All-terrain individual reconnaissance and attack integrated small unmanned aerial vehicle

Abstract

The invention relates to an all-terrain single-soldier reconnaissance and attack integrated small unmanned aerial vehicle, and relates to the technical field of reconnaissance and attack integrated unmanned aerial vehicles, the unmanned aerial vehicle comprises a vehicle body, a projectile body and a recoil mechanism, and the recoil mechanism comprises a recoil air bag arranged on the vehicle body and filled with gas with certain pressure; and the control assembly is arranged on the recoil air bag and controls the recoil air bag to communicate with the outside or to be closed, and after the projectile body is separated from the machine body, the control assembly controls the recoil air bag to communicate with the outside and enables air in the recoil air bag to be sprayed out, so that the machine body accelerates to move forwards under the combined action of the reverse thrust of the sprayed air and the driving force of the machine body. According to the unmanned aerial vehicle, after the projectile body falls off, the control assembly controls the recoil airbag to communicate with the outside, gas is sprayed out rapidly, forward reverse thrust is generated on the vehicle body, the risk that the unmanned aerial vehicle is tracked and shot down is greatly reduced, and the unmanned aerial vehicle can better meet the investigation and shooting requirements of all-terrain individual soldiers and other different environments.

Description

Technical Field

[0001] This application relates to the technical field of reconnaissance and strike integrated unmanned aerial vehicles (UAVs), and particularly to a small all-terrain single-soldier reconnaissance and strike integrated UAV. Background Art

[0002] UAV systems have been widely used in military and civilian fields. In particular, reconnaissance and strike integrated UAVs with both observation and strike capabilities have shown significant advantages. With the development of technology, the demand for UAVs is gradually moving towards miniaturization, intelligence, and multi-functionality, which has prompted researchers to continuously explore new technologies and design solutions to improve the performance of existing systems.

[0003] During flight, the UAV observes the target and then drops bombs for strike. To improve the strike accuracy, the UAV needs to decelerate before dropping the bomb, then drop the bomb, and then accelerate to fly away. However, the time spent from after dropping the bomb to completing the acceleration is relatively long, which increases the risk of the UAV being tracked and shot down and reduces the reconnaissance and strike capabilities of the UAV. Summary of the Invention

[0004] In order to reduce the risk of the UAV being tracked and shot down and improve the reconnaissance and strike capabilities of the UAV, this application provides a small all-terrain single-soldier reconnaissance and strike integrated UAV.

[0005] The small all-terrain single-soldier reconnaissance and strike integrated UAV provided by this application adopts the following technical solutions: The small all-terrain single-soldier reconnaissance and strike integrated UAV includes a fuselage, a projectile body, and a recoil mechanism. The recoil mechanism includes: A recoil airbag, which is arranged on the fuselage and filled with gas at a certain pressure; A control component, which is arranged on the recoil airbag and controls the connection or disconnection of the recoil airbag with the outside world. When the projectile body is separated from the fuselage, the control component controls the recoil airbag to communicate with the outside world and causes the gas in the recoil airbag to be ejected, so that the fuselage accelerates forward under the combined action of the reverse thrust of the ejected gas and its own driving force.

[0006] By adopting the above technical solutions, before the UAV takes off, a certain pressure of gas is filled into the recoil airbag to make the recoil airbag expand; during the flight of the fuselage, the fuselage drives the projectile body and the recoil mechanism to move together. When the fuselage observes and moves to the target, it decelerates to perform the bomb dropping operation; the projectile body drops, and the fuselage accelerates to move. At the same time, the control component controls the recoil airbag to communicate with the outside world, and the gas is quickly ejected under the combined action of the self-rebound force and air pressure of the recoil airbag, thereby generating a forward reverse thrust on the fuselage. The reverse thrust and the self-driving force of the fuselage are superimposed on each other, greatly accelerating the moving speed of the fuselage, thus greatly reducing the risk of the UAV being tracked and shot down, improving the reconnaissance and strike capabilities of the UAV, and enabling the UAV to better meet the reconnaissance and strike requirements in different environments such as all-terrain single-soldier.

