CN212006942U

CN212006942U - Satellite guidance fire extinguishing shrapnel

Info

Publication number: CN212006942U
Application number: CN202020562314.1U
Authority: CN
Inventors: 李哲; 吴丹; 陈涛
Original assignee: Xi'an Sentton Intelligent Control Technology Co ltd
Current assignee: Xi'an Sentton Intelligent Control Technology Co ltd
Priority date: 2020-04-15
Filing date: 2020-04-15
Publication date: 2020-11-24
Anticipated expiration: 2030-04-15

Abstract

The utility model discloses a satellite guidance fire extinguishing shrapnel, the utility model discloses a cavity is constituteed to casing, foam back casing and control cabin casing in hood, foam procapsid, foam to place a plurality of bullets of putting out a fire in the cavity, drive arrangement makes this device arrive the overhead back of ignition, can shed the bullet of putting out a fire, the utility model discloses follow and shed the fire extinguishing agent to ignition aloft, its coverage is great to can compromise crown fire and surface fire.

Description

Satellite guidance fire extinguishing shrapnel

Technical Field

The utility model belongs to the fire extinguishing bomb field, concretely relates to satellite guidance fire extinguishing shrapnel.

Background

Fire is one of the most frequent and most common major disasters that threaten public safety and social development. With the development of society, people also have a variety of technical measures for fire prevention, fire fighting and the like.

Along with the development of science and technology in recent years, unmanned aerial vehicle is applied to all walks of life and professions, has also demonstrated advantages such as its flexibility, easy operation, safe and reliable in the fire control field. The biggest advantage of unmanned aerial vehicle is the conflagration scene that can the fastest entering personnel can't arrive fast to put out a fire the operation, can prevent the conflagration from spreading effectively. The existing air-drop fire extinguishing bomb matched with the fire extinguishing unmanned aerial vehicle is filled with a water system or water-based fire extinguishing agent, and the difference exists between the throwing effect and the fire extinguishing area compared with a dry powder fire extinguishing agent. The fire extinguishing bomb adopts dry powder extinguishing agent, the inside of the whole bomb body is filled with the dry powder extinguishing agent, the fixed-height detonating mechanism is used for tree crown fire or the grounding detonating mechanism is used for surface fire, and the fire situations which can be dealt with by the fixed-height detonating mechanism and the grounding detonating mechanism are single. And because the reason of unmanned aerial vehicle input precision, can not carry out the accuracy effectively and put out a fire at the conflagration initial stage, reduce the wasting of resources. Therefore, a fire extinguishing bomb which can accurately guide and simultaneously give consideration to crown fire and surface fire and has a large fire extinguishing area is needed.

The invention with application number of 201910663499.7 provides a forest fire extinguishing bomb with a time delay in propping open, which is controlled to break at a position 10-20 meters away from a tree crown and release a fire extinguishing agent through two parameters of the height of an airplane and the landing acceleration of a bomb body. The control mode does not consider factors such as resistance, airplane speed and the like, so that the error is large, and accurate aerial drop fire extinguishing at the initial stage of a fire disaster is difficult.

The invention with application number 201911094989.6 provides a double-insurance explosion-leading air-drop forest fire extinguishing bomb. The invention mainly explains that a double-insurance newspaper guiding technology is adopted, so that the generation of a dummy bomb is prevented, and the effective release dispersion and fire extinguishing of the fire extinguishing agent are ensured. Its shortcoming lies in that can't compromise crown fire to can't put in the precision and put out a fire.

Disclosure of Invention

An object of the utility model is to overcome current fire extinguishing bomb can not the accurate guidance, can not compromise simultaneously not enough such as crown fire and surface fire, provide a satellite guidance fire extinguishing primary and secondary bomb.

In order to achieve the purpose, the utility model discloses a casing and control cabin casing behind casing, foam in hood, foam procapsid, the foam, casing and control cabin casing connect gradually and constitute the cylindricality cavity jointly behind casing, the foam in hood, foam procapsid, the foam, are provided with a plurality of bullets of putting out a fire in the cylindricality cavity, are provided with the rudder on the control cabin casing, are provided with control system in the control cabin casing.

