Self-rescue device for vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a self-rescue device for a vertical take-off and landing fixed-wing unmanned aerial vehicle. Comprising a fuselage, wings are arranged on the two sides of the fuselage, the wings are symmetrically arranged on the two sides of the fuselage, and fixed wings are arranged on the fuselage and the wings; a pair of supporting frames is arranged on each of the two sides of the machine body, and the supporting frames on the two sides of the machine body are symmetrically arranged. A monitoring module matched with the fixed wings is arranged in the fuselage; a protective frame is arranged below the machine body; air nozzles are arranged below the fuselage and the wings, a through hole is formed in the fuselage, a parachute is arranged in the through hole, a first upper protection plate is arranged above the parachute, a plurality of first lower protection plates are arranged below the parachute, and the first lower protection plates and the first upper protection plate are located in the through hole; the problem that the unmanned aerial vehicle lacks various protections after being out of control in the prior art is effectively solved, and the safety of the unmanned aerial vehicle after being out of control is greatly improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a self-rescue device for a vertical take-off and landing fixed-wing unmanned aerial vehicle. Background Art

[0002] With the rapid development of technology, unmanned aerial vehicles have been widely used in many fields, such as military, scientific research, civilian, etc., and play an important role in aspects such as electric power, communication, meteorology, agriculture, ocean, exploration, photography, disaster prevention and mitigation, crop yield estimation, patrol and public security. It has the advantages of being flexible, responsive, unmanned flight, low operation requirements, etc., and can realize functions such as real-time image transmission and detection of high-risk areas by carrying various sensors, becoming a powerful supplement to satellite remote sensing and traditional aerial remote sensing.

[0003] However, despite the significant progress of unmanned aerial vehicle technology, in the actual use process, the situation of unmanned aerial vehicle out of control still occurs from time to time. Once out of control, in the lightest case, it will cause damage to the unmanned aerial vehicle itself, and in the most serious case, it may cause serious damage to the surrounding personnel and property. Especially for larger fixed-wing unmanned aerial vehicles, the potential risks are more prominent. At present, there are relatively few effective protection measures for unmanned aerial vehicles out of control in the existing technology, and there is an urgent need for a device that can ensure the safety of unmanned aerial vehicles at critical moments. Summary of the Invention

[0004] To solve the above problems, the present invention proposes a self-rescue device for a vertical take-off and landing fixed-wing unmanned aerial vehicle, which effectively solves various protection problems of unmanned aerial vehicles lacking after out of control in the existing technology, and greatly improves the safety of unmanned aerial vehicles after out of control.

[0005] To achieve the above object, the present invention proposes the following technical solution: A self-rescue device for a vertical take-off and landing fixed-wing unmanned aerial vehicle, including a fuselage, wings are arranged on both sides of the fuselage, the wings are symmetrically arranged on both sides of the fuselage, and fixed wings are arranged on both the fuselage and the wings; a pair of support frames are respectively arranged on both sides of the fuselage, and the support frames on both sides of the fuselage are symmetrically arranged; a monitoring module cooperating with the fixed wings is arranged inside the fuselage; a protection frame is arranged below the fuselage, and a first protection mechanism cooperating with the protection frame is arranged on the fuselage; jet nozzles are arranged below both the fuselage and the wings, a perforation is arranged on the fuselage, a parachute is arranged inside the perforation, a first upper protection plate is arranged above the parachute, a plurality of first lower protection plates are arranged below the parachute, both the first lower protection plate and the first upper protection plate are located inside the perforation, and a first control mechanism cooperating with the first lower protection plate and the first upper protection plate is arranged inside the fuselage.

[0006] Furthermore: The first protection mechanism includes a pair of first adjustment mechanisms. Each first adjustment mechanism includes a connection control block fixedly connected to the side of the fuselage. Inside the connection control block, a first protection worm and a first protection worm gear are rotatably connected. The first protection worm and the first protection worm gear mesh with each other. The first protection worm gear is coaxially fixedly connected with a first active connecting rod. The other end of the first active connecting rod is coaxially rotatably connected with a first auxiliary connecting rod and a first connecting rod. Inside the connection control block, a first driven connecting rod is rotatably connected. The other end of the first driven connecting rod is rotatably connected with a second connecting rod and a second auxiliary connecting rod. The other end of the first auxiliary connecting rod is rotatably connected to the center of the first driven connecting rod. The other end of the second auxiliary connecting rod is rotatably connected to the center of the first connecting rod. The other ends of the first connecting rod and the second connecting rod are both rotatably connected to the protection frame.

