CN113232854B - Distributed unmanned aerial vehicle platform applied to ballistic launching and launching method - Google Patents
Distributed unmanned aerial vehicle platform applied to ballistic launching and launching method Download PDFInfo
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- CN113232854B CN113232854B CN202110533385.8A CN202110533385A CN113232854B CN 113232854 B CN113232854 B CN 113232854B CN 202110533385 A CN202110533385 A CN 202110533385A CN 113232854 B CN113232854 B CN 113232854B
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- 230000005540 biological transmission Effects 0.000 claims description 12
- 238000004146 energy storage Methods 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 5
- 230000010354 integration Effects 0.000 abstract description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] 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
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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Abstract
The invention relates to a distributed unmanned aerial vehicle platform applied to ballistic launching and a launching method, wherein two task machines with the same structure are symmetrically distributed around a protecting and conveying machine, and each task machine is connected with the protecting and conveying machine through a connecting mechanism to form an aerial vehicle platform body; the task plane and the escort plane are both tail seat type unmanned planes, two first power systems are arranged on a body of the task plane, wings are arranged at two ends of the body of the task plane, and second power systems are arranged at the end parts of the wings; the flight platform body finishes the shape following storage with the launching device through the tail stay bar, liquid/air pressure is converted into mechanical kinetic energy through the launching device to be launched, the flight platform cooperatively rotates to fly horizontally after the preset height is reached, the flight platform is separated after the carrying resources are transmitted to the mission machine by the protection and delivery machine, the protection and delivery machine returns, and the mission machine also performs the return voyage after the mission machine finishes the mission; the invention realizes the integration of storage, transportation and launching of the ballistic launch tailstock type unmanned aerial vehicle, and the combined type flight platform improves the stability of effective task load, voyage and takeoff.
Description
Technical Field
The invention relates to a distributed unmanned aerial vehicle platform applied to ballistic launching and a launching method, and belongs to the technical field of aviation.
Background
Under the horizontal flight state of tail sitting posture unmanned aerial vehicle, fly with conventional fixed wing aircraft mode, it is easy to control. Under the transition flight state, thrust commutates for the organism synchronization, and the conversion process simplifies to the maneuver of fixed wing aircraft, and the manipulation is simple and convenient, easily realize, however because tail sitting posture unmanned aerial vehicle takes off the aircraft tail when taking off, whole organism is as the windward side when taking off, and maneuverability and stability are relatively poor. The types of the existing mature trajectory launching unmanned aerial vehicle are a fixed wing and a rotor type with single function, such as American spring blades (Switchblade), BattleHawk (BattleHawk) individual missile, Israel hero 30 individual missile, Turkey Apague-II individual missile and Sloack predator AX-1 individual missile, and the trajectory launching SOUID unmanned aerial vehicle with a foldable rotor system and an autonomous unfolding capability proposed by California university and the firefly individual missile type comprise firefly individual missile developed by Israel, RotemL quadrotor missile and the future complex war environment.
In the prior art, patent document No. CN110127067A discloses a combined vertical take-off and landing high-speed fixed-wing unmanned aerial vehicle platform, which comprises an oiling machine, a mission machine, a connecting mechanism and an oil pipeline, wherein two ends of the connecting mechanism are respectively connected with the fuselage or the wing of the oiling machine and the mission machine, and two ends of the oil pipeline are respectively connected with the oil tanks of the oiling machine and the mission machine. The fuel charger adopts a tail-seated vertical take-off and landing unmanned aerial vehicle, the mission machine adopts a stealth high-speed unmanned aerial vehicle, the combined vertical take-off and the coordinated horizontal take-off are realized, the fuel charger conveys fuel to the mission machine through an oil conveying pipe, then the fuel charger is separated from the mission machine and returns to the vertical landing, the mission machine returns after completing the mission, the fuel charger vertically takes off and turns to the horizontal flight state to be close to the mission machine, the fuel charger and the mission machine are butted through a connecting mechanism, and the fuel charger and the mission machine return to and vertically land.
