CN112591074B - Foldable barrel type multi-rotor unmanned aerial vehicle - Google Patents
Foldable barrel type multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN112591074B CN112591074B CN202110017573.5A CN202110017573A CN112591074B CN 112591074 B CN112591074 B CN 112591074B CN 202110017573 A CN202110017573 A CN 202110017573A CN 112591074 B CN112591074 B CN 112591074B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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Abstract
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 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 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 avionics system is arranged on the unmanned aerial vehicle horns, and the horn action assembly is a retraction mechanism of an automatic retraction horn or a spring retraction mechanism of the automatic retraction horn; the multi-rotor unmanned aerial vehicle can be enabled to enter a working state quickly and be recovered and put into a box for storage quickly, and is convenient to store and carry; after the multi-rotor unmanned aerial vehicle is launched from the launching barrel through the launching mechanism, the horn of the multi-rotor unmanned aerial vehicle can be quickly and automatically unfolded and locked to match with soldiers for combat.
Description
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 large space when being stored, is inconvenient to carry, the retraction arms are realized by manual work, great inconvenience is brought to users, 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 is time-consuming and labor-consuming; after the use, the arm is manually contracted and then can be put into the storage box, which is extremely inconvenient; particularly, when troops combat, 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 can be matched with soldiers for combat; however, the existing multi-rotor unmanned aerial vehicle cannot meet the use requirement.
Disclosure of Invention
The invention aims at solving the problems in the prior art and provides a foldable cylinder type multi-rotor unmanned aerial vehicle, which comprises a multi-rotor unmanned aerial vehicle body with a cylinder structure formed by a bottom supporting plate, a top supporting plate and a plurality of cylinder rods, wherein a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body and is a retraction mechanism of an automatic retraction horn or a spring and release mechanism of an automatic retraction horn; the retraction mechanism can enable the multi-rotor unmanned aerial vehicle to automatically extend and retract the horn, so that the multi-rotor unmanned aerial vehicle can quickly enter a working state and be quickly recycled into a box for storage, manual intervention is not needed, and the multi-rotor unmanned aerial vehicle is very convenient and fast; the multi-rotor unmanned aerial vehicle can be placed into a long straight cylinder for storage after the arm is contracted, so that the multi-rotor unmanned aerial vehicle is convenient to store and carry; the elastic release mechanism can enable the horn of the multi-rotor unmanned aerial vehicle to be folded, contracted and restrained, so that the multi-rotor unmanned aerial vehicle is conveniently arranged in the transmitting cylinder, the occupied space is small, and the multi-rotor unmanned aerial vehicle is convenient to carry; after the multi-rotor unmanned aerial vehicle is launched from the launching barrel through the launching mechanism, the horn of the multi-rotor unmanned aerial vehicle can be quickly and automatically unfolded and locked, so that the multi-rotor unmanned aerial vehicle can be quickly enter into a working state, and the multi-rotor unmanned aerial vehicle is matched with soldier combat, so that the use requirement of quickly deploying the multi-rotor unmanned aerial vehicle when combat is met.
In order to achieve the above object, the present invention adopts the following technical scheme:
the utility model provides a many rotor unmanned aerial vehicle of collapsible cylinder, includes bottom sprag board and top backup pad, be connected with many cylinder body of rod between bottom sprag board and the top backup pad, many cylinder body of rod are circumference and arrange, install unmanned aerial vehicle avionics system in the top backup pad, install the battery that is used for supplying power for unmanned aerial vehicle avionics system in the bottom sprag board, be provided with horn action subassembly between bottom sprag board and the top backup pad, horn action subassembly and many cylinder body fixed connection, be provided with a plurality of unmanned aerial vehicle horn on the horn action subassembly, be provided with the unmanned aerial vehicle power module who is connected with unmanned aerial vehicle avionics system electricity on the unmanned aerial vehicle horn, unmanned aerial vehicle power module includes driving motor, motor cabinet and screw, driving motor installs on unmanned aerial vehicle horn through the motor cabinet, the screw is installed on driving motor's output shaft; the arm action assembly is a retracting mechanism of an automatic retracting arm or a bouncing mechanism of the automatic retracting arm.
