A missile-borne unmanned aerial vehicle delivery system structure

Abstract

The present invention discloses a missile-borne UAV delivery system structure, including a UAV component, an engine component and a missile structure component; the missile structure component cover is arranged on the outside of the UAV component and the engine component, the UAV component is connected to the engine component through an explosive bolt, and the delivery power is provided by the engine component, and the explosive bolt is controlled to break through a separation controller to separate the engine component from the UAV component, and the delivery of the UAV component is completed. The present invention can effectively solve the problem of deceleration of the missile-borne UAV delivery system at the end of the trajectory, and will not introduce redundant materials to interfere with the normal operation of the UAV rotor; the separation process will not produce redundant materials except for the overall structure of the engine, the structural separation is fast, and the separation components have strong integrity, and it has high practical application value.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicle delivery system structure, and in particular to a missile-borne unmanned aerial vehicle delivery system structure. Background Art

[0002] Multi-rotor unmanned aerial vehicles have the characteristics of easy take-off and hovering operation, and have been widely used in many fields. In the civilian field, multi-rotor unmanned aerial vehicles can excellently complete tasks such as forest fire prevention, earthquake disaster relief, geological surveys, line patrols, landform surveying and mapping, and aerial photography.

[0003] However, due to the limitation of volume and space and the difficulty of making major technological breakthroughs in existing battery technology in a short period of time, multi-rotor unmanned aerial vehicles have the disadvantages of short range, short flight time, slow speed, etc., making it difficult to meet the needs of rapid and long-distance delivery operations. The existing solution is mainly to deliver through transport aircraft, but there are many limitations for transport aircraft in wartime, such as the need to take off from an airport, which makes it difficult to meet the requirements of close-range combat, etc., while missile-type transport platforms can be directly ignited after loading to meet the requirements of rapidity; different charges and launch angles can be selected according to the distance of the target to meet the distance requirements of different combat missions; missile-type transport platforms also have the advantages of small target features, strong penetration capability, and fast flight speed, and are more ideal transport platforms for multi-rotor unmanned aerial vehicles.

[0004] However, the current difficulty of the missile-borne UAV delivery system is the matching problem between the deceleration of the missile at the end of the trajectory and the deployment of the UAV. The missile flies at a high speed, while the UAV needs a lower speed to start and stabilize. The speed difference between the two is large. How to decelerate the missile speed after reaching the target area to provide a good deployment opportunity for the normal operation of the UAV is particularly important. There are two main solutions at this stage. The first is to choose a fixed-wing UAV, which is more suitable for cylindrical folding, but the fixed-wing UAV cannot perform hovering operations; the second is to choose to shut down the engine at the end of the trajectory and use a deceleration parachute to decelerate, but the deceleration parachute has an unpredictable flight trajectory after the engine is separated from the UAV, and it is impossible to guarantee whether it will affect the normal operation of the UAV rotor. Therefore, effectively solving the deceleration problem with as little excess as possible has become a difficulty in the missile-borne UAV delivery system. Summary of the invention

[0005] The purpose of the present invention is to overcome the defects of the prior art and provide a missile-borne UAV delivery system structure, which can effectively solve the problem of deceleration of the missile-borne UAV delivery system at the end of the trajectory, and will not introduce redundant materials to interfere with the normal operation of the UAV rotor. In addition to the overall structure of the engine, no redundant materials will be generated during the separation process, and the structure separation is fast and the separation components have strong integrity.

[0006] The objective of the present invention is achieved as follows: a missile-borne UAV delivery system structure comprises a UAV component, an engine component and a missile structure component; the missile structure component cover is arranged on the outside of the UAV component and the engine component, the UAV component is connected to the engine component through an explosive bolt, and the delivery power is provided by the engine component, and the explosive bolt is controlled to break through a separation controller to separate the engine component from the UAV component, thereby completing the delivery of the UAV component.