Patent document No. CN208484842U discloses a folding wing drone launching device, including: base, control valve, gas receiver, launching tube and tray. The base is provided with a first cavity, a second cavity and a channel arranged in the base, and the first cavity and the second cavity are communicated through the channel; the control valve is arranged in the first cavity and provided with an air inlet and an air outlet, and the air inlet is positioned in the channel and communicated with the second cavity; one end of the air storage cylinder is fixed on the base, and a cavity of the air storage cylinder is communicated with the second cavity; one end of the launching tube is fixed on the base, and the cavity of the launching tube is communicated with the air outlet; the supporting block is arranged in the cavity of the launching tube; when the control valve is powered off, the air cylinder and the launching tube are closed, and when the control valve is powered on, the air cylinder is communicated with the launching tube. Although the invention provides a folding wing unmanned aerial vehicle launching device, the folding wing unmanned aerial vehicle is a rotor aircraft, and has a defect in high-speed and large-range cruising function after launching.
Therefore, a new flying platform is needed to solve the difficulties of the prior art.
Disclosure of Invention
The invention provides a distributed unmanned aerial vehicle platform applied to ballistic launching and a launching method, which are suitable for large unmanned aerial vehicles, and have the advantages of strong reliability, good carrying capacity and long voyage.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a distributed unmanned aerial vehicle platform applied to ballistic launching comprises a protection and conveying machine, wherein two task machines with the same structure are symmetrically distributed around the protection and conveying machine, and each task machine is connected with the protection and conveying machine through a connecting mechanism to form an aerial vehicle platform body;
the task machine comprises a task machine body, wherein two first power systems are arranged on the part, opposite to the protection and conveying machine, of the task machine body, the two first power systems are distributed on two sides of the connecting mechanism, wings are symmetrically arranged at two ends of the task machine body, and a second power system is arranged at the end part of each wing; two support rods are arranged on one side of the body of the task machine, which is provided with the first power system, and are symmetrically distributed on two sides of the connecting mechanism through support rod driving devices;
the other side of the body of the mission machine is symmetrically provided with tail stay bars, one end of each tail stay bar is connected with the body of the mission machine through a tail stay bar driving device, the other end of each tail stay bar is provided with a tail stay vertical tail wing, and the two tail stay vertical tail wings are connected through a tail stay horizontal tail wing; a task machine elevator is arranged at the position of the wing close to the tail boom horizontal tail wing;
the conveying protection machine comprises a conveying protection machine body, a power device is arranged at the top end of the conveying protection machine body, a rudder and a lifting rudder are arranged at each radial part of the cross structure, communicated hollow parts are arranged in the cross structure, and a material storage part is formed by the hollow parts; the radial part of the cross structure which is relatively arranged is connected with a transmission port of the connecting mechanism to realize the transmission function;
the flying platform body is arranged in the launching device before launching;
as a further preferable mode of the present invention, the first power system is connected to the mission machine body through a first power system connection member;
the second power system is connected with the wing through a second power system connecting piece;
as a further preferred aspect of the present invention, the tail stay bar and the support bar each include a connection portion and a hinge portion, the connection portion of the tail stay bar is used for connecting a matched tail stay horizontal tail wing, and the hinge portion of the tail stay bar is used for hinging the mission machine body;
the connecting part of the supporting rod is used for supporting the mission machine on the ground, and the hinged part of the supporting rod is hinged with the mission machine body;
as a further preferred aspect of the present invention, when the flight platform body is separated by the launching device, the tail stay driving device drives the tail stay, and the support bar driving device drives the support bar, so that the tail stay and the support bar are closed toward the mission machine body;
as a further preferred aspect of the present invention, the launching device includes a launching tube, a front support connecting lug of the launching tube is mounted at a position close to the tube opening, one end of the front support of the launching tube is hinged with the front support connecting lug of the launching tube, and the other end of the front support of the launching tube is hinged with the front fixing seat of the launching tube;