As a further preferred aspect of the present invention, the retracting mechanism of the automatic retracting arm includes a lower support plate, an upper support plate, a motor, a screw, and a connector; the lower support plate and the upper support plate are respectively provided with a plurality of mounting holes for connecting with a plurality of cylindrical rod bodies, and are respectively connected with the cylindrical rod bodies through the mounting holes; the motor is arranged 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 at the top of the upper supporting plate, the rib plates are vertically arranged and connected together at the top of the rib plates, the screw rod is vertically arranged between the lower supporting plate and the upper supporting plate, the bottom end of the screw rod is in transmission connection with an output shaft of the motor, and the top end of the screw rod is rotationally connected to the connection position of the top of the rib plates after passing through the hole in the middle of the upper supporting plate; the connector is in threaded connection with the screw rod, a plurality of first execution components are connected to the connector and are arranged circumferentially, the first execution components comprise a hinging block, a rotating arm and a sleeve, the tail end of the hinging block is hinged with the connector, the head end of the hinging block is hinged with 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 with the edge of the upper support plate towards the top of the end face of the upper support plate; the sleeve pipe is kept away from the end connection unmanned aerial vehicle horn of last backup pad.
As a further preferable mode of the invention, the head end of the hinging block is of a U-shaped structure, and the tail end of the rotating arm is hinged in the U-shaped structure of the head end of the hinging block; the tail end of the rotating arm is better rotationally connected with the head end of the hinging block.
As a further preferred aspect of the present invention, the first end of the rotating arm is formed with two arms, the ends of the two arms are respectively bent for 90 degrees and then rigidly connected to the outer circumferential surface of the sleeve, and the bending directions of the ends of the two arms are consistent; the head end of the rotating arm is convenient to rigidly connect with the outer circumferential surface of the sleeve, and meanwhile, the rotating angle of the unmanned aerial vehicle arm is improved when the unmanned aerial vehicle arm is contracted.
As a further preferred aspect of the present invention, the spring and release mechanism of the automatic expanding arm includes a central disc, on which a plurality of mounting holes for connecting with a plurality of cylindrical rods are formed, and the central disc is connected with the cylindrical rods through the mounting holes; the middle part of the central disc is provided with a linear steering engine, the execution end of the linear steering engine is vertically downward, and the end part of the execution end of the linear steering engine is provided with a clamping disc; the device comprises a central disc, a first execution assembly, a second execution assembly, a spring and a clamping piece, wherein the first execution assembly is arranged on the central disc, the second execution assembly is arranged in the circumferential direction, the first execution assembly comprises a folding piece, a spring and the clamping piece, the folding piece is connected with an 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; two positioning plates are formed at the top of the end face of the tail end of the folding piece, the two positioning plates are hinged with the edge of the central disc through a rotating shaft, notches for accommodating the two positioning plates are formed at the edge of the central disc, spring positioning pins are respectively arranged on the central discs on two sides of the two positioning plates, the two spring positioning pins are oppositely arranged, movement 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 slide in the movement grooves formed on the outer side faces of the two positioning plates respectively, and positioning grooves are formed at the stroke tail end of each movement groove; when the spring pulls the folding piece to rotate to the horizontal position by taking the rotating shaft as the 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; a middle plate is arranged below the clamping disc, the middle plate is connected with a plurality of cylindrical rods, a guide column is arranged at the top of the middle plate, and a guide hole matched with the guide column is formed in the clamping disc; the intermediate plate can improve the connection stability between the cylindrical rods, and the guide column plays a role in guiding the clamping disc.
As a further preferred mode 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 rods, a through hole for a power supply 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 formed at the edge of the battery fixing frame between two adjacent cylindrical rods; the battery fixing frame is used for connecting the battery with the cylindrical rods, so that the structural stability of the battery after being installed is improved; the groove structure at the edge of the battery fixing frame is used for limiting the unmanned aerial vehicle arm in a contracted state.
As a further preferred mode of the invention, a barrel launching auxiliary device is arranged at the bottom of the bottom supporting plate, the barrel launching auxiliary device comprises a base, a plurality of supporting columns are vertically arranged at the top of the base, the supporting columns are circumferentially arranged, a supporting frame is connected between the supporting columns, a conical 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 the cylindrical rods on the bottom supporting plate; the gun barrel launching auxiliary device is used for bearing instant overload force of gun barrel launching, and after the gun barrel launching auxiliary device automatically drops off.
As a further preferred aspect of the present invention, a four-point landing gear is attached to the outer circumferential surface of the bottom support plate; the unmanned aerial vehicle is convenient to realize ground autonomous take-off when the unmanned aerial vehicle needs ground take-off.
