Rescue throwing deceleration projectile body

Abstract

The utility model relates to a rescue throwing deceleration projectile body, which comprises a projectile body, a projectile head, a wing seat, a slow descent assembly and a propulsion power assembly, the projectile head, the projectile body and the wing seat are sequentially arranged from left to right, a material cavity is arranged in the projectile body, and a plurality of flying wing surfaces are arranged on the peripheral surface of the wing seat. The propelling power assembly is located in the wing seat and used for providing driving force for flight of the projectile body, the slow descending assembly comprises a plurality of buffering fan blades, extension plates are formed on the back faces of the buffering fan blades, the ends of the extension plates are hinged to the flight wing face, and the slow descending assembly is opened when the projectile body lands. And in the falling process of the projectile body, the multiple buffering fan blades can be opened, the wind resistance of the projectile body is increased, the falling speed of the projectile body is reduced, and the probability of material damage is greatly reduced.

Description

TECHNICAL FIELD

[0001] The utility model belongs to unmanned plane rescue equipment technical field, concretely relates to a rescue throw and drop deceleration bullet body. BACKGROUND

[0002] The existing rescue materials generally adopt the transportation type and the air drop type method to deliver, the above two ways are difficult to transport under some special conditions, such as the road damage caused by landslide after earthquake, the sea rescue action and the fire rescue action. The above three special conditions cannot directly adopt the transportation type and the air drop type method to deliver, need to consider various factors and cooperate with other ways to deliver;But with the development of power technology, material technology and control and navigation technology, the material transportation through the bullet launching mode becomes the main trend of the present rescue material transportation, but there is a problem in the bullet launching mode for material transportation: the flying speed is particularly fast during the bullet launching process, and the material is easily damaged when being thrown to the ground, and in view of this, the present scheme is generated. SUMMARY

[0003] In view of the deficiencies of the prior art, the technical problem to be solved by the utility model is to provide a rescue throw and drop deceleration bullet body, which can accurately project at a long distance and can buffer when descending, and can greatly reduce the damage of the materials.

[0004] To solve the above technical problems, the utility model adopts the technical scheme of a rescue throw and drop deceleration bullet body, which comprises a bullet body, a bullet head, a wing seat, a slow descent assembly and a propelling power assembly, the bullet head, the bullet body and the wing seat are arranged in sequence from left to right, the bullet body is provided with a material cavity, the outer peripheral surface of the wing seat is provided with a plurality of flight wing surfaces, the propelling power assembly is located in the wing seat and is used to provide driving force for the flight of the bullet body, the slow descent assembly comprises a plurality of buffer vanes, the back surface of the buffer vane is formed with an extension plate, the end of the extension plate is hinged to the flight wing surface, and the slow descent assembly is opened when the bullet body lands.

[0005] Further, the vertical section of the buffer vane is formed in an arc shape.

[0006] Further, the slow descent assembly comprises a driving assembly, and the driving assembly comprises a plurality of opening and closing motors, magnetic attraction pieces or electrically driven locks.

[0007] The driving assembly comprises a plurality of opening and closing motors, and the plurality of opening and closing motors are used to drive the plurality of buffer vanes to unfold.

[0008] The driving assembly comprises a magnetic attraction piece, the magnetic attraction piece comprises an electrified magnetic attraction plate, a leaf adhesion area is formed on the side surface of the wing seat, the buffer leaf is made of magnetic attraction metal material, the leaf adhesion area is provided with the electrified magnetic attraction plate, and the buffer leaf is adsorbed in the leaf adhesion area.

[0009] The driving assembly comprises an electrically-driven buckle, a plurality of annularly arranged clamps are formed on the side surface of the wing seat, the clamps are provided with the electrically-driven buckle, the surface of the buffer leaf towards the surface of the body is provided with a ring, the ring is inserted into the clamp, and the electrically-driven buckle realizes the buckling of the ring by electrification or de-electrification.

[0010] Further, the warhead is provided with a flight control rudder, and the flight control rudder is used for controlling the flight and positioning of the body.

[0011] Further, the upper surface of the body is provided with two hook ears which are arranged at intervals.

[0012] Further, a communication interface is arranged between the two hook ears, and the communication interface is connected with an adaptive interface on the unmanned aerial vehicle when the hook ears are hung on the unmanned aerial vehicle.

