Central paddle layout type unmanned rescue aircraft

Abstract

A central paddle layout type unmanned rescue aircraft comprises an annular buoyancy lower shell, an annular upper cover plate, a rotor wing mechanism, a rudder mechanism, a battery and an electronic speed controller. The annular upper cover plate and the annular buoyancy lower shell are buckled together in a sealed mode to form an annular air chamber buoyancy body. The rotor mechanism is located in the middle of the inner side of the annular air chamber buoyancy body; an upper protective net cover is arranged above the rotor wing mechanism, and a lower protective net cover is arranged below the rotor wing mechanism; the rudder mechanism is positioned below the lower protective net cover; the battery and the electronic speed controller are packaged in the annular air chamber buoyancy body, and the electronic speed controller is electrically connected with the battery; a grabbing life-saving rope and an infrared recognition sensor are installed in the circumferential direction of the annular air chamber buoyancy body in a surrounding mode. The drowning device can take off from the near shore to reach a drowning position at the first time, the aircraft can land on the sea surface to form a buoyancy platform, the floating aircraft can automatically lock a drowning person and actively approach the drowning person, the drowning person can be prevented from sinking by grabbing the aircraft, and safety guarantee is provided for the drowning person to wait for subsequent rescue.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a central blade layout unmanned rescue aerial vehicle. Background Art

[0002] With the development of the global marine economy, maritime transportation and water entertainment activities are increasing day by day, and maritime accidents, especially drowning incidents, occur frequently, bringing huge challenges to maritime rescue.

[0003] In coastal and shallow water areas, when a drowning incident occurs, the rescue personnel on the shore can quickly reach the drowning location and provide rescue for the drowning person by throwing a life buoy or a life raft.

[0004] If the drowning location is in an area far from the shore, it is difficult to throw a traditional life buoy or life raft in place by conventional means. If there is a strong wind and wave environment, it will bring great difficulties to the rescue of the drowning person and easily miss the golden rescue time.

[0005] In recent years, the technology of unmanned aerial vehicles has developed rapidly. In particular, multi-rotor drones with vertical takeoff and landing capabilities can quickly cover a large area due to their flexibility and efficiency, and are not restricted by terrain and obstacles. They are especially suitable for performing tasks in complex marine environments, thus showing great potential in the fields of search, monitoring, emergency rescue, etc.

[0006] However, most of the common unmanned aerial vehicles on the market at present focus on aspects such as photography, monitoring, and cargo transportation, and the functional design for maritime rescue is generally weak, especially the rescue ability for drowning persons is generally poor. Content of the Utility Model

[0007] Aiming at the problems existing in the prior art, the utility model provides a central blade layout unmanned rescue aerial vehicle, which can take off from the shore and reach the drowning location in the first time. The aerial vehicle can land on the sea surface to form a buoyancy platform. The aerial vehicle floating on the sea surface can automatically lock the drowning person and actively approach the drowning person. The drowning person can avoid sinking by grasping the aerial vehicle, providing safety guarantee for the drowning person to wait for subsequent rescue.

[0008] To achieve the above object, the utility model adopts the following technical solution: A central blade layout unmanned rescue aircraft, comprising an annular buoyancy lower housing, an annular upper cover plate, a rotor mechanism, a rudder mechanism, a battery and an electronic speed controller; the annular upper cover plate and the annular buoyancy lower housing are hermetically buckled together to form an annular air chamber buoyancy body; the rotor mechanism is arranged in the middle inside the annular air chamber buoyancy body; an upper protective net cover is fixedly arranged on the inner side of the annular upper cover plate above the rotor mechanism, and a lower protective net cover is fixedly arranged on the inner side of the annular buoyancy lower housing below the rotor mechanism; the rudder mechanism is arranged in the middle inside the annular air chamber buoyancy body below the lower protective net cover; the battery and the electronic speed controller are both encapsulated inside the annular air chamber buoyancy body, and the electronic speed controller is electrically connected to the battery.

[0009] A grasping rescue rope is installed around the circumferential direction of the annular air chamber buoyancy body.

[0010] An infrared recognition sensor is installed around the circumferential direction of the annular air chamber buoyancy body.

[0011] The rotor mechanism includes a double-output shaft motor, an upper blade, a lower blade and a rotor mechanism support frame; the rotor mechanism support frame adopts a cross-shaped structure, and the rotor mechanism support frame is fixedly connected to the annular buoyancy lower housing; the double-output shaft motor is vertically fixedly installed at the center of the rotor mechanism support frame; the upper blade is installed on the upper motor shaft of the double-output shaft motor; the lower blade is installed on the lower motor shaft of the double-output shaft motor; a coaxial double-blade power assembly is formed by the double-output shaft motor, the upper blade and the lower blade; the double-output shaft motor is electrically connected to the electronic speed controller.