As a further preferable mode of the invention, a top fairing is arranged on the top supporting plate, a body fairing is sleeved on the periphery of the plurality of cylindrical rod bodies, and an opening for the unmanned aerial vehicle arm to pass through is formed in the body fairing; the top fairing and the organism fairing make the unmanned aerial vehicle appearance accord with aerodynamic design, reduce the air resistance when unmanned aerial vehicle flies.
The invention has the advantages that:
the multi-rotor unmanned aerial vehicle body with a cylinder structure is formed by a bottom supporting plate, a top supporting plate and a plurality of cylinder rods, and a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body and is a retraction mechanism of an automatic retraction horn or a spring mechanism of an automatic retraction horn; the retraction mechanism can enable the multi-rotor unmanned aerial vehicle to automatically extend and retract the horn, so that the multi-rotor unmanned aerial vehicle can quickly enter a working state and be quickly recycled into a box for storage, manual intervention is not needed, and the multi-rotor unmanned aerial vehicle is very convenient and fast; the multi-rotor unmanned aerial vehicle can be placed into a long straight cylinder for storage after the arm is contracted, so that the multi-rotor unmanned aerial vehicle is convenient to store and carry; the elastic release mechanism can enable the horn of the multi-rotor unmanned aerial vehicle to be folded, contracted and restrained, so that the multi-rotor unmanned aerial vehicle is conveniently arranged in the transmitting cylinder, the occupied space is small, and the multi-rotor unmanned aerial vehicle is convenient to carry; after the multi-rotor unmanned aerial vehicle is launched from the launching barrel through the launching mechanism, the horn of the multi-rotor unmanned aerial vehicle can be quickly and automatically unfolded and locked, so that the multi-rotor unmanned aerial vehicle can be quickly enter into a working state, and the multi-rotor unmanned aerial vehicle is matched with soldier combat, so that the use requirement of quickly deploying the multi-rotor unmanned aerial vehicle when combat is met.
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 jack according to an embodiment of the present invention when the retraction jack deploys the arm of the unmanned aerial vehicle;
fig. 3 is a schematic perspective view of a retraction jack according to an embodiment of the present invention when the retraction jack retracts a boom of the unmanned aerial vehicle;
FIG. 4 is an exploded view of a jack structure according to an embodiment of the present invention;
FIG. 5 is a schematic view of the attachment of the bottom support plate to a four-point landing gear of the present invention;
FIG. 6 is a schematic diagram of a second embodiment of the present invention;
fig. 7 is a schematic perspective view of a second flick mechanism in the 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 spring mechanism according to an embodiment of the present invention when the unmanned aerial vehicle arm is retracted;
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 cowling removed;
FIG. 12 is a schematic view of a second bottom support plate and top support plate connected to four cylindrical rods in accordance with an embodiment of the present invention;
FIG. 13 is a schematic view of the barrel firing aid of the present invention;
the meaning of the reference numerals in the figures is as follows:
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 fixed frame, 101-retraction mechanism, 11-motor, 12-lead screw, 13-connector, 14-hinged block, 15-rotary arm, 16-sleeve, 17-rib plate, 18-bottom support plate, 19-upper support plate, 201-ejection mechanism, 21-linear steering engine, 22-clamping disc, 23-folding piece, 24-positioning plate, 25-movement groove, 26-positioning groove, 27-connecting plate, 28-spring, 29-fixing piece, 211-center disc, 212-rotary shaft, 213-clamping piece, 214-guiding hole, 215-spring positioning pin, 216-manual deflector rod, 31-mounting hole, 41-base, 42-supporting post, 43-supporting frame, 51-middle plate, 52-guiding post, 61-four-landing gear.
Detailed Description
The invention is described in detail below with reference to the drawings and the specific embodiments.
