CN110683071A - Carrying system carrying rotor unmanned aerial vehicle - Google Patents
Carrying system carrying rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN110683071A CN110683071A CN201810725967.4A CN201810725967A CN110683071A CN 110683071 A CN110683071 A CN 110683071A CN 201810725967 A CN201810725967 A CN 201810725967A CN 110683071 A CN110683071 A CN 110683071A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- fairing
- rotor
- carrying
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
The invention discloses a carrying system for carrying a rotor unmanned aerial vehicle, wherein the rotor unmanned aerial vehicle is confined in the carrying system, the carrying system can quickly reach a preset airspace, and can eject the rotor unmanned aerial vehicle confined in the rotor unmanned aerial vehicle out after reaching the preset airspace, so that the rotor unmanned aerial vehicle directly starts to work in the preset airspace, such as photographing, detecting, infrared positioning and the like.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a carrying system for carrying a rotor unmanned aerial vehicle.
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, rotor unmanned aerial vehicle is a comparatively important branch in the unmanned aerial vehicle, rotor unmanned aerial vehicle can hover, the volume is less, can carry out special operation such as fixed point shooting, but receive the structural characteristic influence of its self, current rotor unmanned aerial vehicle also has its distinctive defect, for example because adopt screw power, its flying speed is slower than wing type unmanned aerial vehicle, its flying height also can receive very big restriction, can not climb to higher height fast, be difficult to satisfy special task requirement, in addition, because the problem of volume and power, energy such as battery that rotor unmanned aerial vehicle can carry is more limited, its working radius is less, be difficult to compete remote reconnaissance, observe the task.
For the reasons, the invention designs the carrying system capable of being matched with the rotor unmanned aerial vehicle, the rotor unmanned aerial vehicle is conveyed to a specific position through the carrying system, and the rotor unmanned aerial vehicle can be ejected out of the carrying equipment, so that the problems are solved.
Disclosure of Invention
In order to overcome the problems, the inventor of the invention has made a keen study, and designs a carrying system for carrying a rotor unmanned aerial vehicle, wherein the rotor unmanned aerial vehicle is confined in the carrying system, the carrying system can quickly reach a predetermined airspace, and can eject the rotor unmanned aerial vehicle confined in the carrying system after reaching the predetermined airspace, so that the rotor unmanned aerial vehicle directly starts to work in the predetermined airspace, such as photographing, detecting, infrared positioning and the like.
In particular, the invention aims to provide a carrying system carrying a rotor unmanned aerial vehicle,
the vehicle system comprises a deployable fairing 1;
a bearing seat 2 is arranged below the inner part of the fairing 1;
wherein, radome fairing 1 can expand, and unmanned aerial vehicle can be placed to its inside, when arriving predetermined airspace expansion radome fairing 1 time, can expose its inside unmanned aerial vehicle.
The bearing seat 2 can be used for confining the rotor wing unmanned aerial vehicle
Wherein, bearing seat 2 can pop out unmanned aerial vehicle when radome fairing 1 expandes.
The bearing seat 2 comprises a limiting cylinder 21 and a bearing plate 22 positioned on the inner side of the limiting cylinder 21;
the limiting cylinder 21 is used for limiting the rotor wing unmanned aerial vehicle;
the supporting plate 22 is used for ejecting the unmanned aerial vehicle from the limiting cylinder 21.
Wherein, the supporting plate 22 can move upwards along the axis direction of the limiting cylinder 21 inside the limiting cylinder 21, so that the unmanned rotorcraft above the inside of the limiting cylinder 21 is ejected out.
Wherein, the fairing 1 comprises at least 3 arc-shaped cover sheets 11 with the same external dimension, and each arc-shaped cover sheet 11 is hinged with the shell of the carrying system.
Wherein, in a predetermined airspace, after each arc-shaped cover piece 11 rotates a predetermined angle relative to the carrying system shell, the support plate 22 ejects the rotor unmanned aerial vehicle.
Wherein the unmanned aerial vehicle comprises a frame 3 and a swing arm 4;
the rotary arm 4 can be bent downwards relative to the frame 3 and is optionally fixed in the bearing seat 2,
the fastening of the swing arm 4 can be released, and preferably the swing arm can automatically rebound to the horizontal position, more preferably, when the unmanned aerial vehicle pops up from the bearing seat 2, the swing arm 4 of the unmanned aerial vehicle automatically rebounds to the horizontal position, and then the unmanned aerial vehicle starts to work.