one end of a rear support of the launching tube is fixed at the bottom of the launching tube, and the other end of the rear support of the launching tube is hinged with a rear fixing seat of the launching tube;
the front support and the rear support of the launch canister are matched to fix the canister opening of the launch canister towards the sky, and an included angle is formed between the central axis of the launch canister and the ground;
as a further optimization of the invention, a launching tube floating piston is embedded in the launching tube at a position close to the bottom of the launching tube, a launching tube ejection control valve is installed on the launching tube floating piston, launching tube following fixtures are symmetrically installed on the inner tube wall of the launching tube, a braking device is installed at the inner tube opening of the launching tube, and the launching tube following fixtures are located between the braking device and the launching tube floating piston;
the bottom of the launching tube is communicated with the energy storage tank through a gas delivery pipe;
as a further preferable mode of the invention, a launching tube handle is arranged on the outer wall of the launching tube;
as a further preferable mode of the invention, the distance between the two oppositely arranged mission machines is the same as the length of each mission machine wing after being unfolded;
a launching method based on the distributed unmanned aerial vehicle platform applied to ballistic launching specifically comprises the following steps:
firstly, before the flight platform body is launched, the whole structure is embedded in a launching tube, the bottom of the flight platform body is propped against a floating piston of the launching tube, and the top of the flight platform body is positioned through a following fixture of the launching tube;
in the second step, in the pressurizing stage, the energy storage tank releases large-volume compressed liquid or compressed gas into the launching tube through a gas transmission pipe so as to instantly pressurize the launching tube;
thirdly, in the launching stage, the compressed liquid or the compressed gas expands to push the launching floating piston in the launching tube to abut against the flying platform body to realize accelerated motion, the flying platform body pushes the launching tube to move along with the type clamp towards the tube opening until the flying platform body is thrown away from the tube opening of the launching tube, and at the moment, the launching tube impacts the braking device along with the type clamp;
fourthly, in a pressure relief stage, after the flight platform body is separated from the launching tube, starting a launching tube ejection control valve to relieve the pressure in the launching tube;
and fifthly, after the flying platform body reaches the preset height, the flying platform body is converted into flat flight, the escort machine transmits the carried resources to the mission machine, the connecting mechanism is unlocked, the flying platform body is separated, the escort machine returns and vertically descends, and the mission machine returns and vertically descends after completing the mission.
Through the technical scheme, compared with the prior art, the invention has the following beneficial effects:
1. task machines are symmetrically distributed on two sides of the escort machine and combined to form a rectangular unmanned aerial platform, so that the following difficulty of the shape of an inner cylinder of a launching device is reduced, and the stability and the robustness of the unmanned aerial platform after launching are improved;
2. the distributed structure provided by the invention is suitable for large-scale unmanned aerial vehicles, has a plurality of power sources and strong reliability, and obviously improves the carrying capacity;
3. according to the invention, the mission machine and the escort machine are combined to form a flight platform, and after resource transmission and separation are carried out in the air, the flight speed and range of the whole mission machine can be effectively improved, and the requirement on the performance index of an energy power system is reduced;
4. the flying platform provided by the invention adopts a ballistic launching mode, so that the difficulty and the cost of taking off the platform are reduced, and the pneumatic safety and the reliability are improved.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a perspective view of a preferred embodiment provided by the present invention;
FIG. 2 is a schematic diagram of a task machine structure according to a preferred embodiment of the present invention;
FIG. 3 is a schematic structural view of a escort machine according to a preferred embodiment of the present invention;
FIG. 4 is a perspective view of a transmitting device of a preferred embodiment provided by the present invention;
fig. 5 is a cross-sectional view of a transmitting device of a preferred embodiment provided by the present invention.