Example 1
As shown in fig. 1-5, the embodiment is a foldable barrel type multi-rotor unmanned aerial vehicle, which comprises a bottom supporting plate 1 and a top supporting plate 2, wherein four cylindrical rod bodies 3 are connected between the bottom supporting plate 1 and the top supporting plate 2, the four cylindrical rod bodies 3 are circumferentially arranged, and a plurality of cylindrical rod bodies 3 can be connected between the bottom supporting plate 1 and the top supporting plate 2 in actual application; the unmanned aerial vehicle avionics system 9 is arranged on the top supporting plate 2, the battery 6 for supplying power to the unmanned aerial vehicle avionics system 9 is arranged on the bottom supporting plate 1, the horn action assembly is fixedly connected with the four cylindrical rod bodies 3 and is fixedly connected with the bottom supporting plate 1 and the top supporting plate 2, four unmanned aerial vehicle arms 8 are arranged on the horn action assembly, the unmanned aerial vehicle power assembly 7 electrically connected with the unmanned aerial vehicle avionics system 9 is arranged on the unmanned aerial vehicle arms 8, the unmanned aerial vehicle power assembly 7 comprises a driving motor, a motor base and a propeller, the driving motor is arranged on the unmanned aerial vehicle arms 8 through the motor base, and the propeller is arranged on an output shaft of the driving motor; the arm action assembly is a retracting mechanism 101 for automatically retracting the arm; in practical application, the horn action assembly can be provided with a plurality of unmanned aerial vehicle horns 8, and the unmanned aerial vehicle horns can be matched with a plurality of cylindrical rods 3.
The retracting mechanism 101 of the automatic retracting arm according to the present embodiment includes a lower support plate 18, an upper support plate 19, a motor 11, a screw 12, and a connector 13; four mounting holes 31 for connecting with the four cylindrical rod bodies 3 are respectively formed on the lower support plate 18 and the upper support plate 19, and the lower support plate 18 and the upper support 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 at the top of the upper supporting plate 19; the screw rod 12 is vertically arranged between the lower support plate 18 and the upper support plate 19, the bottom end of the screw rod 12 is in transmission connection with the output shaft of the motor 11, and the top end of the screw rod 12 penetrates through a hole in the middle of the upper support plate 19 and is rotationally connected to the top connection parts of the four rib plates 17; the connector 13 is in threaded connection with the screw rod 12, four execution components I are connected to the connector 13, the four execution components I are circumferentially arranged, each execution component I comprises a hinging block 14, a rotating arm 15 and a sleeve 16, the tail end of the hinging block 14 is hinged with the connector 13, the head end of the hinging block 14 is hinged with 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 top of the end surface of the sleeve 16 facing the upper support plate 19 is hinged with the edge of the upper support plate 19; the end part of the sleeve 16, which is 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 into 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 component 7.
In this embodiment, the head end of the hinge block 14 is of a U-shaped structure, and the tail end of the rotating arm 15 is hinged in the U-shaped structure of the head end of the hinge block 14; the tail end of the rotating arm 15 is better rotatably connected with the head end of the hinging block 14; the head end of the rotary arm 15 is provided with two arm bodies, the end parts of the two arm bodies are respectively bent for 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 rotary arm 15 is convenient to rigidly connect with the outer circumferential surface of the sleeve 16, and the rotation angle of the unmanned aerial vehicle arm 8 is improved.
The embodiment also comprises a battery fixing frame 10, wherein the battery fixing frame 10 is connected with the four cylindrical rod bodies 3, a through hole for a battery 6 to pass through is formed in the middle of the battery fixing frame 10, and a groove structure for accommodating the unmanned aerial vehicle arm 8 is formed at the edge of the battery fixing frame 10 between 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 being installed 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 contracted state.
The four-point landing gear 61 is connected to the outer circumferential surface of the bottom supporting plate 1; the unmanned aerial vehicle is convenient to realize ground autonomous take-off when the unmanned aerial vehicle needs ground take-off.
In practical application, the bottom of the bottom support plate 1 may also be provided with a barrel launching auxiliary device, as shown in fig. 13, where the barrel launching auxiliary device includes a base 41, a plurality of struts 42 are vertically disposed at the top of the base 41, the plurality of struts 42 are circumferentially arranged, a support frame 43 is connected between the plurality of struts 42, the top ends of the struts 42 are formed with cone structures, and the top ends of the plurality of struts 42 are in movable contact with the bottom ends of a plurality of cylindrical rod bodies 3 on the bottom support plate 1; the gun barrel launching auxiliary device is used for bearing instant overload force of gun barrel launching, and after the gun barrel launching auxiliary device automatically drops off.
The top fairing 4 is arranged on the top supporting plate 2; in practical application, the periphery of the four cylindrical rod bodies 3 can be sleeved with a body fairing 5, and an opening for the unmanned aerial vehicle arm 8 to pass through is formed in the body fairing 5; the top fairing 4 and the body fairing 5 enable the appearance of the unmanned aerial vehicle to conform to aerodynamic design, and air resistance of the unmanned aerial vehicle during flight is reduced.