[0007] Furthermore: The first control mechanism includes a first control worm rotatably connected inside the fuselage. Inside the fuselage, a second control worm gear meshing with the first control worm is rotatably connected. On both sides of the second control worm gear, a first transmission large gear and a first transmission small gear are coaxially fixedly connected respectively. Inside the fuselage, a first sliding rack meshing with the first transmission large gear is slidably connected. A first upper protection plate matching with the perforation is fixedly connected to the first sliding rack. Inside the fuselage, a second transmission large gear meshing with the first transmission small gear is rotatably connected. The second transmission large gear is coaxially fixedly connected with a first rotating groove ring. A first fixed groove ring is fixedly connected inside the fuselage. A plurality of first lower protection plates are arranged between the first rotating groove ring and the first fixed groove ring. Sliding grooves matching with the first lower protection plates are arranged on both the first rotating groove ring and the first fixed groove ring.

[0008] Furthermore: A sliding groove matching with the first upper protection plate is arranged inside the fuselage.

[0009] Furthermore: Motors are coaxially fixedly connected to both the first protection worm and the first control worm. The monitoring module can control the motors.

[0010] Furthermore: An air pump matching with the jet nozzle is arranged inside the fuselage. The monitoring module can control the air pump.

[0011] Furthermore: When the fixed wing is operating normally, the monitoring module can restrict the operation of the motors and the air pump. When the fixed wing is out of control, the monitoring module can control the operation of the motors and the air pump.

[0012] Furthermore: The length of the protection frame is greater than the length of the fuselage.

[0013] Furthermore: The front end of the protection frame is arc-shaped.

[0014] Compared with the prior art, the gain effect of the present invention is: 1. When the monitoring module detects that the fixed-wing aircraft is out of control, it will immediately start the motor and the air pump. The movement of the motor can drive the components of the first protection mechanism to move, thereby adjusting the position of the protective frame. The length of the protective frame is greater than the length of the fuselage. At the same time, the front end of the protective frame is arc-shaped, which can play a buffering and protective role when the unmanned aircraft touches the ground, avoiding the risk of the fuselage "hard landing".

[0015] 2. The movement of the motor will also drive the first control mechanism. The movement of the first control mechanism can open the perforation, and then the parachute will open, thereby effectively reducing the landing speed of the unmanned aircraft and avoiding its out-of-control speed from being too large. The air pump will jet air through the jet nozzle, thereby realizing the overall stability of the fuselage and the wings, ensuring its levelness, and thus realizing the cooperation with the first protection mechanism to provide guarantee for its horizontal landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a perspective view of the present invention.

[0017] Figure 2 is a structural diagram of the lower part of the present invention.

[0018] Figure 3 is a perspective view of the first protection mechanism of the present invention.

[0019] Figure 4 is an enlarged view of the first protection mechanism of the present invention.

[0020] Figure 5 is a perspective view of the first control mechanism of the present invention.

[0021] Figure 6 is a partial structural diagram of the first control mechanism of the present invention.

[0022] Figure 7 is a partial perspective view of the first control mechanism of the present invention.

[0023] Figure 8 is a sectional view of the first control mechanism of the present invention.

[0024] In the figure: 1, fuselage; 2, wing; 3, support frame; 4, protective frame; 5, jet nozzle; 6, connection control block; 7, first protection worm; 8, first protection worm gear; 9, first active connecting rod; 10, first driven connecting rod; 11, first auxiliary connecting rod; 12, first connecting link; 13, second connecting link; 14, second auxiliary connecting rod; 15, first control worm; 16, second control worm gear; 17, first driving large gear; 18, first sliding rack; 19, parachute; 20, first driving small gear; 21, second driving large gear; 22, first rotating groove ring; 23, first fixed groove ring; 24, first lower protection plate; 25, first upper protection plate. DETAILED DESCRIPTION OF THE INVENTION

[0025] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0026] A self-rescue device for a vertical takeoff and landing fixed-wing unmanned aerial vehicle, comprising a fuselage 1. Wings 2 are arranged on both sides of the fuselage 1, and the wings 2 are symmetrically arranged on both sides of the fuselage 1. Fixed wings are arranged on both the fuselage 1 and the wings 2. A pair of support frames 3 are respectively arranged on both sides of the fuselage 1, and the support frames 3 on both sides of the fuselage 1 are symmetrically arranged. A monitoring module cooperating with the fixed wings is arranged inside the fuselage 1. A protective frame 4 is arranged below the fuselage 1, and a first protection mechanism cooperating with the protective frame 4 is arranged on the fuselage 1. Jet nozzles 5 are arranged below both the fuselage 1 and the wings 2. A perforation is arranged on the fuselage 1, and a parachute 19 is arranged inside the perforation. A first upper protection plate 25 is arranged above the parachute 19, and a plurality of first lower protection plates 24 are arranged below the parachute 19. The first lower protection plates 24 and the first upper protection plate 25 are both located inside the perforation. A first control mechanism cooperating with the first lower protection plates 24 and the first upper protection plate 25 is arranged inside the fuselage 1.

