CN101363699A - Spinning stability fire-fighting rocket bomb, launching set thereof and system - Google Patents
Spinning stability fire-fighting rocket bomb, launching set thereof and system Download PDFInfo
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- CN101363699A CN101363699A CNA2007101438583A CN200710143858A CN101363699A CN 101363699 A CN101363699 A CN 101363699A CN A2007101438583 A CNA2007101438583 A CN A2007101438583A CN 200710143858 A CN200710143858 A CN 200710143858A CN 101363699 A CN101363699 A CN 101363699A
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- fire extinguishing
- rocket projectile
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/46—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing gases, vapours, powders or chemically-reactive substances
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C3/00—Fire prevention, containment or extinguishing specially adapted for particular objects or places
- A62C3/02—Fire prevention, containment or extinguishing specially adapted for particular objects or places for area conflagrations, e.g. forest fires, subterranean fires
- A62C3/0228—Fire prevention, containment or extinguishing specially adapted for particular objects or places for area conflagrations, e.g. forest fires, subterranean fires with delivery of fire extinguishing material by air or aircraft
- A62C3/025—Fire extinguishing bombs; Projectiles and launchers therefor
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C31/00—Delivery of fire-extinguishing material
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C8/00—Hand tools or accessories specially adapted for fire-fighting, e.g. tool boxes
- A62C8/005—Receptacles or other utensils for water carrying; Bombs filled with extinguishing agents
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C99/00—Subject matter not provided for in other groups of this subclass
- A62C99/009—Methods or equipment not provided for in groups A62C99/0009 - A62C99/0081
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- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides an extinguishing rocket shell with stabilizing spin and distant delivery and a transmission device system thereof. A solid rocket engine is used as power for distantly delivering and spraying extinguishing agent for extinguishing fire; inclined multi-nozzle technology is adopted, so that when the extinguishing rocket shell flies along the default ballistic trajectory, the rocket shell body can maintain stabilizing spin; technologies of separation and non-separation of a warhead part and a boaster are respectively adopted to adapt to various fire extinguishing requirements; technologies of delay ignition and impact trigger are respectively adopted to adapt to requirements for different conditions.
Description
Technical field
But the present invention relates to a kind of spinning stability flight, be used for the rocket projectile and the emitter thereof of remote delivery and spraying fire-extinguishing agent.The present invention relates in particular a kind of can by multiple rocket launcher emission, by solid propellant rocket provide flight and spin stabilization power, throw the rocket projectile of packaged in advance extinguishing chemical and the method for designing and the technology of emitter thereof to target (district) at a distance.
Background technology
Fire is to threaten public safety in social life, one of disaster of harm people lives and properties.Now, fire is the common wicked problems that countries in the world face.It caused the heavy losses of many life, property to human society.Along with development of social productivity, the wealth of society increases day by day, and fire damage rises and the general trend of fire hazard expanded range is an objective law.According to the data introduction that the United Nations " World Fire Statistics Centre " provides, the loss of breaking out of fire, the U.S. doubled less than 7 years, and Japan doubled in average 16 years, and China doubled in average 12 years.More than 10,000 of whole world breaking out of fire every day causes hundreds of people's death.In recent years, about 40,000 of the annual breaking out of fire of China, dead people more than 2000, hinder 3000～4000 people, more than 10 hundred million yuan of the direct property loss that annual fire causes, especially cause the especially big malignant fire of tens people, hundreds of people's death to happen occasionally, caused tremendous loss for the country and people masses' lives and properties.Stern reality proves, fire is the higher a kind of disaster of occurrence frequency in the multiple disaster in the world today, also is a kind of disaster of space-time span maximum.
According to the characteristics of fire, in various types of fire, the scene of most of type fire or target area are that the fire extinguishing personnel can't implement to put out a fire nearby, need the remote extinguishing chemical of delivering to implement fire extinguishing.For example: forest fire.
Forest fire is the most dangerous enemy of forest, also is the most fearful disaster of forestry, and it can bring the most harmful to forest, has destructive consequence.Forest in blocks is not just burnt in forest fire, the animal in the injury woods, but also reduce the updating ability of forest, cause the effect of the barren of soil and the water conservation of destruction forest, even cause the ecological environment disequilibrium.Therefore, fast and effeciently subduing forest fire is a difficult problem anxious to be solved.