The working principle of this embodiment is as follows:
a multi-rotor unmanned aerial vehicle body with a barrel structure is formed by a bottom supporting plate 1, a top supporting plate 2 and four cylindrical rod bodies 3, a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body, and the horn action assembly 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 retraction jack 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 the motor 11 of the retraction jack 101 to drive the screw rod 12 to rotate, so that the connector 13 on the screw rod 12 moves downwards along the axial direction of the screw rod 12, and the connector 13 drives the edge of the supporting plate 19 above the unmanned aerial vehicle arm 8 to rotate upwards through the hinging block 14, the rotating arm 15 and the sleeve 16, thereby realizing automatic unfolding of the unmanned aerial vehicle arm 8; when the unmanned aerial vehicle arm 8 is contracted, the unmanned aerial vehicle avionics system 9 controls the motor 11 of the retraction jack 101 to drive the screw rod 12 to rotate, so that the connector 13 on the screw rod 12 moves upwards along the axial direction of the screw rod 12, and the connector 13 drives the edge of the support plate 19 above the unmanned aerial vehicle arm 8 to rotate downwards along the axial direction through the hinging block 14, the rotating arm 15 and the sleeve 16, thereby realizing automatic contraction of the unmanned aerial vehicle arm 8; during the retraction of the unmanned aerial vehicle horn 8, the hinge block 14 and the rotary arm 15 will pass 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 horn, so that the multi-rotor unmanned aerial vehicle can quickly enter a working state and be quickly recycled into a box for storage, manual intervention is not needed, and the multi-rotor unmanned aerial vehicle is very convenient and fast; the multi-rotor unmanned aerial vehicle can be put into a long straight cylinder for storage after the horn is contracted, so that the multi-rotor unmanned aerial vehicle is convenient to store and carry; the retraction jack is controlled by the avionics system of the multi-rotor unmanned aerial vehicle to work, and the action task is automatically completed.
Example two
As shown in fig. 6-13, the embodiment is a foldable barrel type multi-rotor unmanned aerial vehicle, which comprises a bottom support 1 plate and a top support plate 2, wherein four cylindrical rod bodies 3 are connected between the bottom support plate 1 and the top support plate 2, the four cylindrical rod bodies 3 are circumferentially arranged, and a plurality of cylindrical rod bodies 3 can be connected between the bottom support plate 1 and the top support plate 2 in actual application; the unmanned aerial vehicle avionics system 9 is arranged on the top supporting plate 2, the battery 6 for supplying power to the unmanned aerial vehicle avionics system 9 is arranged on the bottom supporting plate 1, the horn action assembly is fixedly connected with the four cylindrical rod bodies 3 and is fixedly connected with the bottom supporting plate 1 and the top supporting plate 2, four unmanned aerial vehicle arms 8 are arranged on the horn action assembly, the unmanned aerial vehicle power assembly 7 electrically connected with the unmanned aerial vehicle avionics system 9 is arranged on the unmanned aerial vehicle arms 8, the unmanned aerial vehicle power assembly 7 comprises a driving motor, a motor base and a propeller, the driving motor is arranged on the unmanned aerial vehicle arms 8 through the motor base, and the propeller is arranged on an output shaft of the driving motor; the arm action assembly is a spring and release mechanism 201 for automatically expanding the arm; in practical application, the horn action assembly can be provided with a plurality of unmanned aerial vehicle horns 8, and the unmanned aerial vehicle horns can be matched with a plurality of cylindrical rods 3.
In this embodiment, the spring and release mechanism 201 of the automatic expanding 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; the middle part of the center plate 211 is provided with a linear steering engine 21, the execution end of the linear steering engine 21 is vertically downward, and the end part of the execution end of the linear steering engine 21 is provided with a clamping plate 22; the center plate 211 is provided with four second execution components which are circumferentially arranged, the second execution components comprise 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 center plate 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; the top of the end face of the tail end of the folding piece 23 is provided with two positioning plates 24, 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 on two sides of the two positioning plates 24, the two spring positioning pins 215 are oppositely arranged, the outer side faces of the two positioning plates 24 facing the two spring positioning pins 215 are respectively provided with a movement groove 25 with an arc structure, the pin heads of the two spring positioning pins 215 respectively slide in the movement 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 movement groove 25; when the spring 28 pulls the folding member 23 to rotate to the horizontal position by taking the rotating shaft 212 as the shaft, the pin heads of the two spring positioning pins 215 are respectively inserted into the two positioning grooves 26.