[0007] Optionally, the control assembly includes: A jet pipe disposed on the recoil airbag and communicating with the inside of the recoil airbag; A control valve disposed on the jet pipe and used to control the opening or closing of the jet pipe. After the projectile body separates from the airframe, the control valve controls the opening of the jet pipe.

[0008] By adopting the above technical solution, the control valve controls the opening of the jet pipe, and the gas in the recoil airbag is ejected under the action of the recoil force and air pressure of the recoil airbag. The ejected gas can generate a reverse thrust on the airframe. The reverse thrust and the self-driving force of the airframe are in the same direction and are superimposed on each other, greatly accelerating the moving speed of the airframe and reducing the risk of the UAV being tracked and shot down.

[0009] Optionally, an interference mechanism is provided on the jet pipe, and the interference mechanism includes: An annular airbag disposed on the jet pipe and filled with pigment powder for forming smoke inside; A puncturing assembly disposed on the jet pipe and on the side of the control valve away from the recoil airbag. When the control valve is opened and the inert gas is ejected, the puncturing assembly is driven to move to puncture the annular airbag, so that the pigment powder mixed gas in the annular airbag is ejected and a smoke for interference is formed around the airframe.

[0010] By adopting the above technical solution, when the gas is quickly ejected through the jet pipe, a thrust is generated on the puncturing assembly. The thrust drives the puncturing assembly to puncture the annular airbag, causing the pigment powder to leak out. The gas pushes a large amount of pigment powder to be quickly ejected to form smoke around the airframe for interference, enabling the UAV to be stealthy. Therefore, under the dual action of the smoke and the reverse thrust, the risk of the UAV being tracked and shot down is greatly reduced, and the reconnaissance and strike ability of the UAV is improved.

[0011] At the same time, the annular airbag is disposed on the jet pipe and on the side of the control valve away from the recoil airbag, that is, the annular airbag and the pigment are located near the gas ejection port of the jet pipe. When the gas starts to be ejected, a large amount of pigment can be ejected under the push of the gas, quickly forming a large-area smoke, improving the smoke interference effect, further reducing the risk of the UAV being tracked and shot down, and improving the reconnaissance and strike ability of the UAV.

[0012] Optionally, the puncturing assembly includes: A thorn ring slidably disposed on the jet pipe in a direction close to or away from the annular airbag; A spring disposed on the outer side wall of the control valve and connected to the thorn ring and used to maintain the separation of the thorn ring from the annular airbag. After the control valve is opened, the gas pushes the thorn ring to puncture the annular airbag. After the control valve is closed, the thorn ring moves back to its original position under the action of the spring.

[0013] By adopting the above technical solution, when the gas is ejected, it pushes the thorn ring to move, and the thorn ring moves to pierce the annular airbag, so that the pigment in the annular airbag is ejected under the action of the gas to form smoke. After the control valve is closed, the thorn ring moves back to its original position under the action of the spring.

[0014] Optionally, the gas ejection pipe includes a connecting section detachably connected to the control valve and a gas ejection section. The connecting section is connected to the recoil airbag. An installation groove is coaxially formed on the inner side wall of one end of the gas ejection section close to the control valve. The annular airbag is snap-fitted and installed on the installation groove, and the thorn ring is slidably installed on the installation groove.

[0015] By adopting the above technical solution, after the annular airbag is punctured, when the gas pushes the pigment, it will also push the annular airbag to be extruded and fall from the gas ejection section; after the drone flies back, the gas ejection section is removed from the control valve, and the spring is connected to the control valve, so that the spring and the thorn ring are removed from the installation groove, and then the annular airbag is snap-fitted and installed onto the installation groove, the annular airbag is pushed to move in place, and then the gas ejection pipe is fixedly installed on the control valve, so that the thorn ring is slidably installed on the installation groove, thus enabling reuse and reducing the cost of the drone.

[0016] Optionally, a ventilation cavity with a frustum-shaped cross-section is formed on the inner side wall of the thorn ring. The diameter of the ventilation cavity at one end close to the recoil airbag is larger than that at one end close to the annular airbag, which is convenient for the gas to push the thorn ring to move, so that the gas in the gas ejection pipe sequentially passes through the inner sides of the ventilation cavity and the annular airbag.

