CN113232854B - A distributed unmanned aerial platform applied to ballistic launch and launch method - Google Patents

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

Distributed unmanned aerial platform applied to ballistic launch and launch method

technical field

The invention relates to a distributed unmanned aerial platform and a launching method applied to ballistic launch, and belongs to the field of aviation technology.

Background technique

When the tail-mounted UAV is in horizontal flight, it flies in the way of a conventional fixed-wing aircraft, which is easy to control. In the transitional flight state, the thrust is synchronously reversed relative to the body, and the conversion process is simplified to the maneuvering action of the fixed-wing aircraft, which is simple and easy to operate. , poor maneuverability and stability. Currently mature models of ballistic launch drones such as the American Switchblade, BattleHawk individual cruise missiles, Israeli Hero 30 individual cruise missiles, Turkey Apa Valley-II individual cruise missiles and Slovak Predator AX -1 Individual cruise missile, the rotor type includes the Firefly individual cruise missile developed by Israel, the RotemL four-rotor cruise missile and the ballistically launched SOUID UAV with a foldable rotor system and autonomous deployment capability proposed by the California Institute of Technology. The relatively simple fixed-wing and rotary-wing types have certain limitations in the complex war environment in the future.

In the prior art, the patent document with publication number CN110127067A discloses a combined vertical take-off and landing high-speed fixed-wing unmanned aerial platform, which is composed of a tanker, a mission aircraft, a connecting mechanism, and an oil pipeline. The two ends of the connecting mechanism are respectively connected with the tanker and the mission aircraft. The fuselage or wing is connected, and the two ends of the fuel pipe are respectively connected to the fuel tanks of the tanker and the mission aircraft. The tanker adopts a tail-sitting vertical take-off and landing UAV, and the mission aircraft adopts a stealth high-speed UAV, which takes off vertically in combination, and then transfers to level flight in coordination. Separated and returned and landed vertically, the mission aircraft returned after completing the mission, the tanker took off vertically and turned into level flight to approach the mission aircraft. The performance indicators such as the payload, range, and cruising speed of the UAV have been improved, and the vertical launch and recovery of the stealth high-speed UAV has been realized, but the problem of poor take-off performance of the tail-mounted UAV has not been solved.

The patent document with the publication number CN208484842U discloses a folding-wing UAV launching device, which includes a base, a control valve, an air storage cylinder, a launching cylinder and a support block. The base is provided with a first cavity, a second cavity and a channel arranged inside the base, and the first cavity and the second cavity are communicated through the channel; the control valve is installed in the first cavity, and the control valve is provided with an air inlet and a The air outlet and the air inlet are located in the channel and communicated with the second cavity; one end of the air storage cylinder is fixed to the base, and the cavity of the air storage cylinder is communicated with the second cavity; one end of the launching cylinder is fixed to the base, and the cavity of the launching cylinder is It communicates with the air outlet; the support block is built into the cavity of the launch cylinder; when the control valve is powered off, the air storage cylinder and the launch cylinder are closed, and when the control valve is energized, the air storage cylinder and the launch cylinder are connected. Although the invention provides a folding-wing UAV launching device, the type of the folding-wing UAV is a rotary-wing aircraft, which lacks the function of high-speed and large-scale cruising after launch.

Therefore, it is urgent to develop a new type of flight platform that can solve the difficulties of the existing technology.

SUMMARY OF THE INVENTION

The invention provides a distributed unmanned aerial platform and a launching method for ballistic launch, which are suitable for large-scale unmanned aerial vehicles, have strong reliability, good carrying capacity and long range.