The second execution assembly of the embodiment comprises two springs 28, and the connecting plate 27 on the folding piece 23 is connected with the fixing piece 29 through the two springs 28; the spring positioning pin 215 has a manual lever 216; a middle plate 51 is arranged below the clamping disc 22, the middle plate 51 is connected with the four cylindrical rod bodies 3, a guide column 52 is arranged at the top of the middle plate 51, and a guide hole 214 matched with the guide column 52 is formed in the clamping disc 22; the intermediate plate 51 can improve the connection stability between the plurality of cylindrical bodies 3, and the guide posts 52 play a role in guiding the positioning plate 22.
The embodiment also comprises a battery fixing frame 10, wherein the battery fixing frame 10 is connected with the four cylindrical rod bodies 3, a through hole for a battery 6 to pass through is formed in the middle of the battery fixing frame 10, and a groove structure for accommodating the unmanned aerial vehicle arm 8 is formed at the edge of the battery fixing frame 10 between 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 being installed 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 contracted state.
In the embodiment, a gun barrel emission auxiliary device is arranged at the bottom of a bottom supporting plate 1, the gun barrel emission auxiliary device comprises a base 41, four support posts 42 are vertically arranged at the top of the base 41, the four support posts 42 are circumferentially arranged, a supporting frame 43 is connected between the four support posts 42, the top ends of the support posts 42 are formed into cone structures, and the top ends of the four support posts 42 are movably contacted with the bottom ends of four cylindrical rod bodies 3 on the bottom supporting plate 1; the gun barrel emission auxiliary device is used for bearing the instant overload force of gun barrel emission, and after the gun barrel emission auxiliary device automatically drops off; other numbers of struts 42 are possible in practice.
In practical application, the four-point landing gear 61 can be connected to the outer circumferential surface of the bottom support plate 1 in the present embodiment; the unmanned aerial vehicle is convenient to realize ground autonomous take-off when the unmanned aerial vehicle needs ground take-off.
In the embodiment, a top fairing 4 is arranged on a top supporting plate 2, a body 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 in the body fairing 5; the top fairing 4 and the body fairing 5 enable the appearance of the unmanned aerial vehicle to conform to aerodynamic design, and air resistance of the unmanned aerial vehicle during flight is reduced.
The working principle of this embodiment is as follows:
a multi-rotor unmanned aerial vehicle body with a barrel structure is formed by a bottom supporting plate 1, a top supporting plate 2 and four cylindrical rod bodies 3, a horn action assembly is arranged on the multi-rotor unmanned aerial vehicle body, and the horn action assembly is a spring-releasing mechanism 201 for automatically expanding 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 flick mechanism 201, 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; in the state of contracting the unmanned aerial vehicle arm 8, the clamping piece 213 on the folding piece 23 is clamped on the clamping disc 22, the unmanned aerial vehicle arm 8 is in a vertical state at this time, 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 spring-releasing mechanism 201, so that the multi-rotor unmanned aerial vehicle is conveniently arranged in the transmitting cylinder, the occupied space is small, and the carrying is convenient; after the multi-rotor unmanned aerial vehicle is launched from the launching barrel through the launching mechanism, the barrel launching auxiliary device is separated from the launching barrel; the unmanned aerial vehicle avionics system 9 controls the linear steering engine 21 of the spring releasing mechanism 201, the actuating end of the linear steering engine 21 drives the clamping disc 22 to move linearly downwards, the clamping piece 213 on the folding piece 23 is separated from the clamping disc 22, the folding piece 23 is pulled by the spring 28 to rotate upwards rapidly by taking the rotating shaft 212 as an axis, in the process, the pin head of the spring positioning pin 215 slides in the moving groove 25 on the positioning plate 24 along the moving groove 25, 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, and the unmanned aerial vehicle avionics system 9 controls the unmanned aerial vehicle power component 7 to start working in a horizontal state; the horn 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 operating requirements of the multi-rotor unmanned aerial vehicle for quick deployment in the combat of troops are met by matching with the combat of soldiers; after the unmanned aerial vehicle power component 7 stops working, the spring positioning pin 215 is stirred through the manual deflector 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 is rotated downwards by taking the rotating shaft 212 as the axis, the connecting plate 27 on the folding piece 23 pulls the spring 28, after all 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 elastic releasing mechanism 201, the actuating end of the linear steering engine 21 drives the clamping disc 22 to move linearly upwards, and the clamping piece 213 on the folding piece 23 is clamped on the clamping disc 22, so that the state of the unmanned aerial vehicle arm 8 is restored to the contracted state.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention; furthermore, the terms "first," "second," and the like, 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 explicitly specified and limited otherwise, the terms "mounted," "connected," and "configured" are to be construed broadly and may be, for example, fixedly connected, configured, detachably connected, configured, or integrally connected and configured; can be mechanically or electrically connected; can be directly connected, can also be indirectly connected through an intermediate medium, and can also be the communication between the two elements; the specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the description of the present specification, descriptions of terms "one embodiment," "some embodiments," "examples," "specific examples," "some examples," or "practical applications," etc., mean 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 present invention; in this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples; 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 has shown and described the basic principles, principal features and advantages of the invention; it will be appreciated by persons skilled in the art that the above embodiments are not intended to limit the invention in any way, and that all technical solutions obtained by means of equivalent substitutions or equivalent transformations fall within the scope of the invention.
