CN110857148A - Rotor unmanned aerial vehicle ejection device on carrying system - Google Patents
Rotor unmanned aerial vehicle ejection device on carrying system Download PDFInfo
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- CN110857148A CN110857148A CN201810960705.6A CN201810960705A CN110857148A CN 110857148 A CN110857148 A CN 110857148A CN 201810960705 A CN201810960705 A CN 201810960705A CN 110857148 A CN110857148 A CN 110857148A
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- 238000005265 energy consumption Methods 0.000 abstract description 2
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- 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—Ground or aircraft-carrier-deck installations for launching aircraft
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- 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—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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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
- B64U50/15—Propulsion using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
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Abstract
The invention discloses a rotor unmanned aerial vehicle ejection system on a carrying system, wherein an ejection device of the ejection system is composed of a sleeve for accommodating and protecting an unmanned aerial vehicle and an ejection device positioned at the lower end of an inner cavity of the sleeve. Rotor unmanned aerial vehicle is folding accomodate the after-fixing on jettison gear upper end support type frame, the jettison gear upper end can with unmanned aerial vehicle carried outside from sleeve inner chamber bottom propelling movement to cavity, can make carrying system carry on the system when arriving predetermined airspace, pop out carrying system with rotor unmanned aerial vehicle from this carrying system in, make rotor unmanned aerial vehicle and carrying system separation come and go up through the layer board afterwards, unmanned aerial vehicle can accomplish tasks such as target location, topography survey and drawing, battlefield guide at predetermined airspace. This ejection system can make rotor unmanned aerial vehicle can reach this operation airspace that is difficult to be deployed fast, without extra energy consumption, has improved rotor unmanned aerial vehicle's energy utilization by a wide margin, has improved the deployment performance for rotor unmanned aerial vehicle possesses the ability of carrying out complicated task.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a rotor unmanned aerial vehicle ejection system on a carrying system.
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; the rotor unmanned aerial vehicle is an important branch of the unmanned aerial vehicle, can hover and perform special operations such as fixed-point shooting, and is influenced by the structural characteristics of the rotor unmanned aerial vehicle, the existing rotor unmanned aerial vehicle also has the specific defects that the flying speed is lower than that of a fixed-wing unmanned aerial vehicle, the flying height is greatly limited, and the special task requirements are difficult to meet; in addition, due to the lift force generation mode, the energy conversion efficiency is far lower than that of a fixed wing unmanned aerial vehicle during working, so that the working radius is smaller, and the unmanned aerial vehicle is difficult to perform remote tasks.
For the above reasons, the present inventors have devised a system of transporting capable of cooperating with a rotorcraft and an ejection system for separating the rotorcraft from the system of transporting, and carried the rotorcraft to a specific position through the system of transporting, and separated the rotorcraft from the system of transporting through the ejection system, thereby solving the above problems.
Disclosure of Invention
In order to overcome the problems, the inventor of the invention has conducted intensive research to design a rotor unmanned plane ejection system on a carrying system,
the ejection system is composed of a sleeve for accommodating and protecting the unmanned aerial vehicle and an ejection device positioned at the lower end of an inner cavity of the sleeve. Rotor unmanned aerial vehicle is folding accomodate the after-fixing on jettison gear upper end support type frame, jettison gear can with the unmanned aerial vehicle that carries outside from sleeve inner chamber bottom propelling movement to cavity, can make when carrying on the system and reacing predetermined airspace, pop out rotor unmanned aerial vehicle from this system of carrying on, make rotor unmanned aerial vehicle and system of carrying on separate through the bearing board is come and go, unmanned aerial vehicle can accomplish tasks such as target location, topography survey and drawing, battlefield guide in predetermined airspace. This ejection system can make rotor unmanned aerial vehicle can reach this operation airspace that is difficult to be deployed fast, without extra energy consumption, has improved rotor unmanned aerial vehicle's energy utilization by a wide margin, has improved the deployment performance for rotor unmanned aerial vehicle possesses the ability of carrying out complicated task.
The invention is completed by a carrying system at the upper end of the ejection device of the inner cavity of the ejection device.
