CN110857146B - Carry on many rotor unmanned aerial vehicle's delivery system - Google Patents
Carry on many rotor unmanned aerial vehicle's delivery system Download PDFInfo
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- CN110857146B CN110857146B CN201810972778.7A CN201810972778A CN110857146B CN 110857146 B CN110857146 B CN 110857146B CN 201810972778 A CN201810972778 A CN 201810972778A CN 110857146 B CN110857146 B CN 110857146B
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- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 2
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- 230000001939 inductive effect Effects 0.000 description 5
- 230000001965 increasing effect Effects 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/80—Transport or storage specially adapted for UAVs by vehicles
- B64U80/82—Airborne vehicles
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Abstract
The invention discloses a carrying system for carrying a plurality of rotor unmanned aerial vehicles, which comprises a cabin body, wherein a plurality of sleeves are arranged in the cabin body, and each sleeve is provided with a rotor unmanned aerial vehicle which can be ejected out; an ejection part is arranged at the bottom of the inner side of the sleeve, and the ejection part can be ejected from the bottom of the sleeve to the top of the sleeve, so that the unmanned rotorcraft can be ejected from the sleeve; therefore, the rotor unmanned aerial vehicle can directly start to work in a preset airspace, such as photographing, detecting, infrared positioning and the like, and can quickly reach an operation airspace which is difficult to reach without energy consumption, so that the operation efficiency of the rotor unmanned aerial vehicle is greatly improved, the operation capacity is expanded, and the rotor unmanned aerial vehicle has the capacity of executing more tasks, and the invention is completed.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a carrying system for carrying a plurality of rotor unmanned aerial vehicles.
Background
With the increasing improvement of unmanned aerial vehicle technology, unmanned aerial vehicles are introduced into more and more fields, and people can conveniently and quickly complete tasks which are seemingly difficult to complete by using the unmanned aerial vehicles; wherein, the rotor unmanned aerial vehicle is a more important branch of the unmanned aerial vehicle, the rotor unmanned aerial vehicle can hover, has smaller volume and can execute special operations such as fixed-point shooting and the like, but, affected by its own structural characteristics, the existing rotorcraft also has its own drawbacks, such as the use of propeller power, the flying speed is slower than that of an airfoil unmanned aerial vehicle, the flying height is also greatly limited, the unmanned aerial vehicle cannot rapidly climb to a higher height and is difficult to meet the requirement of a special task, in addition, because of the problems of volume and power, the energy sources such as batteries and the like which can be carried by the rotor unmanned aerial vehicle are relatively limited, the working radius is small, which is difficult to be competent for long-distance reconnaissance and observation tasks, in addition, for some special tasks, one unmanned aerial vehicle is often difficult to be competent, a plurality of unmanned aerial vehicles are required to operate cooperatively, how to rapidly launch the multiple unmanned aerial vehicles to a specified area becomes a greater problem.
Because of the reason, the inventor designs one kind can with rotor unmanned aerial vehicle complex delivery system, transport rotor unmanned aerial vehicle to specific position through this delivery system, pop out a plurality of rotor unmanned aerial vehicles from delivery system one by one again to solve above-mentioned problem.
Disclosure of Invention
In order to overcome the problems, the inventor of the invention carries out intensive research and designs a carrying system for carrying a plurality of rotor unmanned aerial vehicles, wherein the carrying system comprises a cabin body, a plurality of sleeves are arranged in the cabin body, and each sleeve is provided with a rotor unmanned aerial vehicle which can be ejected out; an ejection part is arranged at the bottom of the inner side of the sleeve, and the ejection part can be ejected from the bottom of the sleeve to the top of the sleeve, so that the unmanned rotorcraft can be ejected from the sleeve; when the carrying system reaches a preset airspace, the rotor unmanned aerial vehicle can be popped out of the sleeve, and then the rotor unmanned aerial vehicle is popped out of the carrying system, and then the bearing plate moves upwards to separate the rotor unmanned aerial vehicle from the sleeve, so that the rotor unmanned aerial vehicle can directly start working in the preset airspace, such as photographing, detection, infrared positioning and the like.