Wherein, when unmanned aerial vehicle buckled downwards for frame 3 at its spiral arm 2, in spacing section of thick bamboo 21 can be embedded into to 2 bottom ends of its spiral arm to confine rotor unmanned aerial vehicle through a spacing section of thick bamboo 21.
The unmanned aerial vehicle also comprises a connecting disc 5 arranged right below the rack 1;
the reciprocating movement of the connecting disc 5 in the vertical direction controls the radial arm 4 to bend downwards or rebound to the horizontal position.
The invention also provides a method for carrying the rotor unmanned aerial vehicle by the system, which is characterized in that,
the fairing 1 is unfolded and the fairing is,
the rotary arm 2 of the unmanned aerial vehicle is bent downwards relative to the frame 1, the unmanned aerial vehicle is locked by the bearing seat 2, then the fairing 1 is closed,
when the rotor unmanned aerial vehicle reaches a preset airspace and the fairing 1 is unfolded, the unmanned aerial vehicle is exposed,
releasing the confinement of the unmanned aerial vehicle, automatically rebounding the swing arm 2 of the unmanned aerial vehicle to the horizontal position, and starting the unmanned aerial vehicle.
The invention has the advantages that:
(1) the carrying system carrying the rotor unmanned aerial vehicle can carry the rotor unmanned aerial vehicle to a designated area through the carrying system, has the capability of quickly reaching a remote operation site, has high working efficiency, and can execute tasks with special requirements on reaction speed and starting time, such as fire reconnaissance, target positioning and the like;
(2) the carrying system carrying the rotor unmanned aerial vehicle can quickly transport the rotor unmanned aerial vehicle to a specific height which is difficult for a conventional rotor unmanned aerial vehicle to reach through the carrying system, and has the capability of executing special tasks;
(3) according to the carrying system carrying the rotor unmanned aerial vehicle, provided by the invention, the energy carried by the rotor unmanned aerial vehicle is not consumed before the carrying system arrives at an operation place, so that the working duration of the rotor unmanned aerial vehicle is longer, and a long-distance operation task can be executed.
Drawings
Fig. 1 shows a schematic view of the overall structure of a vehicle system carrying a rotorcraft according to a preferred embodiment of the invention;
figure 2 shows a schematic view of a preferred embodiment of the present invention showing the structure of a fairing on a vehicle carrying a rotorcraft when deployed;
figure 3 shows a cross-section of a support base in a carrier system carrying a rotorcraft according to a preferred embodiment of the invention;
fig. 4 is a schematic structural view of a rotor drone in a carrier system carrying the rotor drone according to a preferred embodiment of the present invention.
The reference numbers illustrate:
1-fairing
11-arc cover sheet
12-support bar
2-bearing seat
21-spacing cylinder
22-bearing plate
3-frame
4-rotating arm
41-polished rod section
42-Ring Sleeve
5-connecting disc
6-a connecting rod is arranged at the top of the steel pipe,
7-drive motor
8-propeller
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 invention, a carrying system for carrying a rotor unmanned aerial vehicle is provided, as shown in fig. 1 and 2, comprising a deployable fairing 1; a bearing seat 2 is arranged below the inner part of the fairing 1; the bearing seat 2 is used for fastening the rotor unmanned aerial vehicle.
In a preferred embodiment, the carrying system releases the drone when reaching a predetermined airspace, and the drone is at a smaller distance from the predetermined working area and can arrive 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 fighting part of the ammunition needs to be replaced by the rotor wing unmanned aerial vehicle.
The releasing of the unmanned aerial vehicle comprises two steps, wherein one step is that the fairing is unfolded, and the other step is that the unmanned aerial vehicle is popped out from the carrying equipment/bearing seat through the bearing plate.
Preferably, the fairing 1 can be unfolded, an unmanned aerial vehicle can be placed in the fairing 1, and when the fairing 1 is unfolded at a preset airspace, the unmanned aerial vehicle in the fairing can be exposed;
the fairing 1 is used for protecting the unmanned aerial vehicle inside, is unfolded when reaching a preset airspace, and exposes the unmanned aerial vehicle inside so that the unmanned aerial vehicle can be conveniently popped up and started to work;
the bearing seat 2 is used for fixing the unmanned aerial vehicle through the spiral arm matching with the unmanned aerial vehicle, and the unmanned aerial vehicle is popped out from the bearing seat 2 when the unmanned aerial vehicle reaches a preset airspace.