[0017] By adopting the above technical solution, the gas can be more conveniently concentrated through the ventilation cavity, increasing the thrust of the gas ejection. Moreover, the gas is also convenient for pushing the thorn ring to move, making the whole process fast and stable, improving the smoke interference effect on the drone, further reducing the risk of the drone being tracked and shot down, and improving the detection and strike ability of the drone.

[0018] Optionally, the gas in the recoil airbag is an inert gas. The recoil mechanism further includes an inflation assembly, and the inflation assembly includes: An intake pipe, which is communicated with the recoil airbag and is used for inputting inert gas and is provided with an intake valve; A pressure detector, which is arranged on the intake pipe and is used for detecting the gas pressure.

[0019] By adopting the above technical solution, the inert gas can reduce the risk of danger when the gas pushes the pigment; the intake pipe is connected to the inflation structure, and then the intake valve is opened. The inflation structure fills the recoil airbag with inert gas through the intake pipe. The pressure detector is used for detecting the air pressure in the recoil airbag. When the air pressure reaches the specified value, both the intake valve and the inflation structure are closed, and then the intake pipe is disassembled from the inflation structure, so as to realize filling the recoil airbag with the inert gas of the required pressure.

[0020] Optionally, a pushing component for assisting in pushing the recoil airbag is provided on the body, and the pushing component includes: The first elastic member and the second elastic member are arranged on the body and located on both sides of the recoil airbag and press against both side surfaces of the recoil airbag under the action of elastic force. In the initial state, the first elastic member and the second elastic member are in a parallel state with each other, and after the recoil airbag is inflated, it pushes the first elastic member and the second elastic member to deform.

[0021] By adopting the above technical solution, after the gas in the recoil airbag is ejected for a period of time, the ejection effect of the gas will drop linearly, and the recoil airbag needs to be filled with gas and has elasticity. The material of the recoil airbag is relatively thin, so the elasticity of the recoil airbag has a certain limit, that is, the amount of gas in the recoil airbag is limited, thus reducing the thrust of the gas on the body.

[0022] The first elastic member and the second elastic member press against the recoil airbag under the action of elastic force, and the recoil airbag will also push the first elastic member and the second elastic member to deform after being inflated. Therefore, when the gas is ejected, the rebound of the first elastic member and the second elastic member can greatly improve the thrust generated during the gas ejection process, further reducing the risk of the UAV being tracked and shot down and improving the reconnaissance and strike ability of the UAV.

[0023] Optionally, a positioning mechanism for positioning the recoil airbag is provided on the body, and the positioning mechanism includes: A placement box is arranged on the body and is in an open state and is provided with a clamping groove for clamping and cooperating with the spray pipe; A locking component is arranged on the body and presses against the spray pipe for positioning. A closed placement chamber is formed between the locking component and the placement box, and the placement chamber is for placing and inflating the recoil airbag and for placing the control valve. The first elastic member and the second elastic member are respectively arranged on the placement box and the locking component.

[0024] By adopting the above technical solution, the recoil airbag is placed in the placement box, so that the spray pipe is clamped and installed in the clamping groove, and then the locking component abuts against the placement box and forms a closed placement chamber with the placement box. At the same time, the locking component presses against the spray pipe for positioning, thus realizing the installation of the recoil airbag. After the recoil airbag is inflated, it presses against the placement chamber for storage, so as to be able to protect the recoil airbag. At the same time, the control valve can also be placed in the placement chamber, reducing the damage to the recoil airbag and the control valve caused by the external environment, improving the stability of the operation of multiple structures, and at the same time reducing the risk of the recoil airbag being damaged due to excessive air pressure. And due to the limitation of the placement chamber, the air pressure in the recoil airbag can be increased to a certain extent, so as to further increase the ejection effect of the gas and the powder, further reducing the risk of the UAV being tracked and shot down and improving the reconnaissance and strike ability of the UAV.

[0025] Furthermore, the first elastic member and the second elastic member are respectively arranged on the placement box and the locking assembly. Therefore, after the locking assembly is locked, the first elastic member and the second elastic member are pressed against the recoil airbag. After the recoil airbag is inflated and expands, it pushes the first elastic member and the second elastic member to deform. Therefore, the placement box and the locking assembly can also protect the first elastic member and the second elastic member, reducing the damage of external impurities or water to the first elastic member and the second elastic member, improving the service life and stability of the vulnerable recoil airbag, control valve, first elastic member and second elastic member, further reducing the risk of the UAV being tracked and shot down, and improving the reconnaissance and strike ability of the UAV.