The elastic wing type air conditioner is characterized in that a front partition frame is arranged between the hood and the foam front shell, a force bearing partition frame is arranged between the foam front shell and the foam middle shell, a rear partition frame is arranged between the foam middle shell and the foam rear shell, a connecting partition frame is arranged between the foam rear shell and the control cabin shell, an elastic wing support is arranged between the force bearing partition frame and the rear partition frame, an elastic wing is arranged on the elastic wing support, and the foam middle shell is arranged among frames formed by the force bearing partition frame, the rear partition frame and the elastic wing support.

The front partition frame, the bearing partition frame and the rear partition frame are provided with a plurality of identical circular through holes, a plurality of fire extinguishing bullets are overlapped to form a cylindrical fire extinguishing bullet group, the fire extinguishing bullet group penetrates through the through holes in the front partition frame, the bearing partition frame and the rear partition frame, one end of the fire extinguishing bullet group is in contact with the connecting partition frame, and the other end of the fire extinguishing bullet group is arranged in the head cover.

The front partition frame, the force bearing partition frame and the back partition frame are all provided with a plurality of through holes, carbon tubes are inserted in the through holes, one ends of the carbon tubes are fixed on the connecting partition frame, and the carbon tubes enable the front partition frame, the force bearing partition frame, the back partition frame and the connecting partition frame to be coaxially arranged.

The carbon tubes on two sides of the bearing spacer frame are provided with two locking press blocks, and the two locking press blocks are fixed on the bearing spacer frame.

The bearing bulkhead is provided with a lifting lug.

A gas generator is arranged between the control cabin shell and the foam rear shell and connected with an air bag, and the air bag can extrude the fire extinguishing bullet after being inflated.

The control system comprises a GPS antenna, a GPS positioning module, an inertia measurement module, a flight control computer and a detonation height control device, wherein the flight control computer is connected with the inertia measurement module and the detonation height control device, the GPS antenna is connected with the GPS positioning module, and the flight control computer is used for acquiring data of the inertia measurement module and controlling the detonation height control device to be started.

The GPS antenna is placed obliquely.

And a separation connector is arranged at the top of the control cabin shell.

Compared with the prior art, the utility model discloses a casing and control cabin casing constitute the cavity behind casing, foam in hood, foam procapsid, the foam to place a plurality of bullets of putting out a fire in the cavity, the assembly is gone up drive arrangement and is made this device arrive the overhead back of the point of fire, can shed the bullet of putting out a fire, the utility model discloses from throwing the fire extinguishing agent to the point of fire aloft, its coverage is great to can compromise crown fire and surface fire.

Further, the utility model discloses be provided with inertial measurement module and GPS orientation module, can correct the flight gesture according to inertial measurement unit's data and the current coordinate that the GPS module measured in the flight, guarantee that the bullet of putting out a fire does not deviate predetermined trajectory.

Further, the utility model discloses a GPS antenna slope is placed, ensures that the GPS signal of fire extinguishing bomb when the flight of negative angle of attack is stable.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

fig. 2 is a schematic view of the internal structure of the present invention;

FIG. 3 is a schematic view, partially in section, of the rear foam housing and the control cabin housing of the present invention;

FIG. 4 is a schematic view of the foam shell structure of the present invention;

in the figure, 1-a head hood, 2-a front bulkhead, 3-a foam front shell, 4-a force bearing bulkhead, 5-a lifting lug, 6-a missile wing, 7-a foam rear shell, 8-a foam middle shell, 9-a control cabin shell, 10-a rudder, 11-a fire extinguishing bullet, 12-a carbon tube, 13-a connecting bulkhead, 14-a stop pressing block, 15-a rear bulkhead, 16-a missile wing support, 17-an air bag, 18-a gas generator, 19-a battery, 20-a steering engine, 21-a GPS antenna, 22-a GPS positioning module, 23-an inertia measuring module, 24-a flight control computer, 25-a detonation height control device and 26-a separation connector.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings.