In particular, it is an object of the present invention to provide a rotorcraft ejection system on a carrier system,
the ejection system comprises a sleeve 2 for accommodating the unmanned gyroplane 1 and an ejection device 3 positioned at the lower end of an inner cavity of the sleeve 2.
Wherein the rotor unmanned aerial vehicle 1 is fixed on the ejection device 3 after being folded and stored and is positioned in the inner cavity of the sleeve 2,
jettison device 3 can launch to the inner chamber upper end of sleeve 2 from the inner chamber lower extreme of sleeve 2, makes rotor unmanned aerial vehicle 1 follow separate in the 2 inner chambers of sleeve.
Wherein the sleeve 2 is arranged at the side of the carrying system,
an openable cabin door 4 is arranged on the side part of the carrying system;
the upper end of the sleeve 2 abuts against the inside of the hatch door 4.
Wherein, hatch door 4 opens when the system of shipping reaches predetermined airspace to jettison device 3 pops out rotor unmanned aerial vehicle 1 from the system of shipping.
The ejection device 3 comprises an ejection base 31 positioned at the lower end and a support jig 32 positioned above the ejection base 31, and a bearing plate 33 is arranged in an inner cavity of the support jig 32;
the ejector base 31 is ejected to the upper end of the inner cavity of the sleeve 2 by the cooperation of the ejector base 31 and the support jig 32,
by constraining the rotorcraft 1 by said support profile 32,
through the supporting plate 33 promotes rotor unmanned aerial vehicle 1, makes rotor unmanned aerial vehicle 1 and support type frame 32 separation.
Wherein, the supporting plate 33 can move along the axial direction of the outer end of the supporting fixture 32 at the upper end of the inner cavity of the supporting fixture 32, and the unmanned rotorcraft 1 positioned at the upper end of the inner cavity of the supporting fixture 32 is pushed out of the supporting fixture 32.
Wherein the rotary wing drone comprises a fuselage 11 and a horn 12;
when the arm 12 of the unmanned rotorcraft is bent downwards relative to the fuselage 11, the outer end of the arm 12 of the unmanned rotorcraft can be embedded into the support jig 32 and then is restrained on the support jig 32,
when the rotorcraft is detached from the support cradle 32, the arm 12 of the drone is automatically deployed to the working position and locked, starting the work.
The rotor unmanned aerial vehicle further comprises a connecting disc 13 arranged right below the vehicle body 11;
the machine arm 12 is controlled to be bent downwards or unfolded to a horizontal position by controlling the displacement of the connecting disc 13 in the vertical direction.
Wherein, an elastic pad 41 is arranged inside the hatch 4;
when the form is closed to hatch door 4, cushion 41 and the rotor unmanned aerial vehicle 1 butt that is located the sleeve 2 inner chamber to restrain rotor unmanned aerial vehicle 1 in sleeve 2.
The method for ejecting the rotor unmanned aerial vehicle by the device comprises the following steps:
step 3, ejecting the ejection device 3 from the lower end of the inner cavity of the sleeve 2 to the upper end of the inner cavity of the sleeve 2, so that the rotor unmanned aerial vehicle 1 moves to the outside of the carrying system;
step 4, the supporting plate 33 moves upwards to push the unmanned rotorcraft 1 out of the support type frame 32, so that the unmanned rotorcraft 1 is separated from the support type frame 32 outside the carrying system, and the horn 12 of the unmanned rotorcraft is unfolded to the working position and locked to start working.