In particular, the invention aims to provide a carrying system for carrying a plurality of rotor unmanned aerial vehicles,
the carrying system comprises a cabin body 1, a plurality of sleeves 2 are installed in the cabin body 1, and a rotor unmanned aerial vehicle 3 which can be ejected is arranged in each sleeve 2.
Wherein, the bottom of the inner side of the sleeve 2 is provided with an ejection part 4;
the rotor unmanned aerial vehicle 3 is fixed on the ejection part 4 after being folded and stored and is positioned inside the sleeve 2,
the ejection part 4 can eject from the bottom of the sleeve 2 to the top of the sleeve 2, and then eject the unmanned rotorcraft 3 from the sleeve 2.
Wherein, an openable cabin door 5 is arranged on the side wall of the cabin body 1;
the top of the opening on the sleeve 2 is abutted against the inner side of the cabin door 5;
preferably, the sleeves 2 are symmetrically distributed in the cabin 1.
Wherein, hatch door 5 opens when the delivery system reaches predetermined airspace to projectile portion 4 pops rotor unmanned aerial vehicle 3 out from the delivery system.
The ejection part 4 comprises a base 41 positioned at the bottom and a support cylinder 42 positioned above the base 41, and a bearing plate 43 is arranged inside the support cylinder 42;
the base 41 is ejected to the top of the sleeve (2) by the base 41 matching with the sleeve 2,
the rotor unmanned aerial vehicle 3 is locked through the supporting cylinder 42,
through the support plate 43 promotes rotor unmanned aerial vehicle 3 for rotor unmanned aerial vehicle (3) breaks away from with a support section of thick bamboo 42.
The support plate 43 is movable outward along the axial direction of the support cylinder 42 inside the support cylinder 42, so as to push out the unmanned rotorcraft 3 located above the inside of the support cylinder 42 to the outside of the support cylinder 42.
Wherein the rotorcraft comprises a frame 31 and a radial arm 32;
when the rotary wing unmanned aerial vehicle bends downwards relative to the frame 31 at the rotary arm 32, the bottom end of the rotary arm 32 can be embedded into the supporting cylinder 42 so as to be fastened on the supporting cylinder 42,
when the rotorcraft is disengaged from the support cylinder 42, the radial arm 32 of the drone automatically rebounds to a horizontal position and starts to work.
The unmanned rotorcraft further comprises a connecting disc 33 arranged right below the rack 31;
the reciprocating movement of the connecting disc 33 in the vertical direction controls the radial arm 32 to bend downwards or rebound to the horizontal position.
Wherein an elastic pad 51 is arranged inside the hatch 5;
under the circumstances that hatch door 5 was closed, cushion 51 and the rotor unmanned aerial vehicle 3 butt that is located the inside of sleeve 2 to fix rotor unmanned aerial vehicle 3 in sleeve 2.
The method for carrying and ejecting the multi-frame rotor unmanned aerial vehicle by the carrying system comprises the following steps:
step 1, a rotor unmanned aerial vehicle 3 is confined on an ejection part 4 in a sleeve 2, and a cabin door 5 is closed;
3, ejecting the ejection parts 4 from the bottom of the sleeve 2 to the top of the sleeve 2 in sequence, wherein the intervals are 1 second;
The invention has the advantages that:
(1) according to the carrying system carrying the multiple rotor unmanned aerial vehicles, which is provided by the invention, the multiple rotor unmanned aerial vehicles can be arranged, so that the purpose of quickly arranging the multiple rotor unmanned aerial vehicles is realized;
(2) according to the carrying system carrying the plurality of rotor unmanned aerial vehicles, which is provided by the invention, the rotor unmanned aerial vehicles can be conveyed to a designated area through the carrying system, the capability of quickly reaching a remote operation site is achieved, the working efficiency is high, and tasks such as fire reconnaissance and the like with special requirements on reaction speed and starting time can be executed;
(3) according to the carrying system carrying the plurality of rotor unmanned aerial vehicles, provided by the invention, the energy carried by the rotor unmanned aerial vehicles is not consumed before the rotor unmanned aerial vehicles arrive at the operation place, so that the working duration of the rotor unmanned aerial vehicles is longer, and long-distance operation tasks can be executed.