[0012] The number of the rudder mechanisms is four, which are respectively denoted as a first rudder mechanism, a second rudder mechanism, a third rudder mechanism and a fourth rudder mechanism; the first rudder mechanism, the second rudder mechanism, the third rudder mechanism and the fourth rudder mechanism are evenly and sequentially distributed along the circumferential direction, and the included angle between any two adjacent rudder mechanisms is 90°.

[0013] A transfer support seat is fixedly arranged at the center below the lower protective net cover; the first rudder mechanism, the second rudder mechanism, the third rudder mechanism and the fourth rudder mechanism are all connected between the transfer support seat and the annular buoyancy lower housing.

[0014] The rudder mechanism includes a rudder mechanism support frame, a servo, a rocker arm, a connecting rod, a rudder plate, a first transfer shaft and a second transfer shaft; the rudder mechanism support frame is fixedly connected to the annular buoyancy lower housing; the servo is fixedly installed on the rudder mechanism support frame; one end of the rocker arm is fixedly connected to the power output shaft of the servo, the other end of the rocker arm is fixedly connected to one end of the connecting rod, and the other end of the connecting rod is fixedly connected to the upper part of the outer plate edge of the rudder plate; one end of the first transfer shaft is rotatably connected to the annular buoyancy lower housing, and the other end of the first transfer shaft is fixedly connected to the middle part of the outer plate edge of the rudder plate; one end of the second transfer shaft is fixedly connected to the middle part of the inner edge of the rudder plate, and the other end of the second transfer shaft is rotatably connected to the transfer support seat; the power output shaft of the servo, the first transfer shaft and the second transfer shaft are coaxially distributed; the connecting rod is parallel to the power output shaft of the servo, the first transfer shaft and the second transfer shaft.

[0015] The beneficial effects of the present utility model:

[0016] The central blade layout type unmanned rescue aircraft of the present utility model can take off from the shore and reach the drowning position in the first time. The aircraft can land on the sea surface to form a buoyancy platform. The aircraft floating on the sea surface can automatically lock the drowning person and actively approach the drowning person. The drowning person can avoid sinking by grasping the aircraft, providing safety guarantee for the drowning person to wait for subsequent rescue. Description of the drawings

[0017] Figure 1 It is a structural schematic diagram (view angle one) of a central blade layout type unmanned rescue aircraft of the present utility model;

[0018] Figure 2 It is a structural schematic diagram (view angle two) of a central blade layout type unmanned rescue aircraft of the present utility model;

[0019] Figure 3 It is a structural schematic diagram (view angle three) of a central blade layout type unmanned rescue aircraft of the present utility model;

[0020] Figure 4 It is a combined body structural schematic diagram of the annular upper cover plate and the upper protection net cover of the present utility model;

[0021] Figure 5 It is a combined body structural schematic diagram of the annular buoyancy lower housing, the rotor mechanism, the rudder mechanism, the battery, the electronic speed controller, the grasping life-saving rope and the infrared recognition sensor of the present utility model;

[0022] Figure 6 It is a structural schematic diagram of the rudder mechanism of the present utility model;

[0023] In the figure, 1 is a ring-shaped buoyant lower housing, 2 is a ring-shaped upper cover plate, 3 is a battery, 4 is an electronic speed controller, 5 is an upper protective net cover, 6 is a lower protective net cover, 7 is a grasping life-saving rope, 8 is an infrared recognition sensor, 9 is a double-output shaft motor, 10 is an upper blade, 11 is a lower blade, 12 is a rotor mechanism support frame, 13 is a first rudder mechanism, 14 is a second rudder mechanism, 15 is a third rudder mechanism, 16 is a fourth rudder mechanism, 17 is an adapter support base, 18 is a rudder mechanism support frame, 19 is a servo motor, 20 is a rocker arm, 21 is a connecting rod, 22 is a rudder plate, 23 is a first transfer shaft, and 24 is a second transfer shaft. Detailed implementation mode

[0024] The following further elaborates on the present utility model in conjunction with the accompanying drawings and specific embodiments.