The invention has the advantages that:
(1) the rotary wing unmanned aerial vehicle ejection device on the carrying system is arranged at any part of the carrying system and can be deployed in multiple numbers, so that the purpose of rapidly deploying multiple rotary wing unmanned aerial vehicles is achieved;
(2) according to the unmanned gyroplane ejection device on the carrying system, provided by the invention, the unmanned gyroplane can be conveyed to a designated area through the carrying system, the unmanned gyroplane ejection device has the capability of quickly reaching a remote operation site, is high in working efficiency, and can execute tasks with special requirements on reaction speed and starting time, such as fire reconnaissance and the like;
(3) according to the rotor unmanned aerial vehicle ejection device on the carrying system, provided by the invention, the energy carried by the rotor unmanned aerial vehicle is not consumed before the rotor unmanned aerial vehicle 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
Figure 1 shows a schematic diagram of the overall architecture of a rotorcraft ejection system on a carrier system according to a preferred embodiment of the invention;
figure 2 shows a schematic structural view of a door on a rotorcraft ejection system on a carrier system open according to a preferred embodiment of the invention;
figure 3 shows a cross-sectional view of a support jig in a rotorcraft launch system on a carrier system according to a preferred embodiment of the present invention;
fig. 4 shows a schematic view of a gyroplane configuration in a gyroplane ejection system on a carrier system according to a preferred embodiment of the present invention.
The reference numbers illustrate:
1-rotor unmanned plane
11-fuselage
12-arm
121-horn carbon tube
122-bearing support
13-connecting disc
14-connecting rod
15-drive motor
16-propeller
2-sleeve
21-limit stop
3-ejection device
31-Ejection base
32-support type frame
33-bearing plate
4-cabin door
41-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 invention, a gyroplane ejection system on a carrying system is provided, as shown in fig. 1 and 2, the ejection system comprises a sleeve 2 for accommodating a gyroplane 1 and an ejection device 3 positioned at the bottom of the sleeve 2.
The rotor unmanned aerial vehicle 1 is fixed on the ejection device 3 after being folded and stored and is positioned in the inner cavity of the sleeve 2,
the ejection device 3 can eject from the lower end of the inner cavity of the sleeve 2 to the upper end of the sleeve 2, so that the unmanned rotorcraft 1 is ejected from the inner cavity of the sleeve 2; will the sleeve setting is in the system lateral part of transporting, and after rotor unmanned aerial vehicle 1 followed pop out in the sleeve 2, rotor unmanned aerial vehicle 1 is whole to be located outside the system of transporting promptly. A limit stop 21 is arranged inside the sleeve 2, near the opening, to prevent the ejector 3 from being completely ejected from the sleeve 2.
In a preferred embodiment, the load system releases the constraint on the unmanned gyroplane when reaching the deployment/scheduled airspace, so that the unmanned gyroplane is separated from the load system, and the unmanned plane is in a smaller distance from the scheduled working area, and can rapidly enter the working state; 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 counterforce generated by the rocket engine ejecting working medium; 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. Meanwhile, the invention can also be used for the launching task of the carrying system of a fixed wing or a helicopter.
Preferably, said sleeve 2 is arranged at the side of a carrier system, in which a plurality of said sleeves 2 may be arranged, at the side of which an openable hatch 4 is arranged; when the hatch door is closed, the upper end of the sleeve 2 abuts against the inner side of the hatch door 4; the cabin door 4 can be opened outwards, when the cabin door is opened, the upper end/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 4 is opened when the carrier system reaches a predetermined airspace, so that the launcher 3 ejects the rotorcraft 1 from the carrier system;
in the invention, the ejection substrate 31 is ejected to the upper end of the sleeve 2 by matching the ejection substrate 31 and the sleeve 2, the ejection between the sleeve 2 and the ejection substrate 31 can be performed in any of various ways, such as setting a compression spring as power to perform ejection, setting compressed air as power to perform ejection, setting an electromagnet to perform ejection by using repulsion force or attraction force, or using an electromagnetic induction coil as power to perform ejection, and the selection can be performed according to specific working requirements.
The cabin door 4 is opened when the carrying system reaches a preset airspace, so that the ejection device 3 ejects the rotor unmanned aerial vehicle 1 from the carrying system; the hatch door can be provided with a plurality of hatches or only one hatch door, 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 ejector 3 comprises an ejector base 31 at the bottom and a support jig 32 above the ejector base 31, and a support plate 33 is arranged in the inner cavity of the support jig 32;
the ejector base 31 is ejected to the upper end of the sleeve 2 by the cooperation of the ejector base 31 and the sleeve 2,
by constraining the rotorcraft 1 by said support profile 32,
through the support plate 33 promotes rotor unmanned aerial vehicle 1 for with rotor unmanned aerial vehicle 1 with support fixture 32 separation.