Drawings
Fig. 1 shows a schematic overall structure of a carrier system carrying multiple rotor drones according to a preferred embodiment of the invention;
FIG. 2 is a schematic view of a preferred embodiment of the present invention showing a partial structure of a door of a carrier system carrying multiple rotor drones when the door is closed
Fig. 3 is a partial schematic structural view showing the opening of an upper door of a carrying system carrying a plurality of unmanned rotorcraft according to a preferred embodiment of the present invention;
FIG. 4 shows a cross-sectional view of a support cylinder in a carrier system carrying multiple rotor drones in accordance with a preferred embodiment of the present invention;
fig. 5 is a schematic structural view of a rotor drone in a carrier system carrying a plurality of rotor drones according to a preferred embodiment of the present invention.
The reference numbers illustrate:
1-cabin body
2-sleeve
21-limit stop
3-rotor unmanned aerial vehicle
31-frame
32-radial arm
321-polished rod section
322-ring sliding sleeve
33-connecting disc
34-connecting rod
35-drive motor
36-propeller
4-ejection part
41-base
42-support cylinder
43-support plate
5-cabin door
51-elastic cushion
Detailed Description
The invention is explained in more detail below with reference to the figures and examples. The features and advantages of the present invention will become more apparent from the description.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The hinge joint of the invention is a connection relationship which has enough strength and is not easy to break, and the connection allows the relative rotation between the two connected with each other; the articulation is generally achieved in the present invention by a rotating shaft or hinge.
According to the carrying system for carrying multiple rotor unmanned aerial vehicles provided by the invention, as shown in fig. 1, 2 and 3, the carrying system comprises a cabin body 1, a plurality of sleeves 2 are installed in the cabin body 1, and a rotor unmanned aerial vehicle 3 capable of being ejected is arranged in each sleeve 2.
Wherein, the bottom of the inner side of the sleeve 2 is provided with an ejection part 4;
the rotor unmanned aerial vehicle 3 is fixed on the ejection part 4 after being folded and stored and is positioned inside the sleeve 2,
the ejection part 4 can eject from the bottom of the sleeve 2 to the top of the sleeve 2, and then eject the unmanned rotorcraft 3 from the sleeve 2.
A limit stop 21 is arranged inside the sleeve 2, near the opening, to prevent the ejector 4 from being completely ejected from the sleeve 2.
In a preferred embodiment, the carrying system releases the rotor unmanned aerial vehicle when reaching a predetermined airspace, so that the rotor unmanned aerial vehicle is separated from the carrying system, and the distance from the unmanned aerial vehicle to a predetermined working area is smaller, so that the unmanned aerial vehicle can reach quickly; therefore, the preparation and navigation time from the moment when the unmanned aerial vehicle is in place and starts to work after receiving the task instruction and the related target information is greatly shortened, the fast response and the fast maneuver of the rotor unmanned aerial vehicle are realized, and the unmanned aerial vehicle can be used for handling emergent emergency tasks.
The carrying system is similar to a rocket or a rocket projectile, the flying principle of the carrying system is similar to that of the rocket, and the carrying system is an aircraft propelled forwards by the reaction force generated by the working medium injected by a rocket engine; the launching mode of the rocket projectile is similar to that of a rocket projectile, the rocket projectile is an ammunition launched by a rocket barrel or a rocket gun, and the warhead of the ammunition needs to be replaced by the rotor unmanned aerial vehicle or a sleeve.
Preferably, an openable hatch door 5 is arranged on the side wall of the cabin body 1;
the top of the opening on the sleeve 2 is abutted against the inner side of the cabin door 5;
preferably, the sleeves 2 are symmetrically distributed in the cabin 1.
When the hatch door is closed, the top of the sleeve 2 abuts against the inside of the hatch door 5; the cabin door 5 can be opened outwards, when the cabin door is opened, the top/opening end of the sleeve 2 is not blocked, and the rotor unmanned aerial vehicle in the sleeve can be freely ejected;
preferably, the hatch 5 is opened when the launch system reaches a predetermined airspace, so that the launcher 4 ejects the rotorcraft 3 from the launch system;
in the invention, the base 41 is ejected to the top of the sleeve 2 by matching the base 41 and the sleeve 2, the sleeve 2 and the base 41 can be ejected in any mode, for example, a compression spring is arranged as power to eject, an elastic rubber band is arranged as power to eject, an electromagnet is arranged to eject by using repulsion force or attraction force, an electromagnetic induction coil can be used as power to eject, and selection can be performed according to specific working requirements.