Claims (9)
1. A collapsible cylinder many rotor unmanned aerial vehicle, its characterized in that: the 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 arranged in the circumferential direction, an unmanned aerial vehicle avionics system is installed on the top supporting plate, a battery for supplying power to the unmanned aerial vehicle avionics system is installed on the bottom supporting plate, a horn action assembly is arranged between the bottom supporting plate and the top supporting plate, the horn action assembly is fixedly connected with the plurality of cylindrical rod bodies, a plurality of unmanned aerial vehicle arms are arranged on the horn action assembly, an unmanned aerial vehicle power assembly electrically connected with the unmanned aerial vehicle avionics system is arranged on the unmanned aerial vehicle arms, the unmanned aerial vehicle power assembly comprises a driving motor, a motor seat and a propeller, the driving motor is installed on the unmanned aerial vehicle arms through the motor seat, and the propeller is installed on an output shaft of the driving motor; the arm action assembly is a retracting mechanism of an automatic retracting arm or a bouncing mechanism of the automatic retracting arm;
the spring and release mechanism of the automatic unfolding arm comprises a central disc, wherein a plurality of mounting holes for being connected with a plurality of cylindrical rods are formed in the central disc, and the central disc is connected with the cylindrical rods through the mounting holes; the middle part of the central disc is provided with a linear steering engine, the execution end of the linear steering engine is vertically downward, and the end part of the execution end of the linear steering engine is provided with a clamping disc; the device comprises a central disc, a first execution assembly, a second execution assembly, a spring and a clamping piece, wherein the first execution assembly is arranged on the central disc, the second execution assembly is arranged in the circumferential direction, the first execution assembly comprises a folding piece, a spring and the clamping piece, the folding piece is connected with an 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; two positioning plates are formed at the top of the end face of the tail end of the folding piece, the two positioning plates are hinged with the edge of the central disc through a rotating shaft, notches for accommodating the two positioning plates are formed at the edge of the central disc, spring positioning pins are respectively arranged on the central discs on two sides of the two positioning plates, the two spring positioning pins are oppositely arranged, movement 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 slide in the movement grooves formed on the outer side faces of the two positioning plates respectively, and positioning grooves are formed at the stroke tail end of each movement groove; when the spring pulls the folding piece to rotate to the horizontal position by taking the rotating shaft as the shaft, the pin heads of the two spring positioning pins are respectively inserted into the two positioning grooves.
2. A foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1, wherein the retraction mechanism of the automatic retraction arm comprises a lower support plate, an upper support plate, a motor, a screw rod and a connector; the lower support plate and the upper support plate are respectively provided with a plurality of mounting holes for connecting with a plurality of cylindrical rod bodies, and are respectively connected with the cylindrical rod bodies through the mounting holes; the motor is arranged 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 at the top of the upper supporting plate, the rib plates are vertically arranged and connected together at the top of the rib plates, the screw rod is vertically arranged between the lower supporting plate and the upper supporting plate, the bottom end of the screw rod is in transmission connection with an output shaft of the motor, and the top end of the screw rod is rotationally connected to the connection position of the top of the rib plates after passing through the hole in the middle of the upper supporting plate; the connector is in threaded connection with the screw rod, a plurality of first execution components are connected to the connector and are arranged circumferentially, the first execution components comprise a hinging block, a rotating arm and a sleeve, the tail end of the hinging block is hinged with the connector, the head end of the hinging block is hinged with 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 with the edge of the upper support plate towards the top of the end face of the upper support plate; the sleeve pipe is kept away from the end connection unmanned aerial vehicle horn of last backup pad.