[0007] When the present invention is working, the propulsion engine and the reverse thrust engine are combined to form an engine assembly of the missile-borne UAV delivery system. The propulsion engine and the propulsion engine start-up timing are controlled by an ignition timing controller. The delivery system can be effectively decelerated at the end of the trajectory of the missile-borne UAV delivery system, and no excess material is generated after the deceleration is completed. After the overall engine assembly has finished working, the explosive bolts connecting the engine assembly and the UAV assembly are broken, prompting the engine assembly to separate from the UAV assembly, thereby completing the effective delivery of the UAV assembly.

[0008] In order to effectively transport the payload by the missile-borne UAV delivery system, the UAV assembly includes a hub, a main rotor, a motor, a flight control cabin, a power supply, a stabilization system and a payload; the main rotor is connected to the hub via a pin, the hub is connected to the motor via a center shaft spline, and the motor, flight control cabin, power supply, stabilization system and payload are all fixedly connected to a component bay reinforcement frame pre-installed in the UAV cabin via bolts.

[0009] In order to keep the drone assembly in a stable flight state, the stabilization system includes a rotor power arm, a rotor motor and an aileron; the aileron is connected to the rotor motor through a pin, and the rotor motor is fixed to the wing power arm through bolts.

[0010] In order to provide transportation power for the missile-borne UAV delivery system, the engine assembly includes explosive bolts, flanges, support rods, reverse thrust nozzles, reverse thrust engines, propulsion engines and main nozzles; the explosive bolts are connected to the flanges through threads; the flanges are aligned and pressed with the outer shell base of the UAV assembly, and the UAV assembly is connected to the engine assembly through explosive bolts; one end of the support rod is connected to the flange, and the other end is fixed to the reverse thrust engine, and the shells of the reverse thrust engine, propulsion engine and main nozzle are integrally formed.

[0011] In order to ensure the structural stability and sealing of the drone assembly and engine assembly of the missile-borne drone delivery system, the missile structural assembly includes a drone hood, a sealing ring, an engine outer cover and a tail wing component; the detachable cover of the drone hood is arranged on the outside of the drone assembly and is connected to the flange through a pin, the sealing ring is arranged between the drone hood and the engine outer cover, the engine outer cover is fixedly connected to the reverse thrust engine by bolts, and the tail wing component is fixedly connected to the casing of the propulsion engine.

[0012] Furthermore, the tail wing component includes a torsion spring, a tail wing and a tail wing base; the tail wing is connected to the tail wing base through a torsion spring and a pin; the tail wing component is fixedly connected to the casing of the propulsion engine through the tail wing base integrally formed with the engine casing.

[0013] In order to effectively decelerate the delivery system at the end of the trajectory of the missile-borne UAV delivery system, the flight control cabin is equipped with flight control hardware of the missile-borne UAV delivery system, flight control hardware of the UAV component, ignition timing controller of the engine component and separation controller.

[0014] The present invention adopts the above technical scheme, and compared with the prior art, the beneficial effects are as follows: the missile-borne UAV delivery system structure includes a UAV component, an engine component (including two functions of propulsion and deceleration) and a missile structure component, a part of the missile structure component is discarded before the engine is separated from the UAV, and the remaining part is fixedly connected to the engine structure and separated from the UAV component together; the separation process will not produce any excess material except the overall structure of the engine, the structural separation is fast and the separation components have strong integrity, which solves the deceleration problem of the missile-borne UAV delivery system at the end of the trajectory, and minimizes the introduction of excess material, reducing the risk of interfering with the normal operation of the UAV rotor, and has a high practical application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the appearance structure of the present invention.

[0016] Figure 2 It is a cross-sectional view of the symmetric surface structure of the present invention.

[0017] Figure 3 Schematic diagram of the structure of the drone assembly of the present invention.

[0018] Figure 4 It is a schematic diagram of the structure of the stabilization system of the drone assembly of the present invention.

[0019] Figure 5 It is a schematic diagram of the structure of the engine assembly of the present invention.

[0020] Figure 6 It is a schematic diagram of the structure of the missile structural assembly of the present invention.

[0021] Figure 7 It is a cross-sectional view of the tail wing component of the missile structural assembly of the present invention.

[0022] Figure 8 This is an operational action example A of the missile-borne UAV delivery system of the present invention.

[0023] Fig. 9 This is operation action example B of the missile-borne UAV delivery system of the present invention.