The cabin door 5 is opened when the carrying system reaches a preset airspace, so that the ejection part 4 ejects the rotor unmanned aerial vehicle 3 from the carrying system; the hatch door can be provided with a plurality of hatches or only one or two hatches, namely, one hatch door can correspond to one or more sleeves 2; preferably, the hatch door can be controlled by hydraulic means, at first outwards remove to the side after certain distance again, can ensure the leakproofness when the hatch door is closed, also can ensure that the hatch door can not block rotor unmanned aerial vehicle's pop-up route after opening.
In a preferred embodiment, the ejection part 4 comprises a base 41 at the bottom and a support cylinder 42 above the base 41, and a support plate 43 is arranged inside the support cylinder 42;
the base 41 is ejected to the top of the sleeve 2 by the base 41 cooperating with the sleeve 2,
the rotor unmanned aerial vehicle 3 is locked through the supporting cylinder 42,
through the support plate 43 promotes rotor unmanned aerial vehicle 3 for break away from with rotor unmanned aerial vehicle 3 and support cylinder 42.
Specifically, as shown in fig. 1, 2 and 4, the size of the support cylinder 42 is substantially consistent with the outer diameter of a quasi-circular structure formed by folding the swing arm of the rotor-wing drone, so that the support cylinder 42 can be just embedded between the swing arm of the drone and the propeller, the end of the swing arm 32 abuts against the inner ring wall surface of the support cylinder 42, the support cylinder 42 can block the swing arm 32 from rotating, and further block the swing arm 32 from rebounding to a horizontal position, thereby realizing the confinement of the drone; the height of the support cylinder 42 is 30-50mm, i.e. the distance between the highest point of the support cylinder 42 and the support plate 43 is 30-50mm, since the support plate 43 can be moved in the vertical direction, the support plate 43 is at the lowest possible point when calculating this height/distance.
When the carrying system ties up unmanned aerial vehicle, bearing board 43 is located the below of spiral arm 32, and the distance between bearing board 43 and the spiral arm is less, is less than 10mm generally, just bearing board 43 can move in vertical direction, and its moving stroke is 30-50mm at least, along with the removal of bearing board 43, bearing board 43 can be released unmanned aerial vehicle's spiral arm from bearing seat 2 promptly, because bearing board 43's translation rate is higher, when unmanned aerial vehicle breaks away from with bearing seat 2, unmanned aerial vehicle has certain initial speed, can continue to move certain distance along this direction.
The repulsion that bearing plate 43 can produce through the electro-magnet is as power, also can be as power through compression spring, can select by oneself according to actual conditions, can realize above-mentioned reciprocating motion and promote rotor unmanned aerial vehicle's function can.
In a preferred embodiment, as shown in figures 1, 2, 3 and 4,
when the cabin door receives a deployment instruction, the cabin door can be started to work and is opened outwards, so that the sleeve and the rotor unmanned aerial vehicle in the cabin door are exposed;
preferably, the ejection device is further provided with a control module, the control module is used for sending a deployment instruction to the cabin door, and the control module can generate and send the deployment instruction based on time information, can also generate and send the deployment instruction based on detected state information, and can also generate and send the deployment instruction based on a ground instruction;
the time information refers to that a preset unfolding instruction is generated and sent after a preset time, and the unfolding instruction is generated and sent after the preset time is filled, such as 40 seconds, generally before the carrying system is started;
the detected state information refers to the position information and the speed information of the carrying system, and is mainly detected by a satellite positioning module such as a GPS receiving module and a Beidou receiving module to acquire the position information, the speed information and other related information of the carrying system, and when the detected state information meets preset conditions, a deployment instruction is generated and issued, for example, when the detected state information reaches the position near 800m, the deployment instruction is generated and issued, or when the detected state information reaches the east longitude 316.3 degrees and the north latitude 39.95 degrees, the deployment instruction is generated and issued, or when the vertical direction speed value is 0, the deployment instruction is generated and issued, and the like;
the ground command refers to a control command sent by a ground control station and received by a carrying system in real time.