Referring to fig. 1 to 4, the utility model discloses a casing 7 and control cabin casing 9 behind casing 8, the foam in hood 1, foam procapsid 3, the foam, casing 7 and control cabin casing 9 connect gradually and constitute the cylindricality cavity jointly in hood 1, foam procapsid 3, the foam, are provided with a plurality of bullets 11 of putting out a fire in the cylindricality cavity, are provided with rudder 10 on the control cabin casing 9, are provided with control system in the control cabin casing 9. A front partition frame 2 is arranged between the hood 1 and the foam front shell 3, a force bearing partition frame 4 is arranged between the foam front shell 3 and the foam middle shell 8, a rear partition frame 15 is arranged between the foam middle shell 8 and the foam rear shell 7, a connecting partition frame 13 is arranged between the foam rear shell 7 and the control cabin shell 9, a missile wing support 16 is arranged between the force bearing partition frame 4 and the rear partition frame 15, a missile wing 6 is arranged on the missile wing support 16, and the foam middle shell 8 is arranged between frames formed by the force bearing partition frame 4, the rear partition frame 15 and the missile wing support 16.

The hood 1 is made of EPS foam, so that the mass of the whole bomb can be reduced, and the hood and the front partition frame 2 are bonded by foam rubber; the shape of the head cover 1 is an ellipsoid shape, which can reduce the resistance of the fire extinguishing bomb in flight and can limit the fire extinguishing bullet 11 from moving forward. The front foam shell 3, the middle foam shell 8 and the rear foam shell 7 are made of EPS foam.

The fire extinguishing bullet 11 is a disposable dry powder fire extinguishing bullet, is cylindrical, is provided with a fire guiding rope outside, and quickly detonates an internal explosion device after meeting fire to throw fire extinguishing agent outwards.

Referring to fig. 2 and 4, a plurality of identical circular through holes are formed in the front partition frame 2, the force bearing partition frame 4 and the rear partition frame 15, a plurality of fire extinguishing bullets 11 are overlapped to form a cylindrical fire extinguishing bullet group, the fire extinguishing bullet group penetrates through the through holes in the front partition frame 2, the force bearing partition frame 4 and the rear partition frame 15, one end of the fire extinguishing bullet group is in contact with the connecting partition frame 13, and the other end of the fire extinguishing bullet group is arranged in the head cover 1. The front bulkhead 2, the force bearing bulkhead 4 and the rear bulkhead 15 are all provided with a plurality of through holes, carbon tubes 12 are inserted into the through holes, one ends of the carbon tubes 12 are fixed on the connecting bulkhead 13, and the carbon tubes 12 enable the front bulkhead 2, the force bearing bulkhead 4, the rear bulkhead 15 and the connecting bulkhead 13 to be coaxially arranged. The carbon tubes 12 on both sides of the bearing spacer frame 4 are provided with stop pressing blocks 14, the two stop pressing blocks 14 are fixed on the bearing spacer frame 4, and the bearing spacer frame 4 is provided with a lifting lug 5. The lifting lug 5 is made of stainless steel, is fixed at the top of the force bearing partition frame 4 by two M8 countersunk head screws, and is used as a hanging point for hanging fire extinguishing bombs on an airplane to bear the weight of the whole bomb.

The main bearing structure comprises a front partition frame 2, a bearing partition frame 4, a rear partition frame 15, a connecting

partition frame

13 and 4 carbon tubes 12, wherein all the partition frames are made of aluminum alloy materials, the four carbon tubes 12 are uniformly distributed in the upper, lower, left and right directions and are inserted into corresponding holes in the four partition frames, and the carbon tubes 12 and the partition frames are bonded by epoxy resin, so that the structural stability is ensured.