[0026] Optionally, the locking assembly includes: A locking box, which is rotatably arranged on the placement box and presses against the jet pipe for positioning, and the placement chamber is formed by the cooperation of the locking box and the placement box; A locking screw, which passes through the locking box and is threadedly connected to the placement box.

[0027] By adopting the above technical solution, the locking box is rotated and abutted against the placement box, so that a closed placement chamber is formed between the locking box and the placement box. The placement chamber can protect the recoil airbag, control valve, first elastic member and second elastic member. Finally, the locking screw is screwed through the locking box and threadedly connected to the ventilation chamber for positioning, further reducing the risk of the UAV being tracked and shot down and improving the reconnaissance and strike ability of the UAV.

[0028] In summary, the present application includes at least one of the following beneficial technical effects: 1. After the projectile falls, the control assembly controls the recoil airbag to communicate with the outside world. The gas is quickly ejected under the action of the self-elastic force and air pressure of the recoil airbag, thereby generating a forward reverse thrust on the airframe. The reverse thrust and the self-driving force of the airframe are superimposed on each other, greatly accelerating the moving speed of the airframe, thereby greatly reducing the risk of the UAV being tracked and shot down, improving the reconnaissance and strike ability of the UAV, and enabling the UAV to better meet the reconnaissance and strike requirements in different environments such as all-terrain single soldiers.

[0029] 2. When the gas is ejected, a thrust is generated on the puncturing assembly, so that a large amount of pigment powder is quickly ejected to form a smoke around the airframe for interference, enabling the UAV to be stealthy. Therefore, under the dual action of the smoke and the reverse thrust, the risk of the UAV being tracked and shot down is greatly reduced, and the reconnaissance and strike ability of the UAV is improved.

[0030] 3. By arranging the annular airbag near the gas ejection port of the jet pipe, a large amount of pigment can be ejected under the push of the gas when the gas starts to be ejected, quickly forming a large-area smoke, improving the smoke interference effect, further reducing the risk of the UAV being tracked and shot down, and improving the reconnaissance and strike ability of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 is a schematic diagram of the three-dimensional structure of the unmanned aerial vehicle; Figure 2 is a schematic diagram of the partial structure of the unmanned aerial vehicle; Figure 3 is Figure 2 the sectional view of A-A in Figure 4 is Figure 3 the enlarged view of part B in

[0032] Reference numerals: 1, airframe; 11, projectile body; 2, recoil mechanism; 21, recoil airbag; 22, control component; 23, jet pipe; 24, control valve; 25, connecting section; 26, jet section; 27, installation groove; 3, interference mechanism; 31, annular airbag; 32, puncturing component; 33, puncturing ring; 34, spring; 35, puncturing needle; 36, ventilation cavity; 4, inflation component; 41, intake pipe; 43, intake valve; 5, positioning mechanism; 51, placement box; 52, clamping groove; 53, fixing groove; 54, placement chamber; 55, sealing groove; 56, partition board; 57, main chamber; 58, auxiliary chamber; 6, locking component; 61, locking box; 62, locking screw; 7, pushing component; 71, first elastic member; 72, second elastic member. Detailed implementation manners

[0033] The following further elaborates on this application in detail.

[0034] The embodiments of this application disclose a small all-terrain single-soldier reconnaissance and strike integrated unmanned aerial vehicle.