In a preferred embodiment, a second type of inductive switch is arranged on the hatch door, and the second type of inductive switch is connected with the supporting plate 43 and used for controlling the supporting plate 43 to start to work;
when the cabin door is opened and moved to a preset position, the corresponding second type inductive switch can be triggered, preferably, the cabin door needs to be completely opened at the moment, and the ejection path of the rotor wing unmanned aerial vehicle cannot be interfered/blocked;
in a preferred embodiment, as shown in fig. 1, 2, 3, inside the hatch 5 an elastic pad 51 is provided; the elastic pad 51 is made of rubber or polymer material, and has certain elasticity and can bear certain acting force.
Under the circumstances that hatch door 5 was closed, cushion 51 and the rotor unmanned aerial vehicle 3 butt that is located sleeve 2 inside to fix rotor unmanned aerial vehicle 3 in sleeve 2, prevent rotor unmanned aerial vehicle vibration or swing in the delivery system.
In a preferred embodiment, when the door 5 is completely opened, the ejection portions 4 in the plurality of sleeves are activated one by one, preferably, each ejection portion 4 is activated at an interval of 1 second, so that the unmanned rotorcraft 3 do not touch each other and interfere with each other, and stable and safe operation of the whole system is ensured.
In a preferred embodiment, as shown in fig. 5, the rotorcraft includes a frame 31 and a radial arm 32; the rotor unmanned aerial vehicle is a four-rotor unmanned aerial vehicle, a six-rotor unmanned aerial vehicle or an eight-rotor unmanned aerial vehicle;
the unmanned aerial vehicle is locked in the carrying system when the rotary arm 32 is bent downwards relative to the frame 31, preferably, the unmanned aerial vehicle can be locked in the carrying system only when the bending angle is about 90 degrees; the most preferred bend angle in the present invention is 95 degrees.
When the carrying system releases the confinement of the unmanned aerial vehicle, the swing arm 32 of the unmanned aerial vehicle automatically rebounds to the horizontal position and starts working; specifically, when the swing arm 32 rebounds to the horizontal position automatically under the action of the elastic force, the motor on the swing arm starts to work at the moment to drive the propeller to rotate, so that the unmanned aerial vehicle hovers in the airspace as soon as possible, and meanwhile, other related devices on the unmanned aerial vehicle start to work, such as a navigation system, a GPS (global positioning system) and the like, so that the unmanned aerial vehicle determines the position as soon as possible, moves to a target position, and starts to execute a preset operation task.
In a preferred embodiment, as shown in fig. 1, 2 and 5, the drone further comprises a connection disc 33 arranged directly below the frame 31,
the reciprocating movement of the connecting disc 33 in the vertical direction controls the radial arm 32 to bend downwards or rebound to the horizontal position. When the connecting disc 33 moves downwards, the radial arm 32 is driven to bend downwards, and when the connecting disc 33 moves upwards, the radial arm 32 is driven to rebound to a horizontal position; similarly, the connecting plate 33 can be driven to move downwards when the radial arm 32 bends downwards, and the connecting plate 33 can be driven to move upwards when the radial arm 32 rebounds to the horizontal position.
In particular, preferably, a connecting rod 34 is provided on the connecting disc 33,
one end of the connecting rod 34 is hinged with the connecting plate 3,
the other end of the link 34 is connected to the radial arm 32. The number of links 34 corresponds to the number of radial arms 32, one for each other.
Further preferably, the radial arm 32 comprises a light rod segment 321,
an annular sliding sleeve 322 is sleeved on the polished rod section 321, and the annular sleeve 322 can slide back and forth along the polished rod section 321, or the annular sleeve 322 is fixed on the polished rod section 321;
the connecting rod 34 is hinged to the annular sliding sleeve 322, that is, the connecting rod 34 is hinged to the radial arm 32 through the annular sliding sleeve 322.
Preferably, a limiting mechanism is arranged on the connecting plate 3 and the frame 31, so that the radial arm can only swing back and forth between the horizontal direction and the downward bending of 95 degrees.