[0025] As Figures 1 to 6 shown, a central blade layout unmanned rescue aircraft includes a ring-shaped buoyant lower housing 1, a ring-shaped upper cover plate 2, a rotor mechanism, a rudder mechanism, a battery 3, and an electronic speed controller 4; the ring-shaped upper cover plate 2 and the ring-shaped buoyant lower housing 1 are hermetically buckled together to form a ring-shaped air chamber buoyancy body; the rotor mechanism is arranged in the middle inside the ring-shaped air chamber buoyancy body 1; an upper protective net cover 5 is fixedly arranged on the inner side of the ring-shaped upper cover plate 2 above the rotor mechanism, and a lower protective net cover 6 is fixedly arranged on the inner side of the ring-shaped buoyant lower housing 1 below the rotor mechanism; the rudder mechanism is arranged in the middle inside the ring-shaped air chamber buoyancy body 1 below the lower protective net cover 5; the battery 3 and the electronic speed controller 4 are both encapsulated inside the ring-shaped air chamber buoyancy body, and the electronic speed controller 4 is electrically connected to the battery 3.

[0026] In this embodiment, both the upper protective net cover 5 and the lower protective net cover 6 are made of high-strength metal or synthetic fiber materials, and an anti-corrosion paint is coated on the surfaces of the upper protective net cover 5 and the lower protective net cover 6 to improve their corrosion resistance while ensuring the strength of the protective net covers and extending their service life. The ring-shaped buoyant lower housing 1 and the ring-shaped upper cover plate 2 are made of lightweight corrosion-resistant materials with a certain strength, such as aluminum alloy or carbon fiber, and the outer surface is painted in light gray to create a strong visual contrast with the bright orange grasping life-saving rope 7, better helping drowning victims quickly identify the grasping life-saving rope 7; the battery 3 is a lithium battery with a high energy density, and the capacity standard of the battery 3 is configured according to the flight endurance of the aircraft not being less than 1 hour.

[0027] A grasping life-saving rope 7 is installed around the circumference of the ring-shaped air chamber buoyancy body.

[0028] In this embodiment, the grasping life-saving rope 7 is made of high-strength nylon rope and is colored bright orange to better help drowning victims quickly identify the grasping life-saving rope 7.

[0029] An infrared recognition sensor 8 is installed around the circumference of the ring-shaped air chamber buoyancy body.

[0030] In this embodiment, the number of infrared recognition sensors 8 is four, and the four infrared recognition sensors 8 are evenly distributed. The viewing angle recognition range of the infrared recognition sensors 8 is not less than 120°. This ensures that the four infrared recognition sensors 8 can achieve 360° full coverage visual recognition, ensuring that the drowning person can be locked by the infrared recognition sensors 8 at the first time.

[0031] The rotor mechanism includes a double-shaft motor 9, an upper blade 10, a lower blade 11 and a rotor mechanism support frame 12; the rotor mechanism support frame 12 adopts a cross-shaped structure, and the rotor mechanism support frame 12 is fixedly connected to the annular buoyancy lower shell 1; the double-shaft motor 9 is vertically fixed at the center of the rotor mechanism support frame 12; the upper blade 10 is installed on the upper end motor shaft of the double-shaft motor 9; the lower blade 11 is installed on the lower end motor shaft of the double-shaft motor 9; the double-shaft motor 9, the upper blade 10 and the lower blade 11 constitute a coaxial double-propeller power assembly; the double-shaft motor 9 is electrically connected to the electric regulator 4.

[0032] There are four rudder mechanisms, which are respectively denoted as a first rudder mechanism 13, a second rudder mechanism 14, a third rudder mechanism 15 and a fourth rudder mechanism 16; the first rudder mechanism 13, the second rudder mechanism 14, the third rudder mechanism 15 and the fourth rudder mechanism 16 are evenly distributed in sequence along the circumferential direction, and the angle between any two adjacent rudder mechanisms is 90°.

[0033] A transfer support seat 17 is fixedly arranged at the center below the lower protective net cover 6; the first rudder mechanism 13, the second rudder mechanism 14, the third rudder mechanism 15 and the fourth rudder mechanism 16 are all connected between the transfer support seat 17 and the annular buoyancy lower shell 1.