Specifically, as shown in fig. 1 and 3, the size of the support jig 32 is substantially the same as the outer diameter of the quasi-circular structure formed by folding the arms of the rotorcraft, so that the support jig 32 can be just embedded between the arms and the propeller of the rotorcraft, the end of the arm 12 abuts against the inner ring wall surface of the support jig 32, and the support jig 32 can block the arm 12 from rotating, and further block the arm 12 from unfolding to the horizontal position, thereby realizing the constraint on the unmanned plane; the height of the support fixture 32 is 30-50mm, i.e. the distance between the highest point of the support fixture 32 and the support plate 33 is 30-50mm, and since the support plate 33 can be moved in the vertical direction, the support plate 33 is at the lowest possible point when calculating this height/distance.
When the system of carring the retrains unmanned aerial vehicle, bearing board 33 is located the below of horn 12, and the distance between bearing board 33 and the horn is less, is less than 10mm generally, just bearing board 33 can move in vertical direction, and its moving distance is 30-50mm at least, along with the removal of bearing board 33, bearing board 33 can be released unmanned aerial vehicle's horn from bearing seat 2 promptly, because bearing board 33's translation rate is higher, when unmanned aerial vehicle and bearing seat 2 separated, unmanned aerial vehicle has certain initial speed, can continue to move certain distance along this direction.
The repulsion that bearing plate 33 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 axial displacement and promote rotor unmanned aerial vehicle's function can.
In a preferred embodiment, as shown in figures 1, 2 and 3,
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 before the carrying system is started, the preset time is filled, for example, the unfolding instruction is generated and sent after 40 s;
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 mainly through a GPS receiving module, a Beidou receiving module and other satellite positioning modules, when the detected state information meets preset conditions, a deployment instruction is generated and sent, for example, the deployment instruction is generated and sent when the detected state information reaches the position near 800m, or the deployment instruction is generated and sent when the detected state information reaches the position near east longitude 116.3 degrees and the north latitude 39.95 degrees, or the deployment instruction is generated and sent when the vertical direction speed value is 0;
the ground command refers to a control command sent by a ground control station and received by the 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 33 and used for controlling the supporting plate 33 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, an elastic pad 41 is provided inside the door 4; the elastic pad 41 is made of rubber or polymer material, and has certain elasticity and can bear certain acting force.
Under the circumstances that hatch door 4 was closed, cushion 41 and the rotor unmanned aerial vehicle 1 butt that is located the sleeve 2 inner chamber to fix rotor unmanned aerial vehicle 1 in sleeve 2, prevent rotor unmanned aerial vehicle vibration or swing in the system of transporting.
In a preferred embodiment, as shown in fig. 4, the rotary wing drone comprises a fuselage 11 and a horn 12; 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 drone is constrained within the carrier system when its arm 12 is bent downwards relative to the fuselage 11, preferably at an angle of around 90 degrees to enable the drone to be constrained within the carrier system; the most preferred bend angle in the present invention is 95 degrees.
When the carrying system releases the constraint on the unmanned aerial vehicle, the arm 12 of the unmanned aerial vehicle automatically expands to a horizontal position and starts working; specifically, when the horn 12 is automatically unfolded to the horizontal position under the action of the elastic force, the motor on the horn is started to work 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 are also started to work, such as a navigation system, a GPS (global positioning system) positioning system and the like, so that the unmanned aerial vehicle can determine the position as soon as possible, move to a target position and start to execute a preset operation task.
In a preferred embodiment, as shown in fig. 1 and 4, the drone further comprises a connection disc 13 disposed directly below the fuselage 11,
the connecting disc 13 moves axially to control the machine arm 12 to bend or unfold to a horizontal position. When the connecting disc 13 moves downwards, the machine arm 12 is driven to bend downwards, and when the connecting disc 13 moves upwards, the machine arm 12 is driven to expand to a working position; similarly, the connecting plate 13 can be driven to move downwards when the arm 12 bends downwards, and the connecting plate 13 can be driven to move upwards when the arm 12 is unfolded to the horizontal position.