The technical scheme adopted by the present invention to solve its technical problems is:

A distributed unmanned flight platform applied to ballistic launch, including escort aircraft, two mission aircraft with the same structure are symmetrically arranged around the escort aircraft, and each mission aircraft is connected with the escort aircraft through a connecting mechanism to form a flight platform body;

The mission aircraft includes a main body of the mission aircraft, and two first power systems are installed on the part of the main body of the mission aircraft opposite to the escort aircraft, and the two first power systems are distributed on both sides of the connecting mechanism. The wings are installed symmetrically at both ends, and the second power system is installed at the end of each wing; two support rods are installed on the side where the first power system is installed on the main body of the mission aircraft, and the two support rods are symmetrical through the support rod drive device Distributed on both sides of the connecting mechanism;

The other side of the fuselage body of the mission aircraft is symmetrically installed with tail braces, and one end of each tail brace is connected to the main body of the mission aircraft through the tail brace driving device, and the other end of the tail brace is installed with a tail brace vertical tail, and two tail braces are installed. The vertical tail fins of the tail braces are connected by the horizontal tail fins of the tail braces; the elevators of the mission aircraft are installed at the positions of the wings close to the horizontal fins of the tail braces;

The escort includes an escort fuselage body, which is arranged in a cross structure, a power device is installed on the top of the escort fuselage body, a rudder and an elevator are installed on each radial part of the cross structure, and the interior of the cross structure is connected. The hollow part of the cross structure forms the material storage place; the radial part of the cross structure is connected with the transmission port of the connecting mechanism to realize the transmission function;

It also includes a launching device, and the flight platform body is arranged in the launching device before launching;

As a further preference of the present invention, the first power system is connected to the fuselage body of the mission aircraft through the first power system connector;

The second power system is connected to the wing through the second power system connector;

As a further preference of the present invention, the tail brace and the support rod both include a connecting part and a hinged part, the connecting part of the tail brace is used to connect the matching tail brace horizontal tail, and the hinge part of the tail brace is used to articulate the task machine body body;

The connecting part of the support rod is used to support the mission aircraft on the ground, and the hinged part of the support rod is hinged with the fuselage body of the mission aircraft;

As a further preference of the present invention, when the flight platform body is separated from the launching device, the tail strut driving device drives the tail strut, and the support rod driving device drives the support rod, so that the tail strut and the support rod are closed in the direction of the main body of the mission aircraft. ;

As a further preference of the present invention, the launching device includes a launching tube, and a connecting lug of the front bracket of the launching tube is installed near the opening of the tube, and one end of the front bracket of the launching tube is hinged with the connecting lug of the front bracket of the launching tube, and the front bracket of the launching tube is hinged. The other end is hinged to the front fixing seat of the launch cylinder;

One end of the rear bracket of the launch tube is fixed at the bottom of the launch tube, and the other end of the rear bracket of the launch tube is hinged with the rear fixing seat of the launch tube;

The front bracket of the launch tube and the rear bracket of the launch tube cooperate to fix the tube mouth of the launch tube towards the sky, and an angle is formed between the central axis of the launch tube and the ground;

As a further preference of the present invention, a launch cylinder floating piston is embedded in the launch cylinder near the bottom of the cylinder, a launch cylinder ejection control valve is installed on the launch cylinder floating piston, and a launch cylinder follower clamp is symmetrically installed on the inner cylinder wall of the launch cylinder, A braking device is installed at the inner cylinder opening of the launch cylinder, and the launch cylinder follower clamp is located between the braking device and the launch cylinder floating piston;

The bottom of the launch cylinder is communicated with the energy storage tank through the gas pipeline;

As a further preference of the present invention, a handle of the launch cylinder is installed on the outer wall of the launch cylinder;

As a further preference of the present invention, the distance between the two mission aircraft arranged oppositely is the same as the length of each mission aircraft after the wings are unfolded;

A launch method based on the described distributed unmanned aerial platform applied to ballistic launch, specifically comprising the following steps:

The first step, before the launch of the flight platform body, the entire structure is embedded in the launch tube, and the bottom of the flight platform body is against the launch tube floating piston, and the top of the flight platform body is positioned through the launch tube follower clamp;

The second step, the pressurization stage, the energy storage tank releases a large volume of compressed liquid or compressed gas into the launch cylinder through the gas pipeline, so as to instantly pressurize the launch cylinder;

In the third step, in the launching stage, the compressed liquid or compressed gas expands and pushes the launching floating piston in the launch cylinder against the flight platform body to achieve accelerated motion. The mouth of the launch cylinder is thrown away, at this time the launch cylinder hits the braking device with the clamp;

The fourth step, the pressure relief stage, after the flight platform body is separated from the launch cylinder, the launch cylinder ejection control valve is activated to release the pressure in the launch cylinder;

Step 5: After the flight platform body reaches the preset height, it turns to level flight. After the escort aircraft transfers the carrying resources to the mission aircraft, the connection mechanism is unlocked, the flight platform body is separated, the escort aircraft returns and land vertically, and the mission aircraft completes the mission. After that, go back and land vertically.