In the figure: 1 is a first task machine, 11 is a task machine body, 12 is a wing, 13 is a first power system, 14 is a first power system connecting piece, 15 is a second power system connecting piece, 16 is a second power system, 17 is a supporting rod, 18 is a task machine elevator, 19 is a tail supporting rod driving device, 110 is a supporting rod driving device, 111 is a tail supporting rod, 112 is a tail supporting horizontal tail wing, 113 is a tail supporting vertical tail wing, 2 is a protecting and conveying machine, 21 is a power device, 22 is a protecting and conveying machine body, 23 is a material storage place, 24 is a rudder, 25 is an elevator, 3 is a second task machine, 4 is a transmission port, 5 is a connecting mechanism, 6 is a transmitting device, 61 is a transmitting barrel, 62 is a transmitting barrel front support connecting support lug, 63 is a transmitting barrel front support, 64 is a transmitting barrel front fixing seat, 65 is a transmitting barrel rear support, 66 is a transmitting barrel rear support, 67 is a gas pipe, 68 is an energy storage tank, 69 is a braking device, 610 is a launching tube handle, 611 is a launching tube following clamp, 612 is a launching tube floating piston, and 613 is a launching tube ejection control valve.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings. In the description of the present application, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
In the prior art, most unmanned aerial vehicles are single-machine four rotors or double-machine eight rotors and are asymmetric, so that the control of the combined four rotors is difficult, and particularly, on a large unmanned aerial vehicle, if a rotor aircraft is insist on adopting, the cruising speed is inevitably weak due to no wing, and the carrying capacity is influenced.
The application aims at providing a flight platform which is suitable for large unmanned aerial vehicles, in arrangement, two task machines with the same structure are symmetrically arranged around a protective conveyor 2, each task machine is connected with the protective conveyor through a connecting mechanism 5 to form a flight platform body, the flight platform body is symmetrically arranged in a rectangular shape, and the controllable effect is improved; because the application is mainly applied to the large unmanned aerial vehicle, the mission machine only needs to be provided with two sets because the aircraft is large in submission and the weight is increased; specifically, as shown in fig. 1, for convenience of explaining the specific structure, two mission machines symmetrically arranged are respectively defined as a first mission machine 1 and a second mission machine 3, only one mission machine is described because the first mission machine and the second mission machine have the same structure, fig. 2 shows a mission machine body 11, two first power systems 13 are installed on the part of the mission machine body opposite to the escort machine, the two first power systems are connected and distributed on two sides of a connecting mechanism through first power system connecting pieces 14, wings are symmetrically installed on two ends of the mission machine body, a second power system 16 is installed on the end of each wing 12 through a second power system connecting piece 15, because the mission machine body is provided with the wings, the cruise speed can be obviously improved and the cruise distance can be prolonged similarly to a fixed wing aircraft during cruising, and meanwhile, each mission machine comprises four power sources, reliability and carrying capacity can be improved.
Two support rods 17 are arranged on one side of the body of the task machine, which is provided with the first power system, and are symmetrically distributed on two sides of the connecting mechanism through support rod driving devices 110; the other side of the mission machine body is symmetrically provided with tail stay rods 111, one end of each tail stay rod is connected with the mission machine body through a tail stay rod driving device 19, the other end of each tail stay rod is provided with a tail stay vertical tail wing 113, and the two tail stay vertical tail wings are connected through a tail stay horizontal tail wing 112; a task machine elevator 18 is arranged at the position of the wing close to the tail boom horizontal tail wing; the arrangement of the tail stay bar and the support bar can maintain the balance of the corresponding task machine when the tail stay bar and the support bar are respectively opened and closed towards opposite directions of the body of the task machine; when the flight platform body is separated by the launching device 6, the tail stay rod driving device drives the tail stay rod, and the support rod driving device drives the support rod, so that the tail stay rod and the support rod are closed towards the body of the mission machine body.