Specifically, as shown in fig. 1 and 3, the bearing block 2 includes a limiting cylinder 21 and a bearing plate 22 located inside the limiting cylinder 21,
the size of the limiting cylinder 21 is basically consistent with the size of a circle defined by a gap corresponding to the swing arm of the unmanned aerial vehicle, so that the limiting cylinder 21 can be just embedded into a circular space defined by the gap corresponding to the swing arm of the unmanned aerial vehicle, the end part of the swing arm 4 abuts against the wall surface of an inner ring of the limiting cylinder 21, the limiting cylinder 21 can block the swing arm 4 from rotating, and further block the swing arm 4 from rebounding to a horizontal position, and therefore the confinement of the unmanned aerial vehicle is realized; the height of the limiting cylinder 21 is 30-50mm, i.e. the distance between the highest position of the limiting cylinder and the supporting plate 22 is 30-50mm, and since the supporting plate 22 can move in the vertical direction, the supporting plate 22 is at the lowest possible position when calculating the height/distance.
When the carrying system is locked up unmanned aerial vehicle, bearing plate 22 is located the below of spiral arm 4, and the distance between bearing plate 22 and the spiral arm is less, is less than 10mm generally, just bearing plate 22 can move on vertical direction, and its moving stroke is 30-50mm at least, along with the removal of bearing plate 22, bearing plate 22 can be released unmanned aerial vehicle's spiral arm from bearing seat 2 promptly, because bearing plate 22's moving speed is higher, when unmanned aerial vehicle breaks away from with bearing seat 2, unmanned aerial vehicle has certain initial speed, can continue to remove certain distance along this direction.
The repulsion that bearing plate 22 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 unmanned aerial vehicle's function can.
In a preferred embodiment, as shown in fig. 1, 2 and 3, the fairing 1 comprises at least 3 arc-shaped cover sheets 11 with the same external dimension, and each arc-shaped cover sheet 11 is hinged with the carrying system shell and can form a closed shell structure after being tightly attached to each other;
preferably, the exterior of the vehicle system of the present invention comprises a vehicle system housing and a fairing 1, wherein the fairing 1 is located at the front end/top and is connected to the vehicle system housing.
The fairing 1 is provided with a locking mechanism, when the arc-shaped cover pieces 11 are tightly attached to each other, the locking mechanism locks the arc-shaped cover pieces 11 to prevent the arc-shaped cover pieces from being separated from each other, the locking mechanism can be automatically released, and when the locking mechanism receives an unfolding instruction, the locking mechanism automatically releases the locking of the arc-shaped cover pieces 11 to enable the arc-shaped cover pieces 11 to be separated from each other and rotate, so that the unmanned aerial vehicle in the fairing is exposed; the locking mechanism can be an electromagnetic lock or a mechanical lock, can be set to any form, and only needs to meet the requirements.
Preferably, the carrying system is further provided with a control module, the control module is used for sending a deployment instruction to the latching mechanism, 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, the position information and the speed information of the carrying system are detected and obtained through satellite positioning modules such as a GPS receiving module and a Beidou receiving module, when the detected state information meets preset conditions, a unfolding instruction is generated and sent, for example, the unfolding instruction is generated and sent when the detected state information reaches the height of about 800m, or the unfolding instruction is generated and sent when the detected state information reaches the position close to east longitude 116.3 degrees and northern latitude 39.95 degrees, or the unfolding instruction is generated and sent when the vertical direction speed value is 0, 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 at the hinged connection of each arc-shaped cover sheet 11 and the carrying system, and the second type of inductive switch is connected with the bearing plate 22 and used for controlling the bearing plate 22 to start;
when the arc-shaped cover piece 11 rotates by a preset angle, the corresponding second-class induction switch can be triggered, and preferably, the preset angle value is more than 90 degrees;
the second type of inductive switch has a plurality ofly, and when all second type of inductive switches are triggered back control supporting board 22 start work, pop out unmanned aerial vehicle from delivery system/supporting seat 2.
In a preferred embodiment, as shown in fig. 2, a support rod 12 is further disposed inside the fairing 1, one end of the support rod 12 is fixedly connected to the inner wall of the arc-shaped cover piece 11, and the other end of the support rod 12 is in contact with a polished rod section 41 of the unmanned aerial vehicle confined in the carrying system to support/limit the unmanned aerial vehicle and prevent the unmanned aerial vehicle from vibrating or swinging in the carrying system, when the locking mechanism releases the locking of the arc-shaped cover piece 11, the support rod 12 is separated from the polished rod section 41 along with the rotation of the arc-shaped cover piece 11.
