supporting columns 42 are circumferentially arranged, supporting frames 43 are connected among the four supporting columns 42, a conical body structure is formed at the top ends of the supporting columns 42, and the top ends of the four supporting columns 42 are in movable contact with the bottom ends of the four cylindrical rod bodies 3 on the bottom supporting plate 1; the gun barrel launching auxiliary device is used for bearing the instantaneous overload force of gun barrel launching, and the gun barrel launching auxiliary device automatically falls off after launching; other numbers of struts 42 may be provided in practice.

In practical applications, the embodiment may further include a four-point landing gear 61 attached to the outer circumferential surface of the bottom support plate 1; when the unmanned aerial vehicle takes off on the ground, the unmanned aerial vehicle can take off on the ground independently.

In the embodiment, a top fairing 4 is arranged on a top support plate 2, an organism fairing 5 is sleeved on the periphery of four cylindrical rod bodies 3, and an opening for an unmanned aerial vehicle arm 8 to pass through is formed on the organism fairing 5; top radome fairing 4 and organism radome fairing 5 make the unmanned aerial vehicle appearance accord with the aerodynamic design, the air resistance when reducing unmanned aerial vehicle flight.

The working principle of the embodiment is as follows:

the multi-rotor unmanned aerial vehicle body is of a cylindrical structure and is composed of a bottom supporting plate 1, a top supporting plate 2 and four cylindrical rod bodies 3, and a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body and is an ejection mechanism 201 for automatically unfolding a horn; the battery 6 supplies power to the unmanned aerial vehicle avionic system 9, the unmanned aerial vehicle avionic system 9 controls the catapult mechanism 201 to act, and meanwhile, the unmanned aerial vehicle avionic system 9 also controls the unmanned aerial vehicle power assembly 7 to work; when the unmanned aerial vehicle power assembly 7 works, the multi-rotor unmanned aerial vehicle body is driven to fly, and a task load is mounted on the bottom supporting plate 1; when the unmanned aerial vehicle arm 8 is contracted, the clamping piece 213 on the folding piece 23 is clamped on the clamping disc 22, at the moment, the unmanned aerial vehicle arm 8 is in a vertical state, and the spring 28 is pulled by the connecting plate 27 on the folding piece 23 to generate elastic potential energy; the unmanned aerial vehicle arm 8 is folded, contracted and restrained by the ejection mechanism 201, so that the multi-rotor unmanned aerial vehicle is conveniently arranged in the launch canister, the occupied space is small, and the carrying is convenient; after the multi-rotor unmanned aerial vehicle is launched from the launching tube through the launching mechanism, the gun tube launching auxiliary device is separated from the gun tube launching auxiliary device; the unmanned aerial vehicle avionics system 9 controls the linear steering engine 21 of the ejection mechanism 201, so that the execution end of the linear steering engine 21 drives the clamping disc 22 to do downward linear motion, the clamping piece 213 on the folding piece 23 is separated from the clamping disc 22, the folding piece 23 is pulled by the elastic force of the spring 28 to rotate upwards quickly by taking the rotating shaft 212 as an axis, in the process, the pin head of the spring positioning pin 215 slides along the moving groove 25 in the moving groove 25 on the positioning plate 24, the elastic potential energy of the spring 28 is gradually reduced, when the spring 28 pulls the folding piece 23 to rotate to a horizontal position by taking the rotating shaft 212 as an axis, the pin head of the spring positioning pin 215 is inserted into the positioning groove 26 to realize positioning and locking, at the moment, the unmanned aerial vehicle arm 8 is unfolded, the unmanned aerial vehicle arm 8 is in a horizontal state, and the unmanned aerial vehicle avionics system 9 controls; the multi-rotor unmanned aerial vehicle has the advantages that the arms of the multi-rotor unmanned aerial vehicle can be quickly and automatically unfolded and locked, so that the multi-rotor unmanned aerial vehicle can quickly enter a working state, and the use requirement that the multi-rotor unmanned aerial vehicle needs to be quickly deployed when troops fight is met by matching with soldiers; after the unmanned aerial vehicle power assembly 7 stops working, the spring positioning pin 215 is shifted through the manual shift lever 216, the pin head of the spring positioning pin 215 is moved out of the positioning groove 26, the folding piece 23 is rotated through the unmanned aerial vehicle arm 8, the folding piece 23 rotates downwards by taking the rotating shaft 212 as the axial direction, the spring 28 is pulled by the connecting plate 27 on the folding piece 23, after all the unmanned aerial vehicle arms 8 are in the vertical state, the unmanned aerial vehicle avionics system 9 controls the linear steering engine 21 of the ejection mechanism 201, the execution end of the linear steering engine 21 drives the clamping disc 22 to move upwards and linearly, the clamping piece 213 on the folding piece 23 is clamped on the clamping disc 22, and therefore the state of the unmanned aerial vehicle arm 8 is recovered to be contracted.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and 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 thus, are not to be construed as limiting the present invention; furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can be, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed; can be mechanically or electrically connected; the two elements can be directly connected, indirectly connected through an intermediate medium, or communicated with each other inside; the specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the description herein, reference to the description of the terms "one embodiment," "some embodiments," "an example," "a specific example," "some examples," or "practical application" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention; in this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example; furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The foregoing shows and describes the general principles, principal features and advantages of the invention; it should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by using equivalent alternatives or equivalent variations fall within the scope of the present invention.