[0013] Further, the warhead is provided with a flight rudder surface on the surface of the body, and the flight rudder surface comprises a plurality of operation pieces which are arranged at intervals.

[0014] Further, the front end of the warhead is made of a buffer material.

[0015] Further, the buffer material is selected from rubber, foamed metal, porous foamed aluminum and polyethylene.

[0016] Further, the middle part of the body is provided with a containing groove penetrating through both sides, and the body further comprises a material storage bin which is clamped in the containing groove.

[0017] Compared with the prior art, the rescue throwing deceleration body has the following beneficial effects:

[0018] The rescue throwing deceleration body provided by the utility model is provided with a propelling power assembly on the wing seat, long-distance accurate throwing is realized, in the process of falling of the body, a plurality of buffer leaves are opened, the wind resistance of the body is increased, the falling speed of the body is slowed down, and the probability of damage of the materials is greatly reduced. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 It is a three-dimensional structure schematic view that the rescue throwing deceleration body is hung on an unmanned aerial vehicle.

[0020] Figure 2The utility model relates to a kind of rescue throwing deceleration projectile body, which is mounted on unmanned aerial vehicle in another direction of the three-dimensional structure schematic diagram.

[0021] Figure 3 The utility model relates to a kind of rescue throwing deceleration projectile body, which is mounted on unmanned aerial vehicle in another direction of the three-dimensional structure schematic diagram.

[0022] Figure 4 The utility model relates to a kind of rescue throwing deceleration projectile body, which is mounted on unmanned aerial vehicle in another direction of the three-dimensional structure schematic diagram.

[0023] Marked in the drawing: 1, material storage warehouse;2, projectile body;21, communication interface;22, lug;23, fan leaf attachment area;3, warhead;31, operating piece;4, wing seat;41, flight wing surface;5, slow descent component;51, buffer fan leaf;511, extension plate;6, propulsion power component;7, unmanned aerial vehicle. DETAILED DESCRIPTION

[0024] In order to make the above features and advantages of the utility model more obvious and easy to understand, the following specific examples are described in detail below, and the drawings are as follows.

[0025] As Figures 1-4 Indicated, the embodiment provides a kind of rescue throwing deceleration projectile, including material storage warehouse 1, projectile body 2, warhead 3, wing seat 4, slow descent component 5 and propulsion power component 6.

[0026] Warhead 3, projectile body 2 and wing seat 4 are sequentially arranged from left to right, flight control rudder is arranged in warhead 3, flight control rudder is used to control projectile flight and positioning direction, flight control rudder can be used in existing projectile body with common equipment. Flight rudder surface is provided on the circumferential surface of projectile body 2 close to warhead 3, and flight rudder surface includes four operating pieces 31, and multiple operating pieces 31 are annularly spaced, and four operating pieces 31 are controlled by deflection to control the steering of projectile, and the specific structure of operating piece 31 is the same as that of operating piece 31 in existing projectile body and the same as the connection mode. Warhead 3 front end is made of buffer material, and the buffer material is selected from rubber, foamed metal, porous foamed aluminum or polyethylene, and the warhead 3 front end in the present scheme is made of rubber, to reduce the impact force on landing.

[0027] Preferably, warhead 3 is integrated with visual component and GPS positioning component, and the visual component and GPS positioning component can be used in existing technology with common visual component and GPS positioning component.

[0028] The body 2 has a material cavity, specifically, the middle part of the body 2 is formed with a containing groove penetrating through both sides, the material storage bin 1 is clamped in the containing groove, according to the model and size of the body, the material storage bin 1 increases with the size of the body, and the storage weight of the material cavity in the material storage bin 1 is preferably in the range of 2-5kg. The material cavity can adapt to various rescue materials such as positioning equipment, fire extinguishing body, food, medicine, lifesaving equipment, etc. According to the emergency demand, the materials are replaced, placed in the material cavity, and can be normally used after being thrown.

[0029] Preferably, the material of the material storage bin 1 is selected to be a buffer material to reduce the impact when landing. The buffer material is selected from rubber, foamed metal, porous foamed aluminum or polyethylene, and in this scheme, rubber is selected as the material for manufacturing the material storage bin 1.