[0024] Fig.10 This is the operation action example C of the missile-borne UAV delivery system of the present invention.

[0025] Fig.11 This is an operational action example D of the missile-borne UAV delivery system of the present invention.

[0026] Fig.12 This is the operation action example E of the missile-borne UAV delivery system of the present invention.

[0027] Fig.13 This is an operational action example F of the missile-borne UAV delivery system of the present invention.

[0028] Fig.14 This is an operational action example G of the missile-borne UAV delivery system of the present invention.

[0029] Fig.15 This is an operational action example H of the missile-borne UAV delivery system of the present invention.

[0030] Among them, 1 UAV component, 11 hub, 12 main rotor, 13 motor, 14 flight control cabin, 15 power supply, 16 stabilization system, 161 rotor power arm, 162 rotor motor, 163 aileron, 17 load; 2 engine component, 21 explosive bolt, 22 flange, 23 support rod, 24 reverse thrust nozzle, 25 reverse thrust engine, 26 propulsion engine, 27 main nozzle; 3 missile structure component, 31 UAV hood, 32 sealing ring, 33 engine outer cover, 34 tail wing component, 341 torsion spring, 342 tail wing, 343 tail wing base. DETAILED DESCRIPTION

[0031] like Figure 1-2 The structure of a missile-borne UAV delivery system shown in the figure includes a UAV component 1, an engine component 2 and a missile structure component 3; the missile structure component 3 is covered on the outside of the UAV component 1 and the engine component 2, the UAV component 1 is connected to the engine component 2 through an explosive bolt 21, and the delivery power is provided by the engine component 2. The explosive bolt 21 is controlled to break through a separation controller, so that the engine component 2 is separated from the UAV component 1, and the delivery of the UAV component 1 is completed.

[0032] The UAV component 1 effectively transports the payload for the missile-borne UAV delivery system, the engine component 2 provides the transport power for the missile-borne UAV delivery system, and the missile structure component 3 provides the UAV component 1 and the engine component 2 with structural stability and sealing guarantee for the UAV delivery system.

[0033] like Figure 3As shown, the UAV component 1 includes a hub 11, a main rotor 12, a motor 13, a flight control cabin 14, a power supply 15, a stabilization system 16 and a load 17; the main rotor 12 is connected to the hub 11 through a pin, and the hub 11 is connected to the motor 13 through a center shaft spline, and the motor 13, the flight control cabin 14, the power supply 15, the stabilization system 16 and the load 17 are all fixedly connected to the component cabin reinforcement frame pre-installed in the UAV cabin by bolts; the flight control cabin 14 is provided with the flight control hardware of the missile-borne UAV delivery system, the flight control hardware of the UAV component 1, the ignition timing controller of the engine component 2 and the separation controller.

[0034] like Figure 4 As shown, the stabilization system 16 includes a rotor power arm 161, a rotor motor 162 and an aile rotor 163; the aile rotor 163 is connected to the rotor motor 162 through a pin, and the rotor motor 162 is fixed to the rotor power arm 161 through bolts.

[0035] like Figure 5 As shown, the engine assembly 2 includes an explosive bolt 21, a flange 22, a support rod 23, a reverse thrust nozzle 24, a reverse thrust engine 25, a propulsion engine 26 and a main nozzle 27; the explosive bolt 21 is connected to the flange 22 by a thread; the flange 22 is aligned and pressed with the shell base of the UAV assembly 1, and the UAV assembly 1 is connected to the engine assembly 2 by the explosive bolt 21; one end of the support rod 23 is connected to the flange 22, and the other end is fixed to the reverse thrust engine 25, and the shells of the reverse thrust engine 25, the propulsion engine 26 and the main nozzle 27 are integrally formed. The propulsion overload transmitted by the engine is mainly transmitted to the shell base of the UAV by the structure of the flange 22 itself, and the explosive bolt 21 itself does not bear the overload; the explosive bolt 21 can be controlled to break through the separation controller at an appropriate time to ensure that the engine assembly 2 and the UAV assembly 1 are normally separated.