In a preferred embodiment, as shown in fig. 4, the rotorcraft comprises a frame 3 and a radial arm 4; 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 confined in the carrying system when the rotary arm 4 is bent downwards relative to the frame 3, preferably, the unmanned aerial vehicle can be confined 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 on the unmanned aerial vehicle, the rotating arm 4 of the unmanned aerial vehicle automatically rebounds to the horizontal position and starts working; specifically, when the swing arm 4 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 and 4, the drone further comprises a connecting disc 5 arranged directly below the frame 3,
the reciprocating movement of the connecting disc 5 in the vertical direction controls the radial arm 4 to bend downwards or rebound to the horizontal position. When the connecting disc 5 moves downwards, the spiral arm 4 is driven to bend downwards, and when the connecting disc 5 moves upwards, the spiral arm 4 is driven to rebound to a horizontal position; similarly, the connecting plate 5 can be driven to move downwards when the radial arm 4 bends downwards, and the connecting plate 5 can be driven to move upwards when the radial arm 4 rebounds to the horizontal position.
In particular, preferably, a connecting rod 6 is provided on said connecting disc 5,
one end of the connecting rod 6 is hinged with the connecting disc 3,
the other end of the connecting rod 6 is hinged with the radial arm 4. The number of the connecting rods 6 is consistent with that of the radial arms 4, and the connecting rods correspond to the radial arms one by one.
Further preferably, said radial arm 4 comprises a polished rod segment 41,
an annular sleeve 42 is sleeved on the polished rod section 41, and the annular sleeve 42 can slide back and forth along the polished rod section 41, or the annular sleeve 42 is fixed on the polished rod section 41;
the connecting rod 6 is hinged with the annular sleeve 42, namely the connecting rod 6 is hinged with the radial arm 4 through the annular sleeve 42.
Preferably, a limiting mechanism is arranged on the connecting disc 3 and the rack 3, 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 arranged between the connecting disc 5 and the frame 3,
the stretching mechanism is used for pulling the connecting disc 5 to be close to the rack 3 upwards, and then the rotating arm 4 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 4 is bent downwards, a large elastic potential energy is stored in the stretching mechanism, so that the swing arm 4 has a tendency of returning to a horizontal position, and when an external force for limiting and closing the swing arm 4 disappears, the swing arm 4 can accelerate and rotate from a static state at a large acceleration under the action of the stretching mechanism, and rebounds to the horizontal position from a downward bending state.
Further preferably, torsion springs are arranged at two hinged positions of one end of the connecting rod 6 hinged with the connecting disc 3 and the connecting rod 6 hinged with the annular sleeve 42, the torsion springs are also part of the stretching mechanism, the torsion springs are used for increasing the elastic force which needs to be overcome when the radial arm 4 is bent from the horizontal position to the bending state, and further increasing the elastic potential energy stored in the stretching mechanism when the radial arm 42 is bent downwards; this torsion spring can also make connecting rod 6 and the acting force that receives a plurality of directions on the swing arm 4, ensures that connecting rod 6 and swing arm 4 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 swing arm must kick-back to horizontal position.
In a preferred embodiment, as shown in fig. 1 and 4, a driving motor 7 and a propeller 8 are arranged at the end of the swing arm 4, the driving motor 7 is used for controlling the propeller 8 to rotate, and when the unmanned aerial vehicle is locked in the carrying system, a control circuit of the driving motor 7 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 the control circuit of the driving motor 7 is switched on after the induction switch is triggered, so that the driving motor 7 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 preset gap is reserved between the radial arm 4 and the propeller 8, one part of the driving motor 7 is embedded in the radial arm 4, the other part is exposed outside, and the end part of the exposed outside is provided with the propeller 8.
Preferably, said radial arm 4 is provided with a plurality, preferably 4-8,
when the unmanned aerial vehicle is confined in the carrying system, a plurality of preset gaps corresponding to the swing arms 4 are circularly arranged; the carrying system is confined in the unmanned aerial vehicle through this space, imbeds in this space and hinders the apron that the swing arm 4 kick-backs to horizontal position promptly, under the effect of the elasticity on the swing arm, the unmanned aerial vehicle is whole promptly fixed, confined in carrying system. The baffle is the limiting cylinder 21.