[0027] As shown in Figure 1 、 2 、3 and 8: When the fixed-wing unmanned aerial vehicle is operating normally, the monitoring module restricts the operation of the motor and the air pump. At this time, the self-rescue device is in a standby state and will not interfere with the normal flight of the unmanned aerial vehicle. When the monitoring module detects that the fixed wings are out of control, the motor and the air pump are immediately started. The motor will drive the first protection mechanism and the first control mechanism to move. The first protection mechanism can adjust the position of the protective frame 4. The length of the protective frame 4 is greater than the length of the fuselage 1. At the same time, the front end of the protective frame 4 is arc-shaped, which can play a buffering and protective role when the unmanned aerial vehicle contacts the ground, avoiding the risk of the fuselage 1 "hard landing"; at the same time, when the first control mechanism moves, the perforation will be opened, and the parachute 19 inside the perforation will be opened, so as to effectively reduce the landing speed of the unmanned aerial vehicle and avoid its out-of-control speed from being too large. At the same time, the movement of the air pump will jet air through the jet nozzles 5. The jetting of the jet nozzles 5 will not only effectively reduce the falling speed of the fuselage 1 and the wings 2, but also the monitoring module will adjust the levelness of the unmanned aerial vehicle through the jet nozzles 5 according to the levelness of the fuselage 1 and the wings 2 to ensure its levelness, so as to cooperate with the first protection mechanism and provide guarantee for its horizontal landing.

[0028] The first protection mechanism includes a pair of first adjustment mechanisms. Each first adjustment mechanism includes a connection control block 6 fixedly connected to the side of the fuselage 1. A first protection worm 7 and a first protection worm gear 8 are rotatably connected within the connection control block 6, and the first protection worm 7 meshes with the first protection worm gear 8. The first protection worm gear 8 is coaxially fixedly connected with a first active connecting rod 9. The other end of the first active connecting rod 9 is coaxially rotatably connected with a first auxiliary connecting rod 11 and a first connecting rod 12. A first driven connecting rod 10 is rotatably connected within the connection control block 6. The other end of the first driven connecting rod 10 is rotatably connected with a second connecting rod 13 and a second auxiliary connecting rod 14. The other end of the first auxiliary connecting rod 11 is rotatably connected to the center of the first driven connecting rod 10. The other end of the second auxiliary connecting rod 14 is rotatably connected to the center of the first connecting rod 12. The other ends of the first connecting rod 12 and the second connecting rod 13 are both rotatably connected to the protection frame 4.

[0029] As Figure 2 , 3 and shown in Figure 4: When the motor drives the first protection worm 7 to rotate, the rotation of the first protection worm 7 can drive the first active connecting rod 9 to rotate through the first protection worm gear 8. With the cooperation of the first auxiliary connecting rod 11 and the second auxiliary connecting rod 14, when the first active connecting rod 9 rotates, it can drive the first driven connecting rod 10, the first connecting rod 12 and the second connecting rod 13 to rotate, thereby realizing the adjustment of the position of the protection frame 4.

[0030] The first control mechanism includes a first control worm 15 rotatably connected within the fuselage 1. A second control worm gear 16 meshing with the first control worm 15 is rotatably connected within the fuselage 1. On both sides of the second control worm gear 16, a first transmission large gear 17 and a first transmission small gear 20 are coaxially fixedly connected respectively. A first sliding rack 18 meshing with the first transmission large gear 17 is slidably connected within the fuselage 1. A first upper protection plate 25 matching the perforation is fixedly connected to the first sliding rack 18. A second transmission large gear 21 meshing with the first transmission small gear 20 is rotatably connected within the fuselage 1. The second transmission large gear 21 is coaxially fixedly connected with a first rotating groove ring 22. A first fixed groove ring 23 is fixedly connected within the fuselage 1. A plurality of first lower protection plates 24 are arranged between the first rotating groove ring 22 and the first fixed groove ring 23. Sliding grooves matching the first lower protection plates 24 are arranged on both the first rotating groove ring 22 and the first fixed groove ring 23. A sliding groove matching the first upper protection plate 25 is arranged within the fuselage 1.