[0036] There is a hollow cavity inside the explosive bolt 21, which is filled with explosives. Under the control of the separation controller, the explosives explode to force the explosive bolt 21 to break; the propulsion engine 26 and the reverse thrust engine 25 can be started and stopped at the appropriate time and correct time under the control of the ignition timing controller.

[0037] like Figure 6 As shown, the missile structure assembly 3 includes a UAV hood 31, a sealing ring 32, an engine cover 33 and a tail wing component 34; the detachable cover of the UAV hood 31 is arranged on the outside of the UAV assembly 1 and is connected to the flange 22 through a pin, and the pin can automatically pop open after receiving the hood separation signal to ensure the normal separation of the UAV hood 31; the sealing ring 32 is arranged between the UAV hood 31 and the engine cover 33 to ensure the sealing between the UAV hood 31 and the flange 22; the engine cover 33 is fixedly connected to the reverse thrust engine 25 by bolts, and the tail wing component 34 is fixedly connected to the shell of the propulsion engine 26.

[0038] like Figure 7 As shown, the tail wing component 34 includes a torsion spring 341, a tail wing 342 and a tail wing base 343; the tail wing 342 is connected to the tail wing base 343 through the torsion spring 341 and the pin; the tail wing component 34 is fixed to the casing of the propulsion engine 26 through the tail wing base 343 which is integrally formed with the engine casing.

[0039] When the present invention is working, the missile-borne UAV delivery system structure maintains the A state (such as Figure 8 ) are stored in a storage box. When transported to the launch area, the missile-borne UAV delivery system of the present invention starts the following workflow:

[0040] 1) The missile-borne UAV delivery system structure is loaded into the launch tube in state A, and the staff loads combat parameters such as target area information before launch. The launch system preheats and activates the power supply 15, and the flight control system in the flight control cabin 14 is activated and starts working;

[0041] 2) The staff issues a launch command, the missile-borne UAV delivery system structure propulsion engine 26 ignites, pushes the missile-borne UAV delivery system structure out of the launch tube, the tail wing component 34 limit device fails, the tail wing 342 rebounds under the action of the torsion spring 341 and is limited under the joint action of the tail wing base 343 and the torsion spring 341, and the missile-borne UAV delivery system structure state changes to state B, such as Fig. 9 As shown; the propulsion engine 26 continues to provide power for the flight of the missile-borne UAV delivery system structure;

[0042] 3) The flight control system in the flight control cabin 14 determines through sensors that the target area has been reached, and the propulsion engine is shut down. When igniting, the controller needs to control the reverse thrust engine to ignite, and high-temperature and high-pressure gas is ejected from the reverse thrust nozzle 24, forcing the missile-borne UAV delivery system to slow down. After the reverse thrust engine is stopped, the UAV head cover 31 separates to both sides, and the missile-borne UAV delivery system structure is in state C ( Fig.10 ) as shown;

[0043] 4) After the drone head cover 31 is separated, the state of the missile-borne drone delivery system of the present invention changes to state D, such as Fig.11 As shown;

[0044] 5) The separation controller issues a separation command, and the explosive in the explosive bolt 21 explodes, forcing the explosive bolt 21 to break. The explosion instantly provides sufficient separation force for the UAV component 1 and the engine component 2, forcing the UAV component 1 and the engine component 2 to separate, and the state of the missile-borne UAV delivery system changes to the E state, such as Fig.12 As shown;

[0045] 6) After the drone component 1 and the engine component 2 are completely separated, they become the F state, such as Fig.13 As shown;

[0046] 7) The motor 13 of the drone component 1 starts to work, driving the propeller hub 11 to rotate, and the main rotor 12 naturally unfolds under the action of centrifugal force. After the main rotor 12 works normally, the flight control system controls the drone component 1 to be in a hovering state and reaches the G state, such as Fig.14 As shown;

[0047] 8) The stabilization system 16 starts to work, the rotor power arm 161 is unlocked in the limit state, rebounds and unfolds in place under the action of the torsion spring, and is limited under the action of the groove and the torsion spring. The rotor motor 162 is powered on and works, and the auxiliary rotor 163 is naturally unfolded in place under the action of centrifugal force. The flight control system controls the drone component 1 to be in a stable flight state, that is, the H state, such as Fig.15 As shown;

[0048] 9) At this point, the missile-borne UAV delivery system of the present invention has completed all preset actions, and the UAV component 1 will start the preset work task with the payload 17.