[0030] The upper surface of the body 2 is formed with a hook 22, the number of hooks 22 is two and they are arranged in front and back, and a communication interface 21 is further arranged between the two hooks 22, when the hook 22 is hung on the unmanned aerial vehicle 7, the communication interface 21 is connected with the adaptive interface on the unmanned aerial vehicle 7, as shown in the figure, the hook 22 is hooked by the unmanned aerial vehicle 7, and the communication interface 21 is connected with the adaptive interface on the unmanned aerial vehicle 7, when the body is separated, the marked target point on the unmanned aerial vehicle 7 is received, and the body is provided with accurate target according to the vision assembly and GPS positioning assembly of the body, and is automatically driven to the target point. Among them, the rescue body reaches a lower point and establishes communication with a high point unmanned aerial vehicle 7 and is transferred to a control center, which can solve the problem of bad communication environment.

[0031] The outer peripheral surface of the wing seat 4 is provided with four annularly spaced flight wing surfaces 41, the propulsion power assembly 6 is located in the wing seat 4 and is used to provide driving force for the flight of the body, the propulsion power assembly 6 adopts the existing technologies of compressed gas projection, electromagnetic drive or chemical propulsion, which will not be repeated here. The flight of the body is realized by the cooperation of the propulsion power assembly 6 and the flight wing surface 41. The propulsion power assembly 6 can realize autonomous flight less than or equal to 5km.

[0032] The slow descent assembly 5 includes four buffer vanes 51 and a driving assembly. The vertical section of the buffer vanes 51 is arc-shaped. The back of the buffer vanes 51 is provided with an extension plate 511. The end of the extension plate 511 is hinged to the flight wing surface 41. The slow descent assembly 5 is opened when the projectile lands. In this embodiment, the driving assembly is a magnetic attraction piece, which is an electrified magnetic attraction plate. The projectile body 2 is provided with a vane fitting area 23 on the side surface close to the wing seat 4. The buffer vanes 51 are made of magnetic metal material. The vane fitting area 23 is provided with an electrified magnetic attraction plate. The buffer vanes 51 are adsorbed to the vane fitting area 23. In the flight process, the electrified magnetic attraction plate is electrified to adsorb the buffer vanes 51 to the vane fitting area 23. When falling, the electrified magnetic attraction plate is de-energized. Under the action of wind resistance, the buffer vanes 51 are opened, the wind resistance received by the whole projectile is increased, and slow descent is realized.

[0033] Another embodiment of the driving assembly: the driving assembly includes four opening and closing motors for driving the plurality of buffer vanes 51 to expand.

[0034] Another embodiment of the driving assembly: the driving assembly includes an electrically driven buckle. The projectile body 2 is provided with a plurality of annularly arranged sockets on the side surface close to the wing seat 4. The electrically driven buckle is arranged in the socket. The surface of the electrically driven buckle buffer vane towards the surface of the projectile body 2 is provided with a ring. The ring of the electrically driven buckle extends into the socket. The electrically driven buckle realizes the buckling of the ring by energization or de-energization. The electrically driven buckle adopts the common electrically driven buckle in the prior art.

[0035] Preferably, in order to enhance the adaptability of the projectile in various weather conditions, the projectile body 2, the bullet 3 and the wing seat 4 are designed to be waterproof. The waterproof structure can adopt the existing structure, so that the performance of the projectile is not greatly affected when facing harsh weather conditions such as heavy rain and strong wind.

[0036] Positioning and projection method: the unmanned aerial vehicle 7 uses a satellite positioning system such as GPS and Beidou, combined with high-precision sensors, barometers and accelerometers, to accurately determine the position and height of the projectile, and then releases the projectile. The projectile independently flies to the target point (the horizontal distance between the projectile and the target should be less than or equal to 5km) under the drive of the propulsion assembly 6. According to the cooperation of the visual assembly, the GPS positioning assembly and the flight control servo in the bullet 3, precise projection is realized.

[0037] By using the above positioning method and projection method, the projectile can effectively play a role in complex terrains such as mountains, jungles and water areas. The unmanned aerial vehicle 7 transports the projectile to the approximate target point. The unmanned aerial vehicle 7 guarantees communication at high altitude. At the same time, the projectile intelligently tracks the target position according to the information target, and implements precise delivery of materials.