Through the above technical solutions, with respect to the prior art, the present invention has the following beneficial effects:

1. In the present invention, mission aircraft are symmetrically arranged on both sides of the escort aircraft, and the combination forms a rectangular unmanned aerial platform, which reduces the difficulty of conforming to the shape of the inner cylinder of the launching device, and improves the stability and robustness of the unmanned aerial platform after launching. sex;

2. The distributed structure provided by the present invention is suitable for large-scale unmanned aerial vehicles, and has many power sources and strong reliability, so that the carrying capacity is significantly improved;

3. The present invention combines the mission aircraft and the escort aircraft to form a flight platform. After resource transmission and separation in the air, the flight speed and range of the entire mission aircraft can be effectively improved, and the requirements for the performance indicators of the energy power system can be reduced;

4. The flight platform provided by the present invention adopts the ballistic launching method, which reduces the difficulty and cost of platform takeoff, and improves the aerodynamic safety and reliability.

Description of drawings

The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

1 is a perspective view of a preferred embodiment provided by the present invention;

2 is a schematic structural diagram of a task machine according to a preferred embodiment provided by the present invention;

3 is a schematic structural diagram of an escort machine according to a preferred embodiment provided by the present invention;

FIG. 4 is a perspective view of a launching device according to a preferred embodiment provided by the present invention;

FIG. 5 is a cross-sectional view of a launching device according to a preferred embodiment of the present invention.

In the figure: 1 is the first mission aircraft, 11 is the main body of the mission aircraft, 12 is the wing, 13 is the first power system, 14 is the first power system connector, 15 is the second power system connector, 16 is the second power system connector The second power system, 17 is the support rod, 18 is the elevator of the task machine, 19 is the tail support rod drive device, 110 is the support rod drive device, 111 is the tail support rod, 112 is the tail support horizontal tail, and 113 is the tail support vertical tail , 2 is the escort machine, 21 is the power unit, 22 is the body of the escort machine, 23 is the material storage place, 24 is the rudder, 25 is the elevator, 3 is the second task machine, 4 is the transmission port, and 5 is the connection mechanism, 6 is the launching device, 61 is the launching tube, 62 is the connecting lug of the launching tube front bracket, 63 is the launching tube front bracket, 64 is the launching tube front fixing seat, 65 is the launching tube rear bracket, 66 is the launching tube rear fixing seat, 67 is the gas pipe, 68 is the energy storage tank, 69 is the braking device, 610 is the launch tube handle, 611 is the launch tube follower clamp, 612 is the launch tube floating piston, and 613 is the launch tube ejection control valve.

Detailed ways

The present invention will now be described in further detail with reference to the accompanying drawings. In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "left side", "right side", "upper", "lower part", etc. are based on the orientation or positional relationship shown in the drawings, only For the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a particular orientation, be constructed and operate in a particular orientation, "first", "second", etc. importance, and therefore should not be construed as a limitation to the present invention. The specific dimensions used in this embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.

In the current technology, most of the unmanned aerial platforms are single-machine four-rotor, or dual-machine eight-rotor and asymmetrical, which makes it difficult to control the combined four-rotor, especially on large-scale unmanned aerial vehicles. The wing will inevitably lead to weak cruising speed and affect the carrying capacity.