[0035] Referring to Figure 1 , the small all-terrain single-soldier reconnaissance and strike integrated unmanned aerial vehicle includes an airframe 1, a projectile body 11, and a recoil mechanism 2. A camera for reconnaissance is provided on the airframe 1. The projectile body 11 is installed on the airframe 1, and a control device for controlling the detachment of the projectile body 11 is provided on the airframe 1. The camera and the control device are both prior arts and will not be elaborated here. The recoil mechanism 2 is used to eject gas after the projectile body 11 detaches. The ejected gas generates a thrust on the airframe 1, and the thrust pushes the airframe 1 forward and the moving direction is the same as the flight direction of the airframe 1 itself, so that the airframe 1 accelerates in flight under the dual action of its own driving force and the thrust, reducing the risk of the unmanned aerial vehicle being tracked and shot down; Multiple recoil mechanisms 2 can be provided to adapt to the separate bomb dropping operations of multiple projectile bodies 11, and when single or multiple projectile bodies 11 drop bombs simultaneously, multiple recoil mechanisms 2 can be started simultaneously to improve the acceleration effect.

[0036] Referring to Figures 1 - 3, the recoil mechanism 2 includes a recoil airbag 21 and a control assembly 22. The recoil airbag 21 is arranged on the airframe 1 through a positioning mechanism 5. The recoil airbag 21 is filled with inert gas at a certain pressure, and before the UAV takes off, the recoil airbag 21 is already filled with inert gas at a certain pressure; the control assembly 22 is arranged on the recoil airbag 21 and controls the connection or disconnection of the recoil airbag 21 with the outside; when the projectile 11 is separated from the airframe 1, the control assembly 22 controls the recoil airbag 21 to communicate with the outside, so that the gas in the recoil airbag 21 is ejected, and the airframe 1 generates a thrust to push the airframe 1 forward, so that the airframe 1 accelerates forward under the dual action of its own driving force and the thrust.

[0037] The control assembly 22 includes an air jet pipe 23 and a control valve 24. The air jet pipe 23 is fixedly installed on the recoil airbag 21 and is in communication with the inside of the recoil airbag 21; the control valve 24 is detachably installed on the air jet pipe 23. The air jet pipe 23 includes a connection section 25 detachably connected to the control valve 24 by screws and a jet section 26. The connection section 25 is connected to the recoil airbag 21; the control valve 24 is used to control the opening or closing of the air jet pipe 23, that is, the control valve 24 controls the communication or disconnection of the jet section 26 and the connection section 25; after the projectile 11 is separated from the airframe 1, the control valve 24 controls the jet section 26 to communicate with the connection section 25, so that the gas in the recoil airbag 21 is ejected, enabling the airframe 1 to accelerate and fly away, and then the control valve 24 controls the jet section 26 to be disconnected from the connection section 25.

[0038] The recoil mechanism 2 further includes an inflation assembly 4. The inflation assembly 4 includes an intake pipe 41 and a pressure detector. The intake pipe 41 is fixedly installed on the recoil airbag 21, and the intake pipe 41 and the connection section 25 are respectively located at both ends of the recoil airbag 21. An intake valve 43 is fixedly installed on the intake pipe 41; the pressure detector is fixedly installed on the intake pipe 41 and is used to detect the air pressure in the intake pipe 41 and the recoil airbag 21.

[0039] Before the UAV takes off, connect the intake pipe 41 to an external inflation structure, open the intake valve 43, and the inflation structure fills the recoil airbag 21 with inert gas through the intake pipe 41. The pressure detector is used to detect the air pressure. When the air pressure reaches the required value, the intake valve 43 is closed, and the inflation structure is disassembled from the intake pipe 41, thereby realizing filling the recoil airbag 21 with inert gas at a certain pressure.

[0040] Refer to Figures 1 - 2 , the positioning mechanism 5 includes a placement box 51 and a locking assembly 6. The placement box 51 is fixedly installed on the airframe 1 by screws and the upper surface is in an open state. The length direction of the placement box 51 is the same as the moving direction of the airframe 1.

[0041] Refer to Figures 2 - 3, semi-circular clamping grooves 52 and fixing grooves 53 are formed at both ends of the placement box 51. The recoil airbag 21 is placed in the placement box 51. The jet section 26 is clamped and installed on the clamping groove 52, and the air inlet pipe 41 is clamped and installed on the fixing groove 53. The locking assembly 6 is arranged on the body 1 and presses against the jet pipe 23 for positioning. A placement chamber 54 for placing and inflating the recoil airbag 21 and in a closed state is formed between the locking assembly 6 and the placement box 51.