[0031] As Figure 1 , 5As shown in Figures 6, 7, and 8: When the motor drives the first control worm 15 to rotate, the rotation of the first control worm 15 can drive the first transmission large gear 17 and the first transmission small gear 20 to rotate through the second control worm wheel 16. The rotation of the first transmission large gear 17 can drive the first upper protective plate 25 to slide through the first sliding rack 18. At the same time, the rotation of the first transmission small gear 20 can drive the first rotating groove ring 22 to rotate through the second transmission large gear 21. Under the action of the first fixed groove ring 23, the rotation of the first rotating groove ring 22 can drive the first lower protective plate 24 to move, thereby realizing the opening of the perforation. After the perforation is opened, under the action of the downward wind, the parachute 19 will open, thereby reducing the falling speed of the drone.

[0032] Both the first protective worm 7 and the first control worm 15 are coaxially fixedly connected with motors, and the monitoring module can control the motors; an air pump matched with the jet nozzle 5 is arranged in the fuselage 1, and the monitoring module can control the air pump; when the fixed-wing operates normally, the monitoring module can limit the operation of the motors and the air pump, and when the fixed-wing is out of control, the monitoring module can control the operation of the motors and the air pump; the length of the protective frame 4 is greater than the length of the fuselage 1; the front end of the protective frame 4 is arc-shaped.

[0033] As Figure 1 and 2 shown: The setting of the monitoring module can realize the monitoring of whether the fixed-wing drone operates normally. When the fixed-wing operates normally, the monitoring module restricts the operation of the motors and the air pump. At this time, the self-rescue device is in a standby state and will not interfere with the normal flight of the drone. When the fixed-wing is out of control, it can rescue the drone. The length of the protective frame 4 is greater than the length of the fuselage 1. At the same time, the setting that the front end of the protective frame 4 is arc-shaped can play a buffering and protective role when the drone contacts the ground, avoiding the risk of the fuselage 1 "hard landing".

[0034] The working process of the present invention is as follows: As Figure 1 、 2As shown in Figures 4, 5, 6, 7, and 8: When the fixed-wing UAV is operating normally, the monitoring module restricts the operation of the motor and the air pump. At this time, the self-rescue device is in a standby state and will not interfere with the normal flight of the UAV. When the monitoring module detects that the fixed-wing is out of control, the motor and the air pump are immediately started. The motor drives the first protection mechanism and the first control mechanism to move. When the motor drives the first protection worm 7 to rotate, the rotation of the first protection worm 7 can drive the first active link 9 to rotate through the first protection worm gear 8. With the cooperation of the first auxiliary link 11 and the second auxiliary link 14, when the first active link 9 rotates, it can drive the first driven link 10, the first connecting link 12, and the second connecting link 13 to rotate, thereby realizing the adjustment of the position of the protective frame 4; When the motor drives the first control worm 15 to rotate, the rotation of the first control worm 15 can drive the first large transmission gear 17 and the first small transmission gear 20 to rotate through the second control worm gear 16. The rotation of the first large transmission gear 17 can drive the first upper protection plate 25 to slide through the first sliding rack 18. At the same time, the rotation of the first small transmission gear 20 can drive the first rotating groove ring 22 to rotate through the second large transmission gear 21. Under the action of the first fixed groove ring 23, the rotation of the first rotating groove ring 22 can drive the first lower protection plate 24 to move, thereby realizing the opening of the perforation. After the perforation is opened, under the action of the downward wind, the parachute 19 will open, thereby reducing the falling speed of the UAV; The setting of the monitoring module can monitor whether the fixed-wing UAV is operating normally. When the fixed-wing is operating normally, the monitoring module restricts the operation of the motor and the air pump. At this time, the self-rescue device is in a standby state and will not interfere with the normal flight of the UAV. When the fixed-wing is out of control, it can rescue the UAV. The length of the protective frame 4 is greater than the length of the fuselage 1. At the same time, the front end of the protective frame 4 is set to be arc-shaped, which can play a buffering and protective role when the UAV contacts the ground, avoiding the risk of the fuselage 1 "hard landing"; At the same time, the movement of the first control mechanism will open the perforation, and the parachute 19 in the perforation will open, thereby effectively reducing the landing speed of the UAV and avoiding its out-of-control speed from being too large. At the same time, the movement of the air pump will jet through the jet nozzle 5. The jet of the jet nozzle 5 will not only effectively reduce the falling speed of the fuselage 1 and the wing 2, but also the monitoring module will adjust the level of the UAV through the jet nozzle 5 according to the level of the fuselage 1 and the wing 2 to ensure its level, thereby realizing the cooperation with the first protection mechanism and providing guarantee for its horizontal landing; It effectively solves the problem that the UAV in the prior art lacks various protections after out-of-control, and greatly improves the safety of the UAV after out-of-control.