[0038] Communication method: when the unmanned aerial vehicle 7 is in a mountainous area, a complex urban radio environment, or a control center cannot reach an effective transmission location, the unmanned aerial vehicle 7 does not need to lower the flight height or enter a complex communication area to realize the dropping of the bomb body. The control center controls the unmanned aerial vehicle 7 to reach the command horizontal coordinate and then drops the bomb body. The bomb body is separated, receives the target point marked on the unmanned aerial vehicle 7, and provides accurate targets for the bomb body according to the bomb body visual component and the GPS positioning component. The bomb body automatically drives to the target point. When the bomb body reaches a lower point, communication is established with the high point unmanned aerial vehicle 7 and is transferred to the control center, which can solve the problem of a bad communication environment.

[0039] The above shows and describes the basic principles and main features of the present application and the advantages of the present application. Those skilled in the art should understand that the present application is not limited to the above embodiments. The above embodiments and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application. These changes and improvements fall within the scope of the present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. A rescue throwing decelerating body, characterized by: The application relates to a flying bomb body, which comprises a bomb body, a bullet head, a wing base, a slow descent assembly and a propelling power assembly, wherein the bullet head, the bomb body and the wing base are sequentially arranged from left to right, the bomb body is internally provided with a material cavity, the outer circumferential surface of the wing base is provided with a plurality of flight wing surfaces, the propelling power assembly is located in the wing base and is used for providing driving force for bomb body flight, and the slow descent assembly comprises a plurality of buffer blades, the back surface of the buffer blade is formed with an extension plate, the end of the extension plate is hinged to the flight wing surface, and the slow descent assembly is opened when the bomb body lands.

2. A rescue throwing deceleration body according to claim 1, characterized in that: The vertical section of the buffer blade is formed in an arc shape.

3. A rescue throwing deceleration body according to claim 1, characterized in that: The slow descent assembly comprises a driving assembly, and the driving assembly comprises a plurality of opening and closing motors, magnetic attraction elements or electrically-driven buckles. The driving assembly comprises a plurality of opening and closing motors, and the plurality of opening and closing motors are used for driving the plurality of buffer blades to expand. The driving assembly comprises a magnetic attraction element, the bomb body is formed with a blade adhering area on the circumferential surface of the side close to the wing base, the buffer blade is made of a magnetic metal material, the blade adhering area is provided with an electrified magnetic attraction plate, and the buffer blade is adsorbed in the blade adhering area. The driving assembly comprises an electrically-driven buckle, the bomb body is formed with a plurality of annularly-arranged clamping ports on the circumferential surface of the side close to the wing base, the clamping port is provided with an electrically-driven buckle, the surface of the buffer blade towards the circumferential surface of the bomb body is formed with a ring, the ring extends into the clamping port, and the electrically-driven buckle realizes the buckling of the ring by electrification or de-electrification.

4. A rescue throwing deceleration body according to claim 1, characterized in that: The bullet head is provided with a flight control rudder, which is used for controlling the flight and positioning of the bomb body.

5. A rescue cast decelerator body according to claim 1, wherein: The upper surface of the bomb body is formed with two hook ears which are arranged at the front and back.

6. A rescue cast decelerator body according to claim 5, wherein: A communication interface is further arranged between the two hook ears, and the communication interface is connected with a matching interface on the unmanned aerial vehicle when the hook ears are hung on the unmanned aerial vehicle.

7. A rescue cast decelerator body according to claim 1, wherein: The bullet head is provided with a flight rudder on the circumferential surface close to the bomb body, and the flight rudder comprises a plurality of operation pieces which are annularly and spacedly arranged.

8. A rescue throwing deceleration body according to claim 1, characterized in that: The front end of the bullet head is made of a buffer material.

9. A rescue throwing deceleration body according to claim 8, characterized in that: The buffer material is selected from rubber, foamed metal, porous foamed aluminum and polyethylene.

10. A rescue cast decelerator body according to claim 1, wherein: The middle part of the bomb body is formed with a containing groove penetrating through both sides, and the bomb body further comprises a material storage bin which is clamped in the containing groove.

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