[0034] The rudder mechanism includes a rudder mechanism support frame 18, a steering gear 19, a rocker arm 20, a connecting rod 21, a rudder plate 22, a first transfer shaft 23 and a second transfer shaft 24; the rudder mechanism support frame 18 is fixedly connected to the annular buoyancy lower housing 1; the steering gear 19 is fixedly installed on the rudder mechanism support frame 18; one end of the rocker arm 20 is fixedly connected to the power output shaft of the steering gear 19, the other end of the rocker arm 20 is fixedly connected to one end of the connecting rod 21, and the other end of the connecting rod 21 is fixedly connected to the upper part of the outer plate edge of the rudder plate 22; one end of the first transfer shaft 23 is rotatably connected to the annular buoyancy lower housing 1, and the other end of the first transfer shaft 23 is fixedly connected to the middle of the outer plate edge of the rudder plate 22; one end of the second transfer shaft 24 is fixedly connected to the middle of the inner edge of the rudder plate 22, and the other end of the second transfer shaft 24 is rotatably connected to the transfer support seat 17; the power output shaft of the steering gear 19, the first transfer shaft 23 and the second transfer shaft 24 are coaxially distributed; the connecting rod 21 is parallel to the power output shaft of the steering gear 19, the first transfer shaft 23 and the second transfer shaft 24.

[0035] The working principle of the rudder mechanism is as follows: when the steering gear 19 is started, the power output shaft of the steering gear 19 will drive the rocker arm 20 to perform a swinging motion, and the connecting rod 21 will move synchronously with the rocker arm 20, thereby driving the rudder plate 22 to swing around the center lines of the first transfer shaft 23 and the second transfer shaft 24.

[0036] The following describes a usage process of the present invention with reference to the accompanying drawings:

[0037] When the drowning location is in an area far from the shore, in order to reach the drowning location in the first time for early rescue, first start the unmanned rescue aircraft of the present invention on the shore.

[0038] Start the double-output shaft motor 9 of the rotor mechanism, drive the upper propeller 10 and the lower propeller 11 to rotate coaxially and synchronously, and the generated lift will drive the unmanned rescue aircraft to take off vertically.

[0039] When the unmanned rescue aircraft reaches the set height of vertical takeoff, start the rudder mechanism. Take the arrangement direction of the first rudder mechanism 13 and the third rudder mechanism 15 as the front-rear direction, and take the arrangement direction of the second rudder mechanism 14 and the fourth rudder mechanism 16 as the left-right direction.

[0040] When the unmanned rescue aircraft needs to fly forward, the rudder plates 22 of the first rudder mechanism 13 and the third rudder mechanism 15 are kept in a vertically downward posture, and the lower edges of the rudder plates 22 of the second rudder mechanism 14 and the fourth rudder mechanism 16 are synchronously deflected backward. At this time, the aerodynamic force generated by the rotor mechanism will generate a backward thrust component under the guiding action of the rudder plates 22 of the second rudder mechanism 14 and the fourth rudder mechanism 16, thereby causing the unmanned rescue aircraft to generate a forward reaction force, and finally enabling the unmanned rescue aircraft to generate forward flight power. Similarly, when the unmanned rescue aircraft needs to fly forward, it only needs to synchronously deflect the lower edges of the rudder plates 22 of the second rudder mechanism 14 and the fourth rudder mechanism 16 forward.

[0041] When the unmanned rescue aircraft needs to fly left, the rudder plates 22 of the second rudder mechanism 14 and the fourth rudder mechanism 16 are kept in a vertically downward posture, and the lower edges of the rudder plates 22 of the first rudder mechanism 13 and the third rudder mechanism 15 are synchronously deflected right. At this time, the aerodynamic force generated by the rotor mechanism will generate a rightward thrust component under the guiding action of the rudder plates 22 of the first rudder mechanism 13 and the third rudder mechanism 15, thereby causing the unmanned rescue aircraft to generate a leftward reaction force, and finally enabling the unmanned rescue aircraft to generate leftward flight power. Similarly, when the unmanned rescue aircraft needs to fly right, it only needs to synchronously deflect the lower edges of the rudder plates 22 of the first rudder mechanism 13 and the third rudder mechanism 15 left.

[0042] When the unmanned rescue aircraft needs to turn in place, the rudder plates 22 of the first rudder mechanism 13, the second rudder mechanism 14, the third rudder mechanism 15 and the fourth rudder mechanism 16 are synchronously deflected clockwise or synchronously deflected counterclockwise, thereby enabling the unmanned rescue aircraft to generate clockwise or counterclockwise rotational flight power.

[0043] With the cooperation of the rotor mechanism and the rudder mechanism, the unmanned rescue aircraft can quickly fly to the air above the drowning position and then switch to hovering. After that, the unmanned rescue aircraft is lowered to the sea surface, and the unmanned rescue aircraft can float relying on buoyancy. Subsequently, the drowning person is locked by the infrared recognition sensor 8, and then, under the guidance of the infrared image, the cooperation of the rotor mechanism and the rudder mechanism continues until the unmanned rescue aircraft moves to the side of the drowning person. At this time, the drowning person can immediately grasp the grasping rescue rope 7 installed circumferentially around the unmanned rescue aircraft, providing a buoyancy platform for the drowning person temporarily, and enabling the drowning person to obtain temporary safety guarantee before the arrival of the rescue personnel, thereby ensuring the success rate of subsequent rescue.