[0042] The locking assembly 6 includes a locking box 61 and a locking screw 62. The locking box 61 is rotatably installed on the upper surface of the placement box 51, and the locking box 61 abuts against the placement box 51 for positioning. The placement chamber 54 is formed by the cooperation of the locking box 61 and the placement box 51. Partition plates 56 are integrally arranged on the side walls of the opposite sides of the locking box 61 and the placement box 51. The two partition plates 56 abut against each other and divide the placement chamber 54 into independent main chamber 57 and sub-chamber 58. The recoil airbag 21 is located in the main chamber 57, and semi-circular sealing grooves 55 are formed on the side walls of the opposite sides of the two partition plates 56. The two sealing grooves 55 clamp and position the connecting section 25, so that the recoil airbag 21 is located in the main chamber 57 and the control valve 24 is located in the sub-chamber 58 for protection. When the locking box 61 rotates away from the placement box 51, the main chamber 57 and the sub-chamber 58 can be opened simultaneously.

[0043] Semi-circular clamping grooves 52 and fixing grooves 53 are also formed on the locking box 61. The two clamping grooves 52 cooperate to clamp and position the jet section 26, and the two fixing grooves 53 cooperate to clamp and position the air inlet pipe 41, so as to position the connecting section 25, the jet section 26, the recoil airbag 21 and the air inlet pipe 41 in this way. The locking screw 62 passes through the locking box 61 and is threadedly connected to the placement box 51 for positioning.

[0044] A pushing assembly 7 for assisting in pushing the recoil airbag 21 is arranged on the placement box 51 and the locking box 61. The pushing assembly 7 includes an elastic member 71 and an elastic member 72. The elastic member 71 and the elastic member 72 are plate-like structures with elasticity. The elastic member 71 and the elastic member 72 are fixedly installed on the opposite side walls of the placement box 51 and the locking box 61 and are located in the main chamber 57. The elastic member 71 and the elastic member 72 respectively press against both sides of the recoil airbag 21 under the action of elastic force for positioning.

[0045] When the recoil airbag 21 is not filled with gas, the elastic member 71 and the elastic member 72 are in a horizontal state and parallel to each other. After the recoil airbag 21 is inflated, it pushes the elastic member 71 and the elastic member 72 to deform. At the same time, after the recoil airbag 21 is inflated, it expands and presses against the inside of the main chamber 57. The main chamber 57 can limit and protect the recoil airbag 21. When the gas is ejected from the recoil airbag 21, the elastic member 71 and the elastic member 72 can push the recoil airbag 21, thereby increasing the force of the gas ejection and prolonging the ejection time.

[0046] Refer to Figures 3 - 4 Figures 3 - 4 , on the inner side wall of one end of the jet section 26 close to the control valve 24, an installation groove 27 is coaxially opened. A disturbing mechanism 3 is arranged on each jet pipe 23. The disturbing mechanism 3 includes an annular airbag 31 and a puncturing component 32. The annular airbag 31 is annular and is clamped and installed in the installation groove 27, and the annular airbag 31 is coaxially arranged with the installation groove 27. The inner diameter of the annular airbag 31 is smaller than the inner diameter of the jet section 26, and a pigment for forming smoke is filled inside. The pigment can be dark pigment powder. The color of the dark pigment powder is designed according to needs, and the pigment powder is selected as a non-combustible material. Pigment powders such as iron oxide red and magnetite can be selected.

[0047] Figures 3 - 4 The puncturing component 32 is arranged on the jet section 26 and is located on the side of the control valve 24 away from the recoil airbag 21. After the control valve 24 is opened, inert gas is ejected, so as to drive the puncturing component 32 to move and puncture the annular airbag 31, so that the pigment powder in the annular airbag 31 is ejected under the pushing action of the inert gas, forming smoke around the body 1 for interference, so that the UAV is hidden, greatly reducing the risk of the UAV being tracked and shot down.