[0035] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0036] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements; for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

Claims

1. A self-rescue device for a vertical take-off and landing fixed-wing unmanned aerial vehicle, comprising a fuselage (1), wings (2) being arranged on both sides of the fuselage (1), the wings (2) being symmetrically arranged on both sides of the fuselage (1), and fixed wings being arranged on both the fuselage (1) and the wings (2); a pair of support frames (3) being arranged on both sides of the fuselage (1), and the support frames (3) on both sides of the fuselage (1) being symmetrically arranged; and characterized in that: A monitoring module cooperating with the fixed wing is arranged in the fuselage (1); a protection frame (4) is arranged below the fuselage (1); a first protection mechanism cooperating with the protection frame (4) is arranged on the fuselage (1); jet nozzles (5) are arranged below the fuselage (1) and the wing (2); a through hole is arranged on the fuselage (1), a parachute (19) is arranged in the through hole, a first upper protection plate (25) is arranged above the parachute (19), a plurality of first lower protection plates (24) are arranged below the parachute (19), the first lower protection plate (24) and the first upper protection plate (25) are both located in the through hole, and a first control mechanism cooperating with the first lower protection plate (24) and the first upper protection plate (25) is arranged in the fuselage (1).

2. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The first protection mechanism comprises a pair of first adjustment mechanisms, the first adjustment mechanism comprising a connection control block (6) fixedly connected to the side of the fuselage (1), a first protection worm (7) and a first protection worm wheel (8) being rotatably connected in the connection control block (6), the first protection worm (7) and the first protection worm wheel (8) being meshed with each other; a first active connecting rod (9) being coaxially fixedly connected to the first protection worm wheel (8), the other end of the first active connecting rod (9) being coaxially rotatably connected to a first auxiliary connecting rod (11) and a first connecting connecting rod (12) ), a first driven link (10) is rotatably connected inside the connection control block (6); the other end of the first driven link (10) is rotatably connected to a second connecting link (13) and a second auxiliary link (14); the other end of the first auxiliary link (11) is rotatably connected to the center of the first driven link (10); the other end of the second auxiliary link (14) is rotatably connected to the center of the first connecting link (12); the other ends of the first connecting link (12) and the second connecting link (13) are both rotatably connected to the protective frame (4).

3. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 2, characterized in that: The first control mechanism comprises a first control worm (15) rotatably connected in the body (1), a second control worm wheel (16) rotatably connected in the body (1) and meshing with the first control worm (15), a first transmission gear (17) and a first transmission pinion (20) being coaxially fixedly connected on both sides of the second control worm wheel (16), a first sliding rack (18) meshing with the first transmission gear (17) being slidably connected in the body (1), and a first upper protective member cooperating with the perforation being fixedly connected to the first sliding rack (18). A plate (25); a second transmission large gear (21) meshing with the first transmission small gear (20) is rotatably connected in the fuselage (1); a first rotating groove ring (22) is coaxially fixedly connected to the second transmission large gear (21); a first fixed groove ring (23) is fixedly connected in the fuselage (1); a plurality of first lower protection plates (24) are arranged between the first rotating groove ring (22) and the first fixed groove ring (23); and sliding grooves matching the first lower protection plates (24) are arranged on the first rotating groove ring (22) and the first fixed groove ring (23).

4. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 3 is characterized in that: A slide groove matching the first upper protective plate (25) is provided in the fuselage (1).

5. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 3, characterized in that: The first protection worm (7) and the first control worm (15) are both coaxially fixedly connected with a motor, and the monitoring module can control the motor.

6. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 5, characterized in that: An air pump that matches the air jet nozzle (5) is arranged inside the fuselage (1), and the monitoring module can control the air pump.

7. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 6, characterized in that: When the fixed wing is operating normally, the monitoring module can limit the operation of the motor and the air pump. When the fixed wing is out of control, the monitoring module can control the operation of the motor and the air pump.

8. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The length of the protective frame (4) is greater than the length of the fuselage (1).

9. The self-rescue device for a vertical take-off and landing fixed-wing UAV according to claim 1, characterized in that: The front end of the protective frame (4) is arc-shaped.

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