[0044] The solutions in the embodiments are not intended to limit the protection scope of the present invention. Any equivalent implementation or modification without departing from the present invention is included in the protection scope of the present invention.

Claims

1. A central blade layout unmanned rescue aircraft, characterized in that: It includes an annular buoyant lower housing, an annular upper cover plate, a rotor mechanism, a rudder mechanism, a battery and an electronic speed controller; the annular upper cover plate and the annular buoyant lower housing are hermetically buckled together to form an annular air chamber buoyancy body; the rotor mechanism is arranged in the middle inside the annular air chamber buoyancy body; an upper protective mesh cover is fixedly arranged on the inner side of the annular upper cover plate above the rotor mechanism, and a lower protective mesh cover is fixedly arranged on the inner side of the annular buoyant lower housing below the rotor mechanism; the rudder mechanism is arranged in the middle inside the annular air chamber buoyancy body below the lower protective mesh cover; the battery and the electronic speed controller are both encapsulated inside the annular air chamber buoyancy body, and the electronic speed controller is electrically connected to the battery.

2. The central blade layout type unmanned rescue aircraft according to claim 1, characterized in that: A grasping life-saving rope is installed around the circumference of the annular air chamber buoyancy body.

3. The central blade layout unmanned rescue aircraft according to claim 1, wherein: An infrared recognition sensor is installed around the circumference of the annular air chamber buoyancy body.

4. The central blade layout type unmanned rescue aircraft according to claim 1, characterized in that: The rotor mechanism includes a double-output shaft motor, an upper propeller blade, a lower propeller blade and a rotor mechanism support frame; the rotor mechanism support frame adopts a cross-shaped structure, and the rotor mechanism support frame is fixedly connected to the annular buoyant lower housing; the double-output shaft motor is vertically fixedly installed at the center of the rotor mechanism support frame; the upper propeller blade is installed on the upper motor shaft of the double-output shaft motor; the lower propeller blade is installed on the lower motor shaft of the double-output shaft motor; the double-output shaft motor, the upper propeller blade and the lower propeller blade form a coaxial double-propeller power assembly; the double-output shaft motor is electrically connected to the electronic speed controller.

5. A central blade layout unmanned rescue aircraft according to claim 1, characterized in that: The number of the rudder mechanisms is four, which are respectively denoted as a first rudder mechanism, a second rudder mechanism, a third rudder mechanism and a fourth rudder mechanism; the first rudder mechanism, the second rudder mechanism, the third rudder mechanism and the fourth rudder mechanism are evenly and sequentially distributed along the circumferential direction, and the included angle between any two adjacent rudder mechanisms is 90°.

6. The central blade layout unmanned rescue aircraft according to claim 5, characterized in that: A transfer support seat is fixedly arranged at the center below the lower protective mesh cover; the first rudder mechanism, the second rudder mechanism, the third rudder mechanism and the fourth rudder mechanism are all connected between the transfer support seat and the annular buoyant lower housing.

7. The central blade layout type unmanned rescue aircraft according to claim 6, characterized in that: The rudder mechanism includes a rudder mechanism support frame, a servo motor, a rocker arm, a connecting rod, a rudder plate, a first transfer shaft and a second transfer shaft; the rudder mechanism support frame is fixedly connected to the annular buoyant lower housing; the servo motor is fixedly installed on the rudder mechanism support frame; one end of the rocker arm is fixedly connected to the power output shaft of the servo motor, the other end of the rocker arm is fixedly connected to one end of the connecting rod, and the other end of the connecting rod is fixedly connected to the upper part of the outer plate edge of the rudder plate; one end of the first transfer shaft is rotatably connected to the annular buoyant lower housing, and the other end of the first transfer shaft is fixedly connected to the middle part of the outer plate edge of the rudder plate; one end of the second transfer shaft is fixedly connected to the middle part of the inner edge of the rudder plate, and the other end of the second transfer shaft is rotatably connected to the transfer support seat; the power output shaft of the servo motor, the first transfer shaft and the second transfer shaft are coaxially distributed; the connecting rod is parallel to the power output shaft of the servo motor, the first transfer shaft and the second transfer shaft.

Images