The tail stay bar and the support bar are arranged to comprise a connecting part and a hinge part, the connecting part of the tail stay bar is used for connecting a matched tail stay horizontal tail wing, and the hinge part of the tail stay bar is used for hinging a mission machine body; the connecting part of the supporting rod is used for supporting the mission machine on the ground, and the hinged part of the supporting rod is hinged with the mission machine body. The supporting rod driving device drives the hinged part of the supporting rod, and the connecting part of the supporting rod rotates relative to the hinged part and contracts towards the body direction of the mission machine body; the tail stay bar driving device drives the hinged part of the tail stay bar, and the connected part of the tail stay bar rotates and contracts towards the direction of the body of the mission machine; meanwhile, the change of the angle of the tail support rod or the support rod can be realized through the position change of the hinge device, so that the adjustment of the attitude of the undercarriage is realized.
Fig. 3 is a schematic structural diagram of a escort machine provided by the present application, which includes a escort machine body 22 arranged in a cross structure, a power device 21 is installed at the top end of the escort machine body, a rudder 24 and an elevator 25 are installed at each radial part of the cross structure, a communicated hollow part is arranged inside the cross structure, and the hollow part forms a material storage 23; the radial part of the cross structure which is relatively arranged is connected with a transmission port 4 of the connecting mechanism to realize the transmission function; the connecting mechanism is a common part in the field of aircrafts and is not described herein; in order to achieve a better flight effect, the distance between the two oppositely arranged mission machines is the same as the length of each mission machine wing after being unfolded. After the whole flying platform body reaches a preset height after being ejected out, the platform flies flatly, the escort machine transmits the carried resources in the material storage place to the task machine, the connecting mechanism is unlocked, the flying platform body is automatically separated, the escort machine returns in advance and runs in the vertical landing direction, and after the task machine completes a corresponding task, the escort machine returns in the vertical landing mode.
The launching device is also provided, namely, the flying platform adopts a ballistic launching mode, so that the difficulty and the cost of taking off the platform are reduced, and the pneumatic safety and the reliability are improved; specifically, as shown in fig. 4 and 5, the launching device includes a launching tube 61, a front support connecting lug 62 of the launching tube is mounted at a position close to the tube opening, one end of a front support 63 of the launching tube is hinged with the front support connecting lug of the launching tube, and the other end of the front support of the launching tube is hinged with a front fixing seat 64 of the launching tube; one end of a rear support 65 of the launching tube is fixed at the bottom of the launching tube, and the other end of the rear support of the launching tube is hinged with a rear fixing seat 66 of the launching tube; the launcher front support and the launcher rear support are matched to fix the opening of the launcher towards the sky, and an included angle is formed between the central axis of the launcher and the ground. Before launching, the whole flight platform body is integrally embedded into the launch canister, the size of the flight platform body is matched with the diameter of the launch canister, and folding is not needed; a launching tube floating piston 612 is embedded in the launching tube at a position close to the bottom of the launching tube, a launching tube ejection control valve 613 is installed on the launching tube floating piston, launching tube following type fixtures 611 are symmetrically installed on the inner tube wall of the launching tube, a braking device 69 is installed at the opening of the inner tube of the launching tube, and the launching tube following type fixtures are located between the braking device and the launching tube floating piston; when the flight platform body is embedded into the launching tube, the bottom end of the flight platform body supports against the floating piston of the launching tube, and the top end of the flight platform is limited by the launching tube following fixture. To facilitate the displacement, a launch barrel handle 610 is mounted on the outer wall of the launch barrel.