Preferably, a stretching mechanism is provided between the connecting disc 33 and the frame 31,
the stretching mechanism is used for pulling the connecting disc 33 to be close to the rack 31 upwards, and then the rotating arm 32 is driven to rebound to the horizontal position. The stretching mechanism comprises a vertically arranged spring which is always in a stretching state; when the swing arm 32 is bent downwards, the stretching mechanism stores a larger elastic potential energy, so that the swing arm 32 has a tendency of returning to a horizontal position, and when the external force for limiting and closing the swing arm 32 disappears, the swing arm 32 can accelerate and rotate from a stationary state at a larger acceleration under the action of the stretching mechanism, and rebounds to the horizontal position from a downward bending state.
Further preferably, a torsion spring is arranged at two hinged positions, one end of the connecting rod 34 is hinged with the connecting plate 3, and the connecting rod 34 is hinged with the annular sliding sleeve 322, and the torsion spring is also a part of the stretching mechanism, so that the elasticity of the radial arm 32 required to be overcome from the horizontal position to the bending state is increased through the torsion spring, and further, the elastic potential energy stored in the stretching mechanism is increased when the radial arm 322 is bent downwards; this torsion spring can also make connecting rod 34 and the acting force that receives a plurality of directions on the spiral arm 32, ensures that connecting rod 34 and spiral arm 32 remove according to setting for the orbit, and then strengthens this system's reliability, in predetermined airspace, when releasing the confinement to unmanned aerial vehicle, unmanned aerial vehicle's spiral arm must kick-back to horizontal position.
In a preferred embodiment, as shown in fig. 2 and 5, a driving motor 35 and a propeller 36 are provided at an end of the swing arm 32, the driving motor 35 is used for controlling the propeller 36 to rotate, and when the drone is locked in the carrying system, a control circuit of the driving motor 35 is in a standby state; an induction switch is arranged at the joint of the swing arm and the rack, the induction switch is triggered when the swing arm returns to the horizontal position, and after the induction switch is triggered, a control circuit of the driving motor 35 is switched on, and the driving motor 35 starts to work. The inductive switch can be an electromagnetic inductive switch, also can be a mechanical contact switch, can be arranged at will, and can realize the functions.
Wherein, a predetermined gap is left between the radial arm 32 and the propeller 36, one part of the driving motor 35 is embedded in the radial arm 32, the other part is exposed outside, and the end of the exposed outside is provided with the propeller 36.
Preferably, the radial arm 32 is provided with a plurality, preferably 4-8,
when the unmanned aerial vehicle is confined in the carrying system, a plurality of the preset gaps corresponding to the swing arms 32 are circularly arranged; the carrying system is used for confining the unmanned aerial vehicle through the gap, namely, a supporting cylinder 42 for preventing the swing arm 32 from rebounding to the horizontal position is embedded into the gap, and under the action of the elastic force on the swing arm, the whole unmanned aerial vehicle is fixed and confined in the carrying system.
The invention also provides a method for carrying and ejecting the multi-rotor unmanned aerial vehicle by using the carrying system for carrying the multi-rotor unmanned aerial vehicle, which comprises the following steps:
step 1, a rotor unmanned aerial vehicle 3 is confined on an ejection part 4 in a sleeve 2, and a cabin door 5 is closed;
3, ejecting the ejection parts 4 from the bottom of the sleeve 2 to the top of the sleeve 2 in sequence, wherein the intervals are 1 second;
The present invention has been described above in connection with preferred embodiments, but these embodiments are merely exemplary and merely illustrative. On the basis of the above, the invention can be subjected to various substitutions and modifications, and the substitutions and the modifications are all within the protection scope of the invention.