[0049] The present invention includes a UAV component, an engine component (including two functions of propulsion and deceleration) and a missile structure component. The ignition timing controller controls the start-up timing of the propulsion engine and the reverse thrust engine. At the end of the trajectory of the missile-borne UAV delivery system, the delivery system can be effectively decelerated, and no excess material is generated after the deceleration is completed. After the overall engine component is completed, the explosive bolt connecting the engine component and the UAV component breaks, prompting the engine component to separate from the UAV component, and completing the effective delivery of the UAV component.

[0050] The present invention is not limited to the above-mentioned embodiments. On the basis of the technical solution disclosed in the present invention, technicians in this field can make some substitutions and deformations to some technical features therein according to the disclosed technical content without creative labor, and these substitutions and deformations are all within the protection scope of the present invention.

Claims

1. A missile-borne UAV delivery system structure, characterized in that: The invention comprises a drone component (1), an engine component (2) and a missile structure component (3); the missile structure component (3) is covered on the outside of the drone component (1) and the engine component (2); the drone component (1) is connected to the engine component (2) via an explosive bolt (21); the engine component (2) provides delivery power; the explosive bolt (21) is controlled to break via a separation controller, so that the engine component (2) is separated from the drone component (1), and delivery of the drone component (1) is completed; The drone assembly (1) comprises a rotor hub (11), a main rotor (12), a motor (13), a flight control cabin (14), a power supply (15), a stabilization system (16) and a load (17); the stabilization system (16) comprises a rotor power arm (161), a rotor motor (162) and an auxiliary rotor (163); the auxiliary rotor (163) is connected to the rotor motor (162) via a pin, and the rotor motor (162) is fixedly connected to the rotor power arm (161) via bolts; The engine assembly (2) comprises an explosive bolt (21), a flange (22), a support rod (23), a thrust reverser nozzle (24), a thrust reverser engine (25), a propulsion engine (26) and a main nozzle (27); the explosive bolt (21) is connected to the flange (22) via a thread; the flange (22) is aligned and pressed against the shell base of the UAV assembly (1), and the UAV assembly (1) is connected to the engine assembly (2) via the explosive bolt (21); one end of the support rod (23) is connected to the flange (22), and the other end is fixed to the thrust reverser engine (25); the shells of the thrust reverser engine (25), the propulsion engine (26) and the main nozzle (27) are integrally formed; The missile structure assembly (3) comprises a drone head cover (31), a sealing ring (32), an engine cover (33) and a tail wing component (34); the detachable cover of the drone head cover (31) is arranged on the outside of the drone assembly (1) and is connected to the flange (22) via a pin; the sealing ring (32) is arranged between the drone head cover (31) and the engine cover (33); the engine cover (33) is fixedly connected to the reverse thrust engine (25) via bolts; and the tail wing component (34) is fixedly connected to the housing of the propulsion engine (26); The tail wing component (34) comprises a torsion spring (341), a tail wing (342) and a tail wing base (343); the tail wing (342) is connected to the tail wing base (343) via the torsion spring (341) and a pin; the tail wing component (34) is fixedly connected to the housing of the propulsion engine (26) via the tail wing base (343) which is integrally formed with the engine housing.

2. The missile-borne UAV delivery system structure according to claim 1 is characterized in that: The main rotor (12) is connected to the hub (11) via a pin, the hub (11) is connected to the motor (13) via a central shaft spline, and the motor (13), the flight control cabin (14), the power supply (15), the stabilization system (16) and the load (17) are all fixedly connected to a component cabin reinforcement frame pre-installed in the unmanned aircraft cabin via bolts.

3. The missile-borne UAV delivery system structure according to claim 2 is characterized in that: The flight control cabin (14) is provided with the flight control hardware of the missile-borne UAV delivery system, the flight control hardware of the UAV component (1), the ignition timing controller of the engine component (2), and the separation controller.

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