The invention also provides a method for carrying the rotor unmanned aerial vehicle by the carrying system of the rotor unmanned aerial vehicle, which comprises the following steps
The fairing 1 is unfolded and the fairing is,
the rotary arm 2 of the unmanned aerial vehicle is bent downwards relative to the frame 1, the unmanned aerial vehicle is locked by the bearing seat 2, then the fairing 1 is closed,
when the rotor unmanned aerial vehicle reaches a preset airspace and the fairing 1 is unfolded, the unmanned aerial vehicle is exposed,
releasing the confinement of the unmanned aerial vehicle, automatically rebounding the swing arm 2 of the unmanned aerial vehicle to the horizontal position, and starting the unmanned aerial vehicle.
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 (10)
1. A carrying system carrying a rotor unmanned aerial vehicle is characterized in that,
the vehicle system comprises a deployable fairing (1);
a bearing seat (2) is arranged below the inner part of the fairing (1).
2. A delivery system as in claim 1,
the fairing (1) can be unfolded, an unmanned aerial vehicle can be placed in the fairing, and when the fairing (1) is unfolded at a preset airspace, the unmanned aerial vehicle in the fairing can be exposed;
the bearing seat (2) can be used for fastening the rotor wing unmanned aerial vehicle.
3. A delivery system as in claim 1,
the bearing seat (2) can eject the unmanned aerial vehicle when the fairing (1) is unfolded.
4. A delivery system as in claim 3,
the bearing seat (2) comprises a limiting cylinder (21) and a bearing plate (22) positioned on the inner side of the limiting cylinder (21);
the limiting cylinder (21) is used for confining the rotor wing unmanned aerial vehicle;
the supporting plate (22) is used for ejecting the unmanned aerial vehicle from the limiting cylinder (21).
5. A delivery system as in claim 4,
the supporting plate (22) can move upwards in the limiting cylinder (21) along the axis direction of the limiting cylinder (21), so that the rotor unmanned aerial vehicle located above the inside of the limiting cylinder (21) is ejected out.
6. A delivery system as in claim 5,
the fairing (1) comprises at least 3 arc-shaped cover sheets (11) with the same appearance size, and each arc-shaped cover sheet (11) is hinged with the shell of the carrying system;
preferably, in a predetermined airspace, the support plate (22) ejects the rotor-wing drone after each arc-shaped cover piece (11) rotates a predetermined angle relative to the carrying system shell.
7. A delivery system as in claim 1,
the unmanned aerial vehicle comprises a frame (3) and a rotary arm (4);
the rotary arm (4) can be bent downwards relative to the frame (3) and is optionally fixed in the bearing seat (2),
the fastening of the swing arm (4) can be released, and preferably the swing arm can automatically rebound to the horizontal position, more preferably, when the unmanned aerial vehicle pops out from the bearing seat (2), the swing arm (4) automatically rebounds to the horizontal position, and then the unmanned aerial vehicle starts to work.
8. A delivery system as in claim 7,
when unmanned aerial vehicle buckled downwards for frame (3) in its spiral arm (2), in its spiral arm (2) bottom can be embedded into a spacing section of thick bamboo (21) to through a spacing section of thick bamboo (21) confinement rotor unmanned aerial vehicle.
9. A delivery system as in claim 7,
the unmanned aerial vehicle also comprises a connecting disc (5) arranged right below the rack (1);
the swing arm (4) is controlled to bend downwards or rebound to a horizontal position through the reciprocating movement of the connecting disc (5) in the vertical direction.
10. Method of loading a rotary-wing drone with a system according to one of claims 1 to 9,
the fairing (1) is unfolded and then,
bending a rotating arm (2) of the unmanned aerial vehicle downwards relative to a frame (1), fastening the unmanned aerial vehicle by using a bearing seat (2), then closing a fairing (1),
when the rotor unmanned aerial vehicle reaches a preset airspace and the fairing (1) is unfolded, the unmanned aerial vehicle is exposed,
releasing the confinement of the unmanned aerial vehicle, automatically rebounding the swing arm (2) of the unmanned aerial vehicle to a horizontal position, and starting the unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810725967.4A CN110683071A (en) | 2018-07-04 | 2018-07-04 | Carrying system carrying rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810725967.4A CN110683071A (en) | 2018-07-04 | 2018-07-04 | Carrying system carrying rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110683071A true CN110683071A (en) | 2020-01-14 |
Family
ID=69106474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810725967.4A Pending CN110683071A (en) | 2018-07-04 | 2018-07-04 | Carrying system carrying rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110683071A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011137335A1 (en) * | 2010-04-30 | 2011-11-03 | Elbit Systems Of America, Llc | Unmanned aerial vehicle based sonar buoy |
| US20140026802A1 (en) * | 2008-06-16 | 2014-01-30 | Aurora Flight Sciences Corporation | Combined submersible vessel and unmanned aerial vehicle |
| US20160137312A1 (en) * | 2014-05-06 | 2016-05-19 | Osterhout Group, Inc. | Unmanned aerial vehicle launch system |
| CN105966181A (en) * | 2016-06-13 | 2016-09-28 | 安徽工程大学 | Foldable lifting device suitable for hovercar and folding and unfolding method of foldable lifting device |
| CN106184704A (en) * | 2016-08-08 | 2016-12-07 | 北京航空航天大学 | One is applicable to rocket-propelled quadrotor |
| US20170057635A1 (en) * | 2015-09-02 | 2017-03-02 | The Boeing Company | Drone launch systems and methods |
-
2018
- 2018-07-04 CN CN201810725967.4A patent/CN110683071A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140026802A1 (en) * | 2008-06-16 | 2014-01-30 | Aurora Flight Sciences Corporation | Combined submersible vessel and unmanned aerial vehicle |
| WO2011137335A1 (en) * | 2010-04-30 | 2011-11-03 | Elbit Systems Of America, Llc | Unmanned aerial vehicle based sonar buoy |
| US20160137312A1 (en) * | 2014-05-06 | 2016-05-19 | Osterhout Group, Inc. | Unmanned aerial vehicle launch system |
| US20170057635A1 (en) * | 2015-09-02 | 2017-03-02 | The Boeing Company | Drone launch systems and methods |
| CN105966181A (en) * | 2016-06-13 | 2016-09-28 | 安徽工程大学 | Foldable lifting device suitable for hovercar and folding and unfolding method of foldable lifting device |
| CN106184704A (en) * | 2016-08-08 | 2016-12-07 | 北京航空航天大学 | One is applicable to rocket-propelled quadrotor |
Non-Patent Citations (1)
| Title |
|---|
| 航空知识: ""大学航模队都玩什么？"黑精灵"变体无人机"", 《中国航空新闻网》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8439301B1 (en) | Systems and methods for deployment and operation of unmanned aerial vehicles | |
| US6392213B1 (en) | Flyer assembly | |
| JP6019044B2 (en) | Collecting / braking device for objects flying freely in outer space | |
| US8276844B2 (en) | Unmanned aerial vehicle launching and landing system | |
| CN109436296A (en) | The folding wings unmanned plane and its launching technique of cartridge type transmitting | |
| US9725172B2 (en) | Surveillance system | |
| EP3749574B1 (en) | Rail-launching munition release | |
| US20200115055A1 (en) | Launched Unmanned Aerial Vehicle | |
| US20130075534A1 (en) | Method for removing orbital objects from orbit using a capture net for momentum transfer | |
| CN110857148A (en) | Rotor unmanned aerial vehicle ejection device on carrying system | |
| CN1628053A (en) | System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle | |
| US20160046372A1 (en) | Rocket Morphing Aerial Vehicle | |
| KR101188294B1 (en) | Unmanned aerial vehicle for electronic warfare which uses jet engine | |
| US20220299296A1 (en) | Decoy system | |
| US20220185501A1 (en) | Tube-launched unmanned aerial vehicle | |
| CN110857149A (en) | But carrying rotor unmanned aerial vehicle's delivery system of recovery type | |
| CN110871904B (en) | Separated carrying system for carrying rotor unmanned aerial vehicle | |
| CN110857146B (en) | Carry on many rotor unmanned aerial vehicle's delivery system | |
| CN110683069A (en) | Carry on rotor unmanned aerial vehicle's arrow machine system | |
| CN110683071A (en) | Carrying system carrying rotor unmanned aerial vehicle | |
| CN110861781A (en) | Rocket-borne rotor unmanned aerial vehicle control system | |
| CN110683070A (en) | Rocket-borne rotor unmanned aerial vehicle | |
| CN110683072A (en) | Rocket-borne rotor unmanned aerial vehicle projection method | |
| CN110865404B (en) | Target positioning system for cooperative operation of multiple rotor unmanned aerial vehicles | |
| KR101374307B1 (en) | Cannon launched aerial observation sub munition and the observation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200114 |
|
| RJ01 | Rejection of invention patent application after publication |