Claims (3)
1. A carrying system for carrying a plurality of rotor unmanned aerial vehicles is characterized in that,
the carrying system comprises a cabin body (1), a plurality of sleeves (2) are arranged in the cabin body (1), a rotor unmanned aerial vehicle (3) capable of being ejected is arranged in each sleeve (2),
an ejection part (4) is arranged at the bottom of the inner side of the sleeve (2);
the rotor unmanned aerial vehicle (3) is fixed on the ejection part (4) after being folded and stored and is positioned in the sleeve (2),
the ejection part (4) comprises a base (41) positioned at the bottom and a support cylinder (42) positioned above the base (41), and a bearing plate (43) is arranged in the support cylinder (42);
the base (41) is ejected to the top of the sleeve (2) through the matching of the base (41) and the sleeve (2),
the rotor unmanned aerial vehicle (3) is locked up through the supporting cylinder (42), the height value of the supporting cylinder (42) is 30-50mm,
the supporting plate (43) can move outwards along the axis direction of the supporting cylinder (42) in the supporting cylinder (42), so that the unmanned rotorcraft (3) above the inside of the supporting cylinder (42) is pushed out of the supporting cylinder (42);
the distance between the bearing plate (43) and the rotary arm is less than 10mm, and the moving stroke of the bearing plate (43) moving in the vertical direction is at least 30-50 mm;
an openable cabin door (5) is arranged on the side wall of the cabin body (1);
after the cabin door (5) is completely opened, starting the ejection parts (4) at intervals of 1 second;
the top of the opening on the sleeve (2) is abutted against the inner side of the cabin door (5);
the sleeves (2) are symmetrically distributed in the cabin body (1);
a limit stop block (21) is arranged at the inner side of the sleeve (2) close to the opening,
one said hatch door (5) corresponding to at least one said sleeve (2); the hatch (5) is controlled by hydraulic means;
an elastic pad (51) is arranged on the inner side of the cabin door (5);
when the hatch (5) is closed, the elastic pad (51) abuts against the unmanned rotorcraft (3) inside the sleeve (2), thereby fixing the unmanned rotorcraft (3) in the sleeve (2);
the rotor unmanned aerial vehicle (3) comprises a frame (31) and a rotary arm (32);
when the rotary wing unmanned aerial vehicle (3) is bent downwards relative to the rack (31) by the rotary arm (32), the bottom end of the rotary arm (32) can be embedded into the support cylinder (42) so as to be confined on the support cylinder (42), and the bending angle is 95 degrees;
the rotor unmanned aerial vehicle (3) further comprises a connecting disc (33) arranged right below the rack (31);
the swing arm (32) is controlled to bend downwards or rebound to a horizontal position through the reciprocating movement of the connecting disc (33) in the vertical direction;
a stretching mechanism is arranged between the connecting disc (33) and the frame (31),
the stretching mechanism comprises a vertically arranged spring which is always in a stretching state; when the rotary arm (32) bends downwards, the stretching mechanism stores larger elastic potential energy, so that the rotary arm (32) has a tendency of returning to a horizontal position, and when the external force for limiting and closing the rotary arm (32) disappears, the rotary arm (32) can accelerate and rotate from a static state at a larger acceleration under the action of the stretching mechanism, and rebounds to the horizontal position from a downward bending state.
2. A delivery system as in claim 1,
the cabin door (5) is opened when the carrying system reaches a preset airspace, so that the ejection part (4) ejects the rotor unmanned aerial vehicle (3) from the carrying system.
3. A delivery system as in claim 1,
when rotor unmanned aerial vehicle (3) follow when breaking away from in supporting a section of thick bamboo (42), rotor unmanned aerial vehicle (3) spiral arm (32) are automatic to kick-back to horizontal position to start work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810972778.7A CN110857146B (en) | 2018-08-24 | 2018-08-24 | Carry on many rotor unmanned aerial vehicle's delivery system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810972778.7A CN110857146B (en) | 2018-08-24 | 2018-08-24 | Carry on many rotor unmanned aerial vehicle's delivery system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110857146A CN110857146A (en) | 2020-03-03 |
| CN110857146B true CN110857146B (en) | 2021-12-24 |
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Inventor after: Qiu Ziyi Inventor after: Jiang Jun Inventor after: Xu Weixiong Inventor after: Cui Ling Inventor after: Wang Hao Inventor after: Wang Yadong Inventor before: Jiang Jun Inventor before: Xu Weixiong Inventor before: Cui Ling Inventor before: Qiu Ziyi Inventor before: Wang Hao Inventor before: Wang Yadong |