Finally, the application also provides a launching method of the flight platform body, wherein the launching method comprises three stages, namely a pressurization stage, a launching stage and a pressure relief stage, wherein in the pressurization stage, the bottom of the launching tube is communicated with an energy storage tank 68 through a gas pipe 67, the energy storage tank instantly releases a large amount of compressed liquid/gas, and the liquid/gas is distributed to the launching tube through a launching tube ejection control valve to realize instant pressurization; the high-pressure liquid/gas expansion pushes a launching barrel floating piston in the launching barrel to abut against the unmanned aerial vehicle platform to realize accelerated motion, the unmanned aerial vehicle platform is thrown away from the barrel, and after the unmanned aerial vehicle platform is launched, the pressure in the launching barrel is relieved; the method comprises the following specific steps:
firstly, before the flight platform body is launched, the whole structure is embedded in a launching tube, the bottom of the flight platform body is propped against a floating piston of the launching tube, and the top of the flight platform body is positioned through a following fixture of the launching tube;
in the second step, in the pressurizing stage, the energy storage tank releases large-volume compressed liquid or compressed gas into the launching tube through a gas transmission pipe so as to instantly pressurize the launching tube;
thirdly, in the launching stage, the compressed liquid or the compressed gas expands to push the launching floating piston in the launching tube to abut against the flying platform body to realize accelerated motion, the flying platform body pushes the launching tube to move along with the type clamp towards the tube opening until the flying platform body is thrown away from the tube opening of the launching tube, and at the moment, the launching tube impacts the braking device along with the type clamp;
fourthly, in a pressure relief stage, after the flight platform body is separated from the launching tube, starting a launching tube ejection control valve to relieve the pressure in the launching tube;
and fifthly, after the flying platform body reaches the preset height, the flying platform body is converted into flat flight, the escort machine transmits the carried resources to the mission machine, the connecting mechanism is unlocked, the flying platform body is separated, the escort machine returns and vertically descends, and the mission machine returns and vertically descends after completing the mission.
To sum up, integration is sent out in storage and transportation that this application has realized trajectory transmission tailstock formula unmanned aerial vehicle, and the flight platform of combination formula has promoted the stability of payload, voyage and taking off.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The meaning of "and/or" as used herein is intended to include both the individual components or both.
The term "connected" as used herein may mean either a direct connection between components or an indirect connection between components via other components.
In light of the foregoing description of the preferred embodiment of the present invention, many modifications and variations will be apparent to those skilled in the art without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (9)
1. A distributed unmanned aerial vehicle platform for ballistic launch, comprising: the flight platform comprises a protection conveyor, wherein two task machines with the same structure are symmetrically distributed around the protection conveyor, and each task machine is connected with the protection conveyor through a connecting mechanism to form a flight platform body;
the task machine comprises a task machine body, wherein two first power systems are arranged on the part, opposite to the protection and conveying machine, of the task machine body, the two first power systems are distributed on two sides of the connecting mechanism, wings are symmetrically arranged at two ends of the task machine body, and a second power system is arranged at the end part of each wing; two support rods are arranged on one side of the body of the task machine, which is provided with the first power system, and are symmetrically distributed on two sides of the connecting mechanism through support rod driving devices;
the other side of the body of the mission machine is symmetrically provided with tail stay bars, one end of each tail stay bar is connected with the body of the mission machine through a tail stay bar driving device, the other end of each tail stay bar is provided with a tail stay vertical tail wing, and the two tail stay vertical tail wings are connected through a tail stay horizontal tail wing; a task machine elevator is arranged at the position of the wing close to the tail boom horizontal tail wing;
the conveying protection machine comprises a conveying protection machine body, a power device is arranged at the top end of the conveying protection machine body, a rudder and a lifting rudder are arranged at each radial part of the cross structure, communicated hollow parts are arranged in the cross structure, and a material storage part is formed by the hollow parts; the radial part of the cross structure which is relatively arranged is connected with a transmission port of the connecting mechanism to realize the transmission function;
the flying platform comprises a flying platform body and is characterized by further comprising a launching device, wherein the flying platform body is arranged in the launching device before launching.