With regard to present fire extinguishing level, China and developed country still exist a certain distance.Remaining that China is at present the most frequently used relies on the manpower fire extinguishing, fire extinguishing personnel and fiery close contact, and danger coefficient increases greatly.It is reported that in recent years, air attack is put out a fire to save life and property the in the world main means and the main developing direction of forest fire.As: Canada drops into various aircraft for the forest fire of putting out a fire to save life and property is annual and surpasses 300, the amphibious forest extinguishing aircraft of custom-designed CL-415, maximum water carrying capacity reaches 6 tons.Though, carry out air attack with water and chemicals and effectively avoided direct contact of people with fire, the personnel's of putting out the fire safety coefficient is increased greatly.But the cost of this mode is quite high, and aircraft whenever to shed once the required time also very long, this is " an utterly inadequate amount " for forest fire.
In recent years, the development of various fire-fighting techniques is also very fast, develops multiple fire-fighting technique and equipment, concludes to get up to have: fixed, hand throwing type, air-drop formula and emission-type, its advantage and deficiency are respectively arranged, as: fixed and hand throwing type is applicable to small size fire and closely fire extinguishing; The air-drop formula mainly is by aircraft (as aircraft) air-drop extinguishing chemical, this fire-fighting mode cost height, and carrying capacity of aircraft is limited, and to come and go the load time long at every turn.According to the characteristics of fire, more satisfactory fire-fighting mode is an emission-type, can put out the large tracts of land fire at a distance, fast and safely.Up to now, state-owned several emission-type fire-fighting techniques and method in.What technology content was the highest is patent 99234830.7 (infrared ray passive guidance throwing type fire extinguisher bomb), adopts infrared guidance, the direction of rudder wing control flight cruise, and Here it is the cruising missile that can put out a fire, its cost and cost are not hanged down.Use for reference the fire extinguisher bomb utility model patent 99234950.8 of mortar technology in addition.And the stable fire extinguishing rocket projectile of the magnetic tape trailer wing, as: patent 94241892.1,94200178.8,98236505.5,97243352.X the function of this empennage is to make the fire extinguishing rocket projectile keep stable in flight course, empennage uses the quality that has also improved body, equal to reduce the quality of payload (extinguishing chemical), also improved cost simultaneously.
Summary of the invention
In sum, we are badly in need of a kind of fire extinguishing means and technology that can be safe, fast, efficient, cheap.
Purpose of the present invention just provides fire extinguishing rocket projectile, emitter and the emission system thereof that meets above-mentioned requirements.
According to a scheme of the present invention, a kind of fire extinguishing rocket projectile of spinning stability is provided, comprising: bullet portion and booster and bindiny mechanism thereof, wherein:
Described bullet portion comprises: fuse (301), bullet portion housing (302), extinguishing chemical (303),
Described booster comprises: bindiny mechanism, igniter, motor body, engine powder charge, grate and the jet pipe group of described booster and described bullet portion.
According to a scheme of the present invention, a kind of emitter of the rocket projectile of putting out a fire is provided, comprising: transmitting tube group (408), transmitting tube casing (407), wherein:
Described transmitting tube group (408) is carried out orientation control to the fire extinguishing rocket projectile;
Transmitting tube casing (407) links together by an axle and transmitting tube antinose-dive leg, and is connected as a body with the launcher base (403) that plays stable and fixation; And
Described fire extinguishing rocket projectile comprises: comprising: bullet portion and booster and bindiny mechanism thereof, wherein:
Described bullet portion comprises: fuse (301), bullet portion housing (302), extinguishing chemical (303),
Described booster comprises: bindiny mechanism, igniter, motor body, engine powder charge, grate and the jet pipe group of described booster and described bullet portion.
According to a scheme of the present invention, a kind of fire extinguishing rocket ammunition system of spinning stability is provided, comprising: the fire extinguishing rocket projectile, be used to launch the emitter of fire extinguishing rocket projectile, it is characterized in that:
Described fire extinguishing rocket projectile is made up of bullet portion and booster and bindiny mechanism thereof, wherein:
Described bullet portion comprises: fuse (301), bullet portion housing (302), extinguishing chemical (303),
Described booster comprises: connector, igniter, motor body, engine powder charge, grate and the jet pipe group of described booster and described bullet portion;
Described emitter comprises:
Transmitting tube group (408) is used for to the fire extinguishing rocket orientation of upspringing, and
Transmitting tube casing (407) is combined described transmitting tube, and described transmitting tube casing (407) links together by an axle and transmitting tube antinose-dive leg, and is connected as a body with a launcher base (403) that plays stable and fixation.
In sum, fire extinguishing rocket projectile of the present invention and emitter thereof etc. have constituted the complete remote fire extinguishing system of a cover, this is a kind of fire extinguishing means and technology that can be safe, fast, efficient, cheap, and fire extinguishing rocket projectile of the present invention and emitter thereof have possessed this several characteristics just.
1. safety: the effective range of fire extinguishing rocket projectile of the present invention can be delivered packaged extinguishing chemical at a distance and is sprayed onto target (district) within 10 kilometers, need not the close scene of a fire of fire extinguishing personnel.In addition, airframe material adopts environment amenable nonmetallic composite and rubber type of material, to object and environmental injury are little on every side.
2. quick: emitter of the present invention can be vehicle-mounted or car drag, mobility is good, can arrive at emitting area fast, launch preparation time is short, twice emitting time (shooting) is also short.
3. efficient: emitter of the present invention is to adopt multibarrel rocket bullet launching tube (pipe), can the multitube salvo, the closeness height, cover characteristics such as scene of a fire area is big, can simultaneously a large amount of extinguishing chemicals be shipped to the target area, even the fire on the abrupt slope that can't base oneself upon for personnel, also can implement fire extinguishing effectively.
4. cheap: every technology of the present invention all is mature technologies, will specifically set forth in the content below, and some technology has the application of nearly half a century and the history of development, and just because of technical maturation, cost will reduce greatly.Adopt cheap material and manufacturing process in design, will make that cost further reduces.
The present invention does not have optional features such as rear-fin stabilizer, and the stable employing body spinning stability technology of flight had both reduced cost, had increased payload again, simultaneously because the spin of body also helps evenly shedding of extinguishing chemical.
The present invention can incite somebody to action packaged extinguishing chemical in advance safe, fast, efficient and at an easy rate, delivers and is sprayed onto the target area at a distance and implement fire extinguishing.
The present invention is not only applicable to remote forest extinguishing, also goes in the remote fire extinguishing of other kind, as: on the fire such as prairie fire, high-rise (or group) fire.In introducing explanation of the present invention, though with the forest extinguishing is that example describes, but and do not mean that the present invention can only be applied to forest extinguishing, in fact of the present invention, be applicable to that all need to deliver extinguishing chemical and implement on scenes of fire and target of fire extinguishing at a distance.
Description of drawings
Fig. 1 is fire extinguishing rocket projectile and emitter effect schematic diagram thereof;
Fig. 2 is fire extinguishing rocket projectile and emitter schematic diagram thereof;
Fig. 3 a is a fire extinguishing rocket projectile body structure schematic diagram;
Fig. 3 b is a fire extinguishing rocket projectile body rearview
Fig. 4 a and Fig. 4 b show side-looking and the front elevational schematic according to emitter of the present invention respectively;
Fig. 5 is a body separating mechanism schematic diagram;
The specific embodiment
Describe the present invention below with reference to accompanying drawings.
Fig. 3 is according to fire extinguishing rocket projectile structural representation of the present invention.Referring to Fig. 3, specifically describe formation according to fire extinguishing rocket projectile of the present invention.
As shown in Figure 3, the fire extinguishing rocket projectile is made up of bullet portion and booster and bindiny mechanism thereof.Bullet portion comprises: fuse 301, bullet portion housing 302, extinguishing chemical 303 and bullet portion and booster coupling part 304.
Booster comprises: bullet portion and booster coupling part 304, igniter 305, motor body 306, engine powder charge (propellant charge) 307, booster grate 308 and jet pipe (group) 309 and 312, booster igniting seat and lead 310 etc.
The effect of fuse is to make the fire extinguishing rocket projectile when reply different target and purpose, after the fire extinguishing rocket projectile flies predetermined zone, opens bullet portion housing in good time, and the encapsulation of extinguishing chemical, sheds extinguishing chemical then, reaches best fire extinguishing effect.
Adopted three kinds of fuse technology in the present invention, be respectively: contact fuze, time faze and infrared ray influence fuse, back two kinds belong to non-contact fuze.
Contact fuze is made up of parts such as protective cap, firing pin, stab detonator, booster explosives.When fire extinguishing rocket projectile when hitting target, the fuse protective cap is crushed earlier, and the boss of firing pin is pressed down, and firing pin promptly rings the detonator thorn, and bullet portion housing is opened medicine and is detonated subsequently, and bullet portion housing and extinguishing chemical encapsulation are opened, and shed extinguishing chemical then.This fuse structure is more cheap.
Time faze is a kind of non-contact fuze.The history of time faze is longer than contact fuze, this fuse by blast cap, set parts such as cap, clockwork, firing pin, igniter cap and form.Before the shooting of fire extinguishing rocket projectile, people need the far and near and purpose needs according to target, turn with the fuze setting spanner and set cap, adjust the length of armed period, finish the time setting to fuse.After the emission of fire extinguishing rocket projectile, the work of fuse clockwork, second hand rotated counterclockwise to institute's set time during corresponding angle, the type hole that sets on the sleeve is aligned, firing pin promptly is released, thorn rings igniter cap then, and fuze action is opened fire extinguishing rocket projectile shell just at vantage point of distance target or predetermined spatial domain.
The infrared ray influence fuse also is a kind of non-contact fuze.This fuse utilizes infrared light-wave to obtain target information and controls fuze actuation, and it partly is made up of ignition control system, security system, explosive train and energy source device etc.Its ignition control system is made up of sensor, signal processing apparatus and actuating unit etc.During near target, the induction type sensor of fuse comes induction targets information according to infrared ray (scene of a fire) characteristic of target and surrounding environment at the fire extinguishing rocket projectile, sends the information of induction to signal processing apparatus (signal processing circuit).Signal processing apparatus amplifies, screens the signal that receives and differentiates processing, from numerous and diverse signal, distinguish target information, in the time of in the clarification of objective amount is included in fire extinguishing rocket projectile fire extinguishing characteristic, it is exactly favourable fuze actuation point, signal processing apparatus is just to actuating unit output enabling signal, and actuating unit gets angry the electric initiating element in the explosive train again to explosive train output time break, open the encapsulation of bullet portion housing and extinguishing chemical, finish the mission of fuse.
The mode of bullet portion housing is divided into two kinds of explosion type and mechanical types again, also can adopt the combination of dual mode according to actual needs.On bullet portion housing, set in advance the weakening groove, when opening in order to explosion type, bullet portion housing is opened by predetermined way; In addition, also bullet portion housing just can be divided into several lobes in advance, open used in order to mechanical type.
The effect of bullet portion housing is at ordinary times as the container of dress extinguishing chemical in, make bullet portion keep certain geometric shape (reducing air drag) during flight, so bullet portion housing needs certain rigidity and intensity.Bullet of the present invention portion housing adopts composite cheaply, and on the one hand, its rigidity and intensity can meet the demands; On the other hand, the processing technology maturation of composite, low price.
The effect of extinguishing chemical is the payload of fire extinguishing rocket projectile, and the selection of extinguishing chemical is not a content of the present invention, but in view of the fire extinguishing rocket projectile be the main delivery vehicle of extinguishing chemical, the physical state and the type of feed of extinguishing chemical had ask for something.Fire extinguishing rocket projectile of the present invention can load bearing fluid, the extinguishing chemical of gas or three kinds of physical states of solid (Powdered), and this is characteristics of the present invention.At forest extinguishing, the present invention advises adopting the extinguishing chemical of liquid or solid state.For the extinguishing chemical of gaseous state, can be applied to the fire extinguishing occasion of other type.In a word, fire extinguishing rocket projectile of the present invention all is suitable for the extinguishing chemical of above three kinds of physical states.No matter adopt the extinguishing chemical of which kind of physical state, the fire extinguishing rocket projectile all requires the inner space of bullet portion is filled up, and remaining space is not arranged, otherwise will influence the stability of fire extinguishing rocket projectile flight and the precision of drop point.
The main effect of booster is, as requested whole fire extinguishing rocket projectile body is pushed to predetermined target area, and it comprises: several sections such as igniter and security insurance mechanism, motor body, motor grain, grate and jet pipe group.
Igniter and security insurance mechanism.The main effect of this part is to adopt the electric ignition mode as requested, initial igniter, and ignition engine powder charge powder column, combustion gas produces thrust through the jet pipe ejection.For preventing that such prevention effect plays in security insurance mechanism at ordinary times storage and the mis-ignition in the transportation, it can be divided into mechanical type insurance institution, electric insurance institution again, and electromechanical insurance institution, as required apolegamy.
The main effect of motor body is to have three, one,, in storage and the transportation, it is the reservoir vessel of propellant charge at ordinary times, requiring has certain sealing property, prevents that dust and moisture from entering engine interior; The 2nd,, in the process of engine operation, it is a pressure vessel of pressing in bearing, and needs certain rigidity and intensity; The 3rd,, in the flight course of fire extinguishing rocket projectile, keep original profile, make it to fly by destined trajectory.Therefore, the present invention adopts the preferred material of composite as housing, and the rigidity of composite and intensity satisfy the requirement of motor body, and in addition, cheap, the technical maturity of composite are suitable for producing in batches.
The main effect of motor grain is the source of thrust power energy, and after igniter was lighted, the combustion gas that the propellant charge burning produces a large amount of HTHPs produced thrust through the jet pipe ejection.Current propellant kind commonly used has double base propellant, modified double base propellant and composite propellant etc.Wherein, the energy of double base propellant is minimum, and price is low, and the energy of composite propellant is the highest, the price height, and the energy of modified double base propellant and price are between between the two above.Can select the propellant kind according to the actual needs for use, but double base propellant, its technical maturity, use extensive, cheap.
How many roots propellant charge selects for use, and are relevant with many factors, be determined by the overall plan of fire extinguishing rocket projectile.For example: concerning a certain rocket gunpowder, under some pressure, there is a definite value in total burning area of propellant loading with the ratio of nozzle throat area, and under the certain condition of caliber, spray throat area size is restricted, the variation of spray throat area size can be very not big, and so, powder charge burning area size roughly also is a definite value.Obviously, if select for use the powder charge radical few, in order to guarantee certain burning area, the powder charge powder column can increase, and the powder charge meeting increases, and range increases far; Otherwise the powder charge radical is many, and grain length is short, and explosive payload reduces thereupon, and range also reduces.So the powder charge radical is determined by overall plan.In addition, the selection of powder charge radical, also frequent consideration should have the section packing factor of trying one's best big.Therefore, in the present invention, adopt many cast powder charge technology, this technology maturity height, charge process is simple, and cost is low.
Grate claims support again, and the effect of grate mainly is a drug blocking, limits propellant charge at ordinary times and moves forward and backward vertically; During engine operation, powder charge burns thinner and thinner, and grate plays and prevents the powder charge ejection or stop up the spray larynx.Grate is drug blocking reliably, guarantees that again combustion gas can enter jet pipe through grate smooth-goingly, so grate will have enough big breathing area and intensity.The grate condition of work is very abominable, and the one, be subjected to the encirclement of high-temperature fuel gas and wash away; The 2nd, bear because of rotating the effect of the centrifugal intertia force that produces at a high speed, so grate is done in general employing casting.The material of grate should adopt the fiberglass and the mild steel of anti-ablation.
The jet pipe group is a vitals of booster, and the required thrust of flight and whole fire extinguishing rocket projectile are free stablizes required rotary power to the jet pipe group for the fire extinguishing rocket projectile provides in the present invention.The jet pipe group has two kinds of compound modes in the present invention: a kind of jet pipe group of being made up of a plurality of angled nozzles with certain inclination angle; Another is except that a plurality of angled nozzle groups, also has the main jet pipe at one or more no inclinations angle.
The jockey of bullet portion and booster.In the present invention, have two kinds of interconnection techniques can supply to select for use, they are respectively monoblock type and separate type.Monoblock type is that bullet portion and booster are connected in one, and in emission, flight and the arrival target area of fire extinguishing rocket projectile, both are always one and do not separate; Separate type is in the flight course of fire extinguishing rocket projectile, promptly behind the booster end-of-job, booster and warhead section from.Monoblock type is simpler than separate type, and separate type many a cover separating mechanism.In the present invention, the mode that this cover separating mechanism adopts the blast of firing delay to separate, promptly, because effective time of booster is certain, the ignition delay time of separating mechanism is defined as working time of booster, can effectively both be separated, make booster break away from the fire extinguishing rocket projectile, fall in the place ahead, launching site, simultaneously bullet portion flies to the target area in boosting with play a part under the spin inertia.Fig. 1 is the course of work schematic diagram that does not have the fire extinguishing rocket projectile that separates according to bullet of the present invention portion and booster.
As shown in Figure 1, according to bullet of the present invention portion with the course of work that booster does not have the fire extinguishing rocket projectile that separates be: the rocket projectile (102) of will putting out a fire is filled in the emitter (102), relation table according to angle and range, regulate the angle of departure governor motion (404) of emitter (202), connect good priming supply circuit (not shown) and connect power supply, light the booster of bullet, booster is started working and is produced thrust.The fire extinguishing rocket projectile flies out along transmitting tube (also being known as finder) (408) under the promotion of booster, flies to target area (105) along predetermined ballistic trajectory (103).
For need be in the target area situation (as forest fire) of (105) overhead spraying fire-extinguishing agent, then fly to when shedding point (104) when the fire extinguishing rocket projectile, start fuse (301), open the extinguishing chemical encapsulation of bullet portion, to target spraying fire-extinguishing agent (303), implement fire extinguishing.
When putting out the fire on ground, then adopt contact fuze (301), open the extinguishing chemical encapsulation of bullet portion,, implement fire extinguishing to target spraying fire-extinguishing agent (303) for needs.
Fig. 2 is according to bullet portion of the present invention and the separative fire extinguishing rocket projectile of booster course of work schematic diagram.
As shown in Figure 2, according to bullet of the present invention portion with the course of work that booster does not have the fire extinguishing rocket projectile that separates be: the rocket projectile (202) of will putting out a fire is filled in the emitter (202), relation table according to angle and range, regulate the angle of departure governor motion (404) of emitter (202), connect priming supply circuit (not shown) and connect power supply, light the booster of bullet, booster is started working and is produced thrust.The fire extinguishing rocket projectile flies out along transmitting tube (also being known as finder) (408) under the promotion of booster, and beginning is along predetermined ballistic trajectory (203) flight.When the booster end-of-job, start separating mechanism, with booster and warhead section from, wherein, the start-up time of separating mechanism is for setting according to engine operating duration in advance.Separate back booster disengaging trajectory and fall, bullet portion then continues to fly to target area (206) along destined trajectory.
For need be in the target area situation (as forest fire) of (206) overhead spraying fire-extinguishing agent, then fly to when shedding point (205) when the fire extinguishing rocket projectile, start fuse (301), open the extinguishing chemical encapsulation of bullet portion, to target spraying fire-extinguishing agent (303), implement fire extinguishing.
When putting out the fire on ground, then adopt contact fuze (301), open the extinguishing chemical encapsulation of bullet portion,, implement fire extinguishing to target spraying fire-extinguishing agent (303) for needs.
Fig. 5 is the schematic diagram that bullet portion separates with the booster linkage section.After the booster design was finished, its working time was just definite, therefore according to the working time of booster, also just can determine the disengaging time point of bullet portion and booster, just the time point of the end-of-job of booster.
Referring to Fig. 3 and Fig. 5, describe bullet portion and the concrete separation process of booster in detail.After the igniting seat of booster and lead (310) energising, cause igniter (504), light booster powder charge powder column (505) then, booster starts starts working, and delayer (508) timing simultaneously begins.At this moment put out a fire rocket projectile under the thrust of booster, fly along destined trajectory.When the booster end-of-job, delayer (508) separates powder charge (510) by what lead (511) and igniting socket (509) started separating mechanism, and that is scheduled to then separates with booster along will the put out a fire bullet portion of rocket projectile of hoop burble point (503).So far, whole separation process finishes, and bullet portion continues to fly to target along destined trajectory, and the separated booster that gets off will fall earthward.
According to fire extinguishing rocket projectile of the present invention, can there be different designs in its bullet portion as required with booster, and these designs can be combined into various fire extinguishing rocket projectile.With reference to Fig. 1, Fig. 3 and Fig. 5, to its possible design and be combined into line description.
The main effect of bullet portion is to load extinguishing chemical, and just extinguishing chemical is the payload of bullet portion and fire extinguishing rocket projectile.In the research and design process of fire extinguishing rocket projectile, a main job is the quantity that increases extinguishing chemical to greatest