[0048] Figures 3 - 4 The puncturing component 32 includes a puncturing ring 33 and a spring 34. The puncturing ring 33 is slidably installed in the installation groove 27 along the direction close to or away from the annular airbag 31. The puncturing ring 33 is located on the side of the annular airbag 31 close to the control valve 24, and a plurality of puncturing needles 35 for puncturing the annular airbag 31 are arranged on the side wall of the puncturing ring 33 close to the annular airbag 31; the puncturing ring 33 is coaxially arranged with the installation groove 27, and a ventilation cavity 36 with a frustum-shaped cross section is formed on the inner side wall. The diameter of one end of the ventilation cavity 36 close to the recoil airbag 21 is larger than the diameter of one end close to the annular airbag 31. The diameter of one end of the ventilation cavity 36 close to the recoil airbag 21 is larger than the inner diameter of the jet section 26 and smaller than the diameter of the installation groove 27. The diameter of one end of the ventilation cavity 36 close to the recoil airbag 21 is smaller than the inner diameter of the jet section 26 and is convenient for the gas to push the puncturing ring 33 to move.

[0049] One end of the spring 34 is fixedly connected to the outer side wall of the control valve 24, and the other end is fixedly connected to the puncturing ring 33. The spring 34 is used to keep the puncturing ring 33 and the puncturing needle 35 disengaged from the annular airbag 31. After the control valve 24 is opened, the gas in the recoil airbag 21 enters the jet section 26 through the connecting section 25. The gas pushes the puncturing ring 33 to move through the ventilation cavity 36, and the gas is ejected after passing through the inner side of the annular airbag 31. The movement of the puncturing ring 33 drives the puncturing needle 35 to puncture the annular airbag 31, and the gas pushes the pigment to be ejected simultaneously, so that the gas and the pigment are ejected simultaneously. By this way, the driving mechanism 1 is accelerated to fly away, and at the same time, smoke is generated for interference, so that the unmanned aerial vehicle is hidden, and the risk of the unmanned aerial vehicle being tracked and shot down is reduced. At the same time, the annular airbag 31 can be replaced by removing the jet section 26 and the control valve 24, so that the unmanned aerial vehicle can be reused, and the cost of the unmanned aerial vehicle is reduced.

[0050] The working principle of the embodiment of the present application is as follows: The airframe 1 drives the projectile 11, the recoil mechanism 2, and the interference mechanism 3 to move together. After the airframe 1 detects a target, it decelerates and starts to drop the bomb. After the projectile 11 is separated from the airframe 1, the control valve 24 controls the connecting section 25 and the jet section 26 to communicate. The gas in the recoil airbag 21 is ejected through the jet section 26 under the action of its own air pressure, the elastic member 71, and the elastic member 72, generating a thrust on the airframe 1. When the gas is ejected, it pushes the puncturing ring 33 to move and puncture the annular airbag 31. Therefore, the ejected gas can push the pigment and the gas to be ejected simultaneously, forming smoke at the airframe 1 for interference. Therefore, the airframe 1 is accelerated to fly away under the dual action of its own driving force and the thrust, and at the same time, the smoke makes the airframe 1 invisible and difficult to track. Therefore, the risk of the unmanned aerial vehicle being tracked and shot down is greatly reduced, and the reconnaissance and strike ability of the unmanned aerial vehicle is improved.

[0051] The above are all the preferred embodiments of the present application. The protection scope of the present application is not limited thereby. Therefore, all equivalent changes made according to the structure, shape, and principle of the present application should be covered within the protection scope of the present application.

Claims

1. Small all-terrain single-soldier reconnaissance and strike integrated UAV, characterized in that: It includes a body (1), a projectile body (11), and a recoil mechanism (2). The recoil mechanism (2) includes: A recoil airbag (21) which is arranged on the body (1) and filled with gas at a certain pressure; A control component (22) which is arranged on the recoil airbag (21) and controls the connection or closing of the recoil airbag (21) with the outside. After the projectile body (11) is separated from the body (1), the control component (22) controls the recoil airbag (21) to communicate with the outside and makes the gas in the recoil airbag (21) spray out, so that the body (1) accelerates forward under the combined action of the reverse thrust of the gas spray and its own driving force.

2. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 1, wherein: The control component (22) includes: A jet pipe (23) which is arranged on the recoil airbag (21) and communicates with the inside of the recoil airbag (21); A control valve (24) which is arranged on the jet pipe (23) and is used to control the opening or closing of the jet pipe (23). After the projectile body (11) is separated from the body (1), the control valve (24) controls the jet pipe (23) to open.

3. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 2, characterized in that: An interference mechanism (3) is arranged on the jet pipe (23). The interference mechanism (3) includes: An annular airbag (31) which is arranged on the jet pipe (23) and contains pigment powder for forming smoke inside; A puncturing component (32) which is arranged on the jet pipe (23) and is located on the side of the control valve (24) away from the recoil airbag (21). After the control valve (24) opens and inert gas sprays out, it drives the puncturing component (32) to move and puncture the annular airbag (31), so that the pigment powder mixed gas in the annular airbag (31) sprays out and forms smoke for interference around the body (1).

4. The small all-terrain single-soldier reconnaissance and strike integrated unmanned aerial vehicle according to claim 3, wherein: The puncturing component (32) includes: A puncturing ring (33) which is slidably arranged on the jet pipe (23) along the direction of approaching or departing from the annular airbag (31); A spring (34) which is arranged on the outer side wall of the control valve (24) and is connected with the puncturing ring (33) and is used to maintain the separation of the puncturing ring (33) from the annular airbag (31). After the control valve (24) opens, the gas pushes the puncturing ring (33) to puncture the annular airbag (31). After the control valve (24) closes, the puncturing ring (33) moves back to its original position under the action of the spring (34).

5. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 4, wherein: The jet pipe (23) includes a connecting section (25) detachably connected to the control valve (24) and a jetting section (26). The connecting section (25) is connected to the recoil airbag (21). An installation groove (27) is coaxially opened on the inner side wall of one end of the jetting section (26) close to the control valve (24). The annular airbag (31) is snap-fitted and installed in the installation groove (27), and the puncturing ring (33) is slidably installed in the installation groove (27).

6. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 4, wherein: A ventilation cavity (36) with a frustum-shaped cross-section is opened on the inner side wall of the puncturing ring (33). The diameter of one end of the ventilation cavity (36) close to the recoil airbag (21) is larger than the diameter of one end close to the annular airbag (31), which is convenient for the gas to push the puncturing ring (33) to move, so that the gas in the jet pipe (23) passes through the inner sides of both the ventilation cavity (36) and the annular airbag (31) in sequence.

7. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 1, wherein: The gas located within the recoil airbag (21) is an inert gas. The recoil mechanism (2) further includes an inflation assembly (4), and the inflation assembly (4) includes: An intake pipe (41) that communicates with the recoil airbag (21) and is used for inputting inert gas and is provided with an intake valve (43); A pressure detector (42) that is arranged on the intake pipe (41) and is used for detecting gas pressure.

8. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 2, characterized in that: A pushing assembly (7) for assisting in pushing the recoil airbag (21) is arranged on the body (1), and the pushing assembly (7) includes: A first elastic member (71) and a second elastic member (72) that are arranged on the body (1) and are located on both sides of the recoil airbag (21) and press against both side surfaces of the recoil airbag (21) under the action of elastic force. In the initial state, the first elastic member (71) and the second elastic member (72) are in a parallel state. After the recoil airbag (21) is inflated, it pushes the first elastic member (71) and the second elastic member (72) to deform.

9. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 8, wherein: A positioning mechanism (5) for positioning the recoil airbag (21) is provided on the body (1), and the positioning mechanism (5) includes: A placement box (51) that is arranged on the body (1) and is in an open state and is provided with a clamping groove (52) that is in clamping fit with the jet pipe (23); A locking assembly (6) that is arranged on the body (1) and presses against the jet pipe (23) for positioning. A placement chamber (54) in a closed state is formed between the locking assembly (6) and the placement box (51). The placement chamber (54) is for placing and inflating the recoil airbag (21) and for placing the control valve (24). The first elastic member (71) and the second elastic member (72) are respectively arranged on the placement box (51) and the locking assembly (6).

10. The all-terrain single-soldier reconnaissance and strike integrated small unmanned aerial vehicle according to claim 9, characterized in that: The locking assembly (6) includes: A locking box (61) that is rotatably arranged on the placement box (51) and presses against the jet pipe (23) for positioning. The placement chamber (54) is formed by the cooperation of the locking box (61) and the placement box (51); A locking screw (62) that passes through the locking box (61) and is threadedly connected to the placement box (51).

Images