The stop pressing blocks 14 are made of aluminum alloy and are used for bearing the pressure of the stop arms of the weapon hangers on the carrier, and the two stop pressing blocks are sleeved on the upper carbon tube 12 and are respectively positioned at two sides of the bearing partition frame 4 and fixed on the bearing partition frame 4 by screws.

A plurality of missile wing supports 16 are arranged between the bearing spacer frame 4 and the rear spacer frame 15, the missile wings 6 are fixed on the missile wing supports 16, the missile wing supports 16 are made of aluminum alloy, are in a long strip shape and are 4, are uniformly distributed between the bearing spacer frame 4 and the rear spacer frame 15 in an X shape, and are fixed on the spacer frames at two sides by 4 screws. The missile wing 6 is made of flame-retardant plastic, and the bottom of the missile wing is provided with four T-shaped seats which are uniformly distributed in an X shape and fixed on a missile wing support 16 by screws.

Referring to fig. 3, a gas generator 18 is arranged between the control cabin shell 9 and the foam rear shell 7, the gas generator 18 is connected with an air bag 17, and the air bag 17 can extrude the fire extinguishing bullet 11 after being inflated. The control system comprises a GPS antenna 21, a GPS positioning module 22, an inertia measurement module 23, a flight control computer 24 and a detonation height control device 25, the GPS antenna 21, the GPS positioning module 22, the inertia measurement module 23, the flight control computer 24 and the detonation height control device 25 are fixed in the control cabin shell 9 as a whole by a support, the flight control computer 24 is connected with the inertia measurement module 23 and the detonation height control device 25, the GPS antenna 21 is connected with the GPS positioning module 22, and the flight control computer 24 is used for collecting data of the inertia measurement module 23 and controlling the initiation of the detonation height control device 25. The GPS antenna 21 is placed obliquely. The control cabin housing 9 is provided with a disconnect connector 26 at the top for communication with the aircraft, which disconnects by gravity.

The air bag 17 and the gas generator 18 together constitute a fire extinguishing bullet throwing and separating device which is fixed in the central position of the connecting bulkhead, and the air bag is placed in the hollow position after the fire extinguishing bullets are arranged.

The control cabin shell 9 is internally provided with four steering engines 20, the four steering engines 20 are distributed and fixed on the control cabin shell 9 in an X shape by screws, the steering engines 10 are made of aluminum alloy materials and used for controlling the flying posture of the fire extinguishing bomb, and the steering engines are fixed on a steering wheel of the steering engines 20 and driven by the steering engines 20. A battery 19 is fixed in the control cabin housing 9.

When the aerial carrier finds the ignition point, the measured longitude and latitude high coordinates are written into a flight control system of the fire extinguishing bomb which is electrified for self-inspection. With the launch command given by the operator, the carrier pylon is unhooked, the fire extinguishing bomb is dropped, the separating connector 26 is pulled away by gravity, the fire extinguishing bomb flies towards the target coordinate according to the predetermined trajectory, the flying attitude is corrected midway according to the data of the inertial measurement unit and the current coordinate measured by the GPS module, and it is ensured that the fire extinguishing bomb does not deviate from the predetermined trajectory.

When the grenade reaches a predetermined height above the target by satellite guidance, the detonation height control means 25 activates and activates the gas generator 18. The gas generator 18 generates a large amount of gas to blow the air bag 17 quickly, the pressure generated by the blowing of the air bag 17 presses the fire extinguishing bullet 11 to the periphery until the foam shell is broken, and the fire extinguishing bullet 11 is thrown to the periphery. The above process will be completed in a very short time, as seen by the naked eye, as the fire extinguishing bomb explodes over the target and the fire extinguishing bullet 11 is thrown over the fire spot. The fire extinguishing bullets 11 in the four groups explode in the crown when contacting the crown fire and throw the fire extinguishing agent to extinguish the crown fire, and after falling to the ground, explode in the ground when contacting the fire in the ground and throw the fire extinguishing agent to extinguish the surface fire.