In particular, preferably, a connecting rod 14 is provided on said connecting disc 13,
one end of the connecting rod 14 is hinged with the connecting plate 3,
the other end of the connecting rod 14 is connected with the horn 12. The number of links 14 corresponds to the number of arms 12, one for each other.
Further preferably, the horn 12 includes a horn carbon tube 121,
a bearing support 122 is sleeved on the horn carbon tube 121, and the annular sleeve 122 can slide back and forth along the horn carbon tube 121, or the annular sleeve 122 is fixed on the horn carbon tube 121;
the connecting rod 14 is hinged to the bearing support 122, that is, the connecting rod 14 is hinged to the horn 12 through the bearing support 122.
Preferably, a limiting mechanism is arranged on the connecting plate 3 and the machine body 11, so that the machine 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 13 and the body 11,
the stretching mechanism is used for pulling the connecting disc 13 to be close to the machine body 11 upwards, and then driving the machine arm 12 to be unfolded to a horizontal position. The stretching mechanism comprises a vertically arranged spring which is always in a stretching state; when the horn 12 is bent downward, a large elastic potential energy is stored in the stretching mechanism, so that the horn 12 has a tendency of returning to a horizontal position, and when an external force for limiting and restraining the horn 12 disappears, the horn 12 can accelerate and rotate from a stationary state at a large acceleration under the action of the stretching mechanism, and is unfolded to the horizontal position from a downward bent state.
Further preferably, a torsion spring is arranged at two hinged positions, one end of the connecting rod 14 is hinged with the connecting plate 3, and the connecting rod 14 is hinged with the bearing support 122, and the torsion spring is also a part of the stretching mechanism, so that the elasticity required to be overcome by the mechanical arm 12 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 mechanical arm 122 is bent downwards; this torsion spring can also make the effort that receives a plurality of directions on connecting rod 14 and the horn 12, ensures that connecting rod 14 and horn 12 move according to setting for the orbit, and then strengthens this system's reliability, in predetermined airspace, when releasing the restraint to unmanned aerial vehicle, unmanned aerial vehicle's horn must can expand to horizontal position.
In a preferred embodiment, as shown in fig. 1 and 4, a driving motor 15 and a propeller 16 are provided at the end of the arm 12, the driving motor 15 is used for controlling the propeller 16 to rotate, and when the unmanned aerial vehicle is constrained in a carrying system, a control circuit of the driving motor 15 is in a standby state; an induction switch is arranged at the joint of the machine arm and the machine body, the induction switch is triggered when the machine arm returns to the horizontal position, and after the induction switch is triggered, a control circuit of the driving motor 15 is switched on, and the driving motor 15 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 horn 12 and the propeller 16, one part of the driving motor 15 is embedded in the horn 12, the other part is exposed outside, and the end of the exposed outside is provided with the propeller 16.
Preferably, the horn 12 is provided with a plurality, preferably 4-8,
when the unmanned aerial vehicle is constrained in a carrying system, a plurality of the preset gaps corresponding to the horn 12 are circularly arranged; the carrying system restrains the unmanned aerial vehicle through the gap, namely, a support type frame 32 which prevents the arm 12 from unfolding to the horizontal position is embedded in the gap, and under the action of elastic force on the arm, the whole unmanned aerial vehicle is fixed and restrained in the carrying system.
The invention also provides a method for ejecting the rotor unmanned aerial vehicle by the rotor unmanned aerial vehicle ejection device on the carrying system, which comprises the following steps:
step 3, ejecting the ejection device 3 from the bottom of the sleeve 2 to the upper end of the sleeve 2;
step 4, the supporting plate 33 moves upwards to push the unmanned rotorcraft 1 out of the support fixture 32, so that the unmanned rotorcraft 1 is separated from the support fixture 32 outside the carrying system, and the horn 12 of the unmanned rotorcraft is unfolded to the horizontal position and starts to work.