The purpose of this application is to provide a flight platform, which is suitable for large-scale unmanned aerial vehicles. In the arrangement, two mission aircraft with the same structure are symmetrically arranged around the escort aircraft 2, and each mission aircraft is connected to the escort aircraft through the connecting mechanism 5. The connection forms the flight platform body, and the flight platform body is symmetrically arranged in a rectangular shape, which improves the controllable effect; since the application is mainly applied to large-scale unmanned aerial vehicles, the weight of the aircraft is increased due to the large aircraft submission, so the mission aircraft only needs to be set up with two Yes; specifically as shown in Figure 1, for the convenience of explaining the specific structure, the two symmetrically arranged task machines are defined as the first task machine 1 and the second task machine 3 respectively. Since the first task machine and the second task machine The structure is the same, so only one will be described. As shown in FIG. 2, the main body of the mission aircraft is included. A power system connector 14 is connected and distributed on both sides of the connecting mechanism. The two ends of the fuselage body of the mission aircraft are symmetrically installed with wings, and the end of each wing 12 is installed with a second power system 16 through the second power system connector 15 . , Since the fuselage has its own wings, it is similar to a fixed-wing aircraft when cruising, which can significantly increase the cruising speed and extend the cruising distance. At the same time, each mission aircraft includes four power sources, which can improve reliability and carrying capacity.

Two supporting rods 17 are installed on the side of the main body of the mission aircraft where the first power system is installed, and the two supporting rods are symmetrically distributed on both sides of the connecting mechanism through the supporting rod driving device 110; the other side of the main body of the mission aircraft is symmetrically installed A tail brace 111 is provided, and one end of each tail brace is connected to the main body of the mission aircraft through the tail brace driving device 19. The other end of the tail brace is installed with a vertical tail fin 113, and the two vertical fins pass between the two vertical fins. The tail support horizontal tail 112 is connected; the mission aircraft elevator 18 is installed at the position where the wing is close to the tail support horizontal tail; the setting of the tail support rod and the support rod, when the two are respectively opened and closed in the opposite direction of the mission aircraft body, can maintain the corresponding The balance of the mission aircraft; and when the flight platform body is separated from the launcher 6, the tail strut drive device drives the tail strut, and the support rod drive device drives the support rod, so that the tail strut and the support rod are closed toward the main body of the mission aircraft. .

Here, to realize the opening and closing and closing of the tail brace or the support rod, the tail brace and the support rod are arranged to include a connecting part and a hinge part, and the connecting part of the tail brace is used to connect the matching tail brace horizontal tail, tail brace The hinge part is used to hinge the fuselage body of the mission aircraft; the connecting part of the support rod is used to support the mission aircraft on the ground, and the hinge part of the support rod is hinged with the fuselage body of the mission aircraft. The support rod driving device drives the hinged part of the support rod, and the connecting part of the support rod rotates relative to the hinged part and shrinks in the direction of the main body of the task machine; When it rotates, it shrinks in the direction of the fuselage body of the mission aircraft; at the same time, through the position change of the hinge device, the angle of the tail strut or the support rod can also be changed, so as to realize the adjustment of the attitude of the landing gear.

3 is a schematic diagram of the structure of the escort machine provided in this application, including the escort machine body body 22, which is arranged in a cross structure, and a power unit 21 is installed on the top of the escort machine body body. Parts are installed with rudder 24 and elevator 25, the interior of the cross structure is a connected hollow part, and the hollow part forms a material storage place 23; the radial part of the cross structure relatively arranged is connected with the transmission port 4 of the connecting mechanism to realize the transmission function; the connecting mechanism is an aircraft The components that are more common in the field will not be described here; in order to achieve a better flight effect, the distance between the two mission aircraft that are arranged opposite to each other is the same as the length of each mission aircraft after the wings are unfolded. When the entire flight platform body reaches the predetermined height after being shot out, the platform will fly horizontally, and the escort aircraft will transfer the carrying resources placed in the material storage area to the mission aircraft, the connection mechanism will be unlocked, the flight platform body will be automatically separated, and the escort aircraft will return first and It runs in the vertical landing direction. When the mission machine completes the corresponding task, it returns to home in the same vertical landing method.