2. The distributed unmanned aerial vehicle platform for ballistic launch of claim 1, wherein: the first power system is connected with the mission machine body through a first power system connecting piece;
the second power system is connected with the wing through a second power system connecting piece.
3. The distributed unmanned aerial vehicle platform for ballistic launch of claim 1, wherein: the tail stay bar and the support bar both comprise a connecting part and a hinged part, the connecting part of the tail stay bar is used for connecting the matched tail stay horizontal tail wing, and the hinged part of the tail stay bar is used for hinging the body of the mission machine body;
the connecting part of the supporting rod is used for supporting the mission machine on the ground, and the hinged part of the supporting rod is hinged with the mission machine body.
4. The distributed unmanned aerial vehicle platform for ballistic launch of claim 3, wherein: when the flight platform body is separated by the launching device, the tail stay rod driving device drives the tail stay rod, and the support rod driving device drives the support rod, so that the tail stay rod and the support rod are closed towards the direction of the body of the mission machine.
5. The distributed unmanned aerial vehicle platform for ballistic launch of claim 1, wherein: the launching device comprises a launching tube, a front support connecting lug of the launching tube is arranged at a position close to a tube opening of the launching tube, one end of a front support of the launching tube is hinged with the front support connecting lug of the launching tube, and the other end of the front support of the launching tube is hinged with a front fixing seat of the launching tube;
one end of a rear support of the launching tube is fixed at the bottom of the launching tube, and the other end of the rear support of the launching tube is hinged with a rear fixing seat of the launching tube;
the launcher front support and the launcher rear support are matched to fix the opening of the launcher towards the sky, and an included angle is formed between the central axis of the launcher and the ground.
6. The distributed unmanned aerial vehicle platform for ballistic launch of claim 1, wherein: a launching tube floating piston is embedded in the launching tube at a position close to the bottom of the launching tube, a launching tube ejection control valve is installed on the launching tube floating piston, launching tube following type fixtures are symmetrically installed on the inner tube wall of the launching tube, a braking device is installed at the opening of the inner tube of the launching tube, and the launching tube following type fixtures are located between the braking device and the launching tube floating piston;
the bottom of the launching tube is communicated with the energy storage tank through a gas conveying pipe.
7. The distributed unmanned aerial vehicle platform for ballistic launch of claim 1, wherein: the outer wall of the launching tube is provided with a launching tube handle.
8. The distributed unmanned aerial vehicle platform for ballistic launch of claim 1, wherein: the distance between the two oppositely arranged mission machines is the same as the length of each mission machine wing after being unfolded.
9. A launching method for a distributed unmanned aerial vehicle platform applied to ballistic launching, based on any one of claims 1-8, characterized in that: the method specifically comprises the following steps:
firstly, before the flight platform body is launched, the whole structure is embedded in a launching tube, the bottom of the flight platform body is propped against a floating piston of the launching tube, and the top of the flight platform body is positioned through a following fixture of the launching tube;
in the second step, in the pressurizing stage, the energy storage tank releases large-volume compressed liquid or compressed gas into the launching tube through a gas transmission pipe so as to instantly pressurize the launching tube;
thirdly, in the launching stage, the compressed liquid or the compressed gas expands to push the launching floating piston in the launching tube to abut against the flying platform body to realize accelerated motion, the flying platform body pushes the launching tube to move along with the type clamp towards the tube opening until the flying platform body is thrown away from the tube opening of the launching tube, and at the moment, the launching tube impacts the braking device along with the type clamp;
fourthly, in a pressure relief stage, after the flight platform body is separated from the launching tube, starting a launching tube ejection control valve to relieve the pressure in the launching tube;
and fifthly, after the flying platform body reaches the preset height, the flying platform body is converted into flat flight, the escort machine transmits the carried resources to the mission machine, the connecting mechanism is unlocked, the flying platform body is separated, the escort machine returns and vertically descends, and the mission machine returns and vertically descends after completing the mission.
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