Claims

1. The utility model provides a satellite guidance primary and secondary bullet of putting out a fire, a serial communication port, casing (7) and control cabin casing (9) behind casing (8), foam in hood (1), foam procapsid (3), the foam, casing (8) and control cabin casing (9) connect gradually and constitute the cylindricality cavity jointly behind casing (7) and the foam in hood (1), foam procapsid (3), the foam, be provided with a plurality of bullets of putting out a fire (11) in the cylindricality cavity, be provided with rudder (10) on control cabin casing (9), be provided with control system in control cabin casing (9).

2. The satellite guidance fire-extinguishing shrapnel as claimed in claim 1, characterized in that a front spacer (2) is arranged between the head cover (1) and the foam front casing (3), a bearing spacer (4) is arranged between the foam front casing (3) and the foam middle casing (8), a rear spacer (15) is arranged between the foam middle casing (8) and the foam rear casing (7), a connecting spacer (13) is arranged between the foam rear casing (7) and the control cabin casing (9), a missile wing support (16) is arranged between the bearing spacer (4) and the rear spacer (15), a missile wing (6) is arranged on the missile wing support (16), and the foam middle casing (8) is arranged between a frame formed by the bearing spacer (4), the rear spacer (15) and the missile wing support (16).

3. The satellite guidance fire-extinguishing shrapnel as claimed in claim 2, characterized in that the front bulkhead (2), the bearing bulkhead (4) and the rear bulkhead (15) are provided with a plurality of identical circular through holes, a plurality of fire-extinguishing bullets (11) are stacked to form a cylindrical fire-extinguishing bullet group, the fire-extinguishing bullet group passes through the through holes on the front bulkhead (2), the bearing bulkhead (4) and the rear bulkhead (15), one end of the fire-extinguishing bullet group is in contact with the connecting bulkhead (13), and the other end of the fire-extinguishing bullet group is arranged in the head cover (1).

4. The satellite-guided fire-extinguishing shrapnel as claimed in claim 2, characterized in that the front bulkhead (2), the force-bearing bulkhead (4) and the rear bulkhead (15) are provided with a plurality of through holes, the through holes are internally inserted with carbon tubes (12), one end of the carbon tube (12) is fixed on the connecting bulkhead (13), and the carbon tube (12) enables the front bulkhead (2), the force-bearing bulkhead (4), the rear bulkhead (15) and the connecting bulkhead (13) to be coaxially arranged.

5. The satellite-guidance fire-extinguishing shrapnel as claimed in claim 4, characterized in that the carbon tubes (12) on both sides of the bearing frame (4) are provided with two locking pressing blocks (14), and the two locking pressing blocks (14) are fixed on the bearing frame (4).

6. The satellite-guided fire-extinguishing shrapnel according to claim 2, characterized in that the force-bearing bulkhead (4) is provided with a lifting lug (5).

7. The satellite-guided fire-extinguishing shrapnel according to claim 1, characterized in that a gas generator (18) is arranged between the control cabin shell (9) and the foam rear shell (7), the gas generator (18) is connected with an air bag (17), and the air bag (17) can press the fire-extinguishing bullet (11) after being inflated.

8. The satellite-guided fire-extinguishing shrapnel as recited in claim 1, characterized in that the control system comprises a GPS antenna (21), a GPS positioning module (22), an inertia measurement module (23), a flight control computer (24) and a detonation height control device (25), the flight control computer (24) is connected with the inertia measurement module (23) and the detonation height control device (25), the GPS antenna (21) is connected with the GPS positioning module (22), and the flight control computer (24) is used for collecting data of the inertia measurement module (23) and controlling the detonation height control device (25) to be turned on.

9. A satellite-guided fire fighting shrapnel according to claim 8, characterised in that the GPS antenna (21) is placed obliquely.

10. The satellite-guided fire extinguishing shrapnel according to claim 1, characterized in that the control cabin housing (9) is provided with a breakaway connector (26) at the top.