Next, the present application also provides a launching device, that is, the flight platform adopts the ballistic launching method, which reduces the difficulty and cost of platform take-off, and improves the aerodynamic safety and reliability; the specific FIG. 4 is shown in FIG. 5 , the launching device includes launching The barrel 61 is installed near the barrel mouth to install the connecting lug 62 of the front bracket of the firing barrel, one end of the front bracket 63 of the firing barrel is hinged with the connecting lug of the front bracket of the firing barrel, and the other end of the front bracket of the firing barrel is hinged to the front fixing seat 64 of the firing barrel; One end of the launch tube rear bracket 65 is fixed at the bottom of the launch tube, and the other end of the launch tube rear bracket is hinged with the launch tube rear fixing seat 66; the launch tube front bracket and the launch tube rear bracket cooperate to fix the launch tube mouth toward the sky, and An angle is formed between the central axis of the launch tube and the ground. Before launching, the entire flight platform body is integrally embedded in the launch tube, the size of the flight platform body matches the diameter of the launch tube, and no folding is required; the launch tube floating piston 612 is embedded in the launch tube near the bottom of the tube, and the launch tube floating piston The launch tube ejection control valve 613 is installed on the top of the launch tube, the launch tube follow-up clamp 611 is symmetrically installed on the inner tube wall of the launch tube, and the braking device 69 is installed at the inner tube mouth of the launch tube. The launch tube follow-up clamp is located between the brake device and the launch tube floating piston. time; when the flight platform body is embedded in the launch tube, the bottom end of the flight platform body presses against the launch tube floating piston, and the top of the flight platform is limited by the launch tube follower clamp. In order to facilitate the displacement, a handle 610 of the launch cylinder is installed on the outer wall of the launch cylinder.

Finally, this application also provides a launch method for the aforementioned flight platform body. There are actually three stages in this launch method, namely the pressurization stage, the launch stage and the pressure relief stage. In the pressurization stage, the bottom of the launch tube passes through the gas pipeline 67 is communicated with the energy storage tank 68, the energy storage tank releases a large amount of compressed liquid/gas instantaneously, and the liquid/gas is distributed to the launch cylinder through the launch cylinder ejection control valve to achieve instantaneous pressurization; the high-pressure liquid/gas expansion pushes the launch cylinder in the launch cylinder to float. The piston is pressed against the unmanned aerial platform to achieve accelerated motion, the unmanned aerial platform is thrown away from the cylinder, and after the unmanned aerial platform is launched, the pressure in the launch cylinder is released; the specific steps are as follows:

The first step, before the launch of the flight platform body, the entire structure is embedded in the launch tube, and the bottom of the flight platform body is against the launch tube floating piston, and the top of the flight platform body is positioned through the launch tube follower clamp;

The second step, the pressurization stage, the energy storage tank releases a large volume of compressed liquid or compressed gas into the launch cylinder through the gas pipeline, so as to instantly pressurize the launch cylinder;

In the third step, in the launching stage, the compressed liquid or compressed gas expands and pushes the launching floating piston in the launch cylinder against the flight platform body to achieve accelerated motion. The mouth of the launch cylinder is thrown away, at this time the launch cylinder hits the braking device with the clamp;

The fourth step, the pressure relief stage, after the flight platform body is separated from the launch cylinder, the launch cylinder ejection control valve is activated to release the pressure in the launch cylinder;

Step 5: After the flight platform body reaches the preset height, it turns to level flight. After the escort aircraft transfers the carrying resources to the mission aircraft, the connection mechanism is unlocked, the flight platform body is separated, the escort aircraft returns and land vertically, and the mission aircraft completes the mission. After that, go back and land vertically.

To sum up, the present application realizes the integration of storage, transportation and delivery of the ballistic-launched tailstock UAV, and the combined flight platform improves the stability of the effective mission load, range and take-off.

It will be understood by those of ordinary skill 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 should also be understood that terms such as those defined in general dictionaries should be understood to have meanings consistent with their meanings in the context of the prior art and, unless defined as herein, are not to be taken in an idealized or overly formal sense. explain.

The meaning of "and/or" described in this application means that each of them exists alone or both are included.

The meaning of "connection" described in this application may be a direct connection between components or an indirect connection between components through other components.

Taking the above ideal embodiments according to the present invention as inspiration, and through the above description, relevant personnel can make various changes and modifications without departing from the technical idea of the present invention. The technical scope of the present invention is not limited to the contents in the specification, and the technical scope 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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