3. The foldable barrel type multi-rotor unmanned aerial vehicle according to claim 2, wherein the head end of the hinge block is of a U-shaped structure, and the tail end of the rotating arm is hinged in the U-shaped structure of the head end of the hinge block.
4. The foldable barrel type multi-rotor unmanned aerial vehicle according to claim 2, wherein two arm bodies are formed at the head end of the rotating arm, the end parts of the two arm bodies are respectively bent for 90 degrees and then are rigidly connected with the outer circumferential surface of the sleeve, and the bending directions of the end parts of the two arm bodies are consistent.
5. The foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1, wherein the second execution assembly comprises two springs, and the connecting plate on the folding piece is connected with the fixing piece through the two springs; the spring positioning pin is provided with a manual deflector rod; the clamping disc is provided with a middle plate below, the middle plate is connected with a plurality of cylindrical rods, a guide column is arranged at the top of the middle plate, and a guide hole matched with the guide column is formed in the clamping disc.
6. The foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1 or 2, further comprising a battery fixing frame, wherein the battery fixing frame is connected with a plurality of cylindrical rods, 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 formed at the edge of the battery fixing frame between two adjacent cylindrical rods.
7. The foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1 or 2, wherein a barrel launching auxiliary device is arranged at the bottom of the bottom supporting plate and comprises a base, a plurality of struts are vertically arranged at the top of the base and are circumferentially arranged, a supporting frame is connected between the plurality of struts, a conical structure is formed at the top ends of the struts, and the top ends of the plurality of struts are movably contacted with the bottom ends of the plurality of cylindrical rods on the bottom supporting plate.
8. A collapsible tube multi-rotor unmanned aerial vehicle as claimed in claim 1 or claim 2 wherein four-point landing gear is attached to the outer circumference of the bottom support plate.
9. The foldable barrel type multi-rotor unmanned aerial vehicle according to claim 1, wherein a top fairing is mounted on the top supporting plate, a body fairing is sleeved on the periphery of the cylindrical rod bodies, and an opening for the unmanned aerial vehicle arm to pass through is formed in the body fairing.
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| CN202110017573.5A CN112591074B (en) | 2021-01-07 | 2021-01-07 | Foldable barrel type multi-rotor unmanned aerial vehicle |
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| CN202110017573.5A CN112591074B (en) | 2021-01-07 | 2021-01-07 | Foldable barrel type multi-rotor unmanned aerial vehicle |
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| CN113716015B (en) * | 2021-08-19 | 2024-06-11 | 航天时代飞鹏有限公司 | Four rotor unmanned aerial vehicle horn independently receive and release mechanism |
| CN114030593B (en) * | 2021-11-03 | 2022-09-13 | 南京甲子智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
| CN113998099A (en) * | 2021-12-14 | 2022-02-01 | 复旦大学 | Many rotor unmanned aerial vehicle that horn can vert |
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| CN105857571B (en) * | 2016-04-08 | 2018-02-27 | 北京博瑞云飞科技发展有限公司 | Unmanned plane with more horn synchronous folding mechanisms |
| CN207141364U (en) * | 2017-03-23 | 2018-03-27 | 西安天问智能科技有限公司 | Multi-rotor aerocraft mechanical arm foldable mechanism and rotor craft |
| CN106904267B (en) * | 2017-04-18 | 2023-08-11 | 昆山合朗航空科技有限公司 | Unmanned aerial vehicle horn mechanism and unmanned aerial vehicle |
| CN208021708U (en) * | 2018-03-23 | 2018-10-30 | 张梦杰 | One kind can auto-folder unmanned plane horn |
| CN110857148A (en) * | 2018-08-22 | 2020-03-03 | 北京理工大学 | Rotor unmanned aerial vehicle ejection device on carrying system |
| CN211308947U (en) * | 2019-12-11 | 2020-08-21 | 复旦大学 | Scalable foldable farming of wing protects unmanned aerial vehicle |
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