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 rotor unmanned aerial vehicle ejection system on a carrying system, which is characterized in that,
this jettison device is including sleeve (2) that hold rotor unmanned aerial vehicle (1) and be located jettison device (3) of this sleeve (2) bottom.
2. The ejection system of claim 1,
the rotor unmanned aerial vehicle (1) is fixed on the ejection device (3) after being folded and stored and is positioned in the cavity inner cavity of the sleeve (2),
jettison device (3) can follow sleeve (2) inner chamber lower extreme and launch to outside sleeve (2) upper end cavity, make rotor unmanned aerial vehicle (1) follow pop out in sleeve (2) cavity.
3. The ejection device of claim 1,
the cavity of the sleeve (2) is arranged at the side part of the carrying system,
an openable cabin door (4) is arranged at the side part of the carrying system;
the upper end face of the cavity of the sleeve (2) abuts against the inner side of the cabin door (4).
4. The ejection system of claim 3,
the cabin door (4) is opened when the carrying system arrives at a deployment airspace, so that the ejection device (3) ejects the rotor unmanned aerial vehicle (1) from the carrying system.
5. The ejection system of claim 1,
the ejection device (3) comprises an ejection base (31) positioned at the lower end and a support type frame (32) positioned at the upper end of the ejection base (31), and a bearing plate (33) is arranged in an inner cavity of the upper end of the support type frame (32);
the ejection base (31) is ejected to the upper end of the sleeve (2) by matching the ejection base (31) with the sleeve (2),
restrain the rotor unmanned aerial vehicle (1) through the support fixture (32),
through the supporting plate (33) pushes the rotor unmanned aerial vehicle (1) so that the rotor unmanned aerial vehicle (1) is separated from the supporting fixture (32).
6. The ejection system of claim 5,
the supporting plate (33) can move along the direction of the pointed upper end of the axis of the supporting fixture (32) in the inner cavity of the supporting fixture (32), so that the unmanned rotorcraft (1) positioned at the upper end of the inner cavity of the supporting fixture (32) is separated from the supporting fixture (32).
7. The ejection system of claim 5,
the rotor unmanned aerial vehicle (1) comprises a vehicle body (11) and a vehicle arm (12);
when the rotor unmanned aerial vehicle (1) is bent downwards relative to the fuselage (11) by the horn (12), the outer end of the horn (12) can be embedded into the support fixture (32) and constrained on the support fixture (32),
when rotor unmanned aerial vehicle (1) with during separation in support type frame (32), rotor unmanned aerial vehicle (1) horn (12) are automatic to be launched to horizontal position and locking, the back start work.
8. The ejection system of claim 7,
the rotor unmanned aerial vehicle (1) further comprises a connecting disc (13) arranged right below the vehicle body (11);
the machine arm (12) is controlled to be bent downwards or unfolded to a working position by controlling the displacement of the connecting disc (13) in the vertical direction.
9. The ejection system of claim 3,
an elastic pad (41) is arranged on the inner side of the cabin door (4);
when hatch door (4) closed the form, cushion (41) and rotor unmanned aerial vehicle (1) butt that is located sleeve (2) inner chamber make rotor unmanned aerial vehicle (1) retrain in sleeve (2) inner chamber.
10. A method of system ejection of a rotary wing drone according to any one of claims 1 to 9, comprising the steps of:
step 1, restraining a rotor unmanned aerial vehicle (1) on an ejection device (3) in an inner cavity of a sleeve (2), and closing a cabin door (4);
step 2, opening a cabin door (4) when the carrying system reaches a preset airspace;
step 3, ejecting the ejection device (3) from the lower end of the inner cavity of the sleeve (2) to the upper end of the inner cavity of the sleeve (2) to enable the rotor unmanned aerial vehicle (1) to move to the outside of the carrying system;
step 4, bearing board (33) rebound with rotor unmanned aerial vehicle (1) release from supporting type frame (32), make rotor unmanned aerial vehicle (1) carry the system outside and support type frame (32) separation, rotor unmanned aerial vehicle's horn (12) expand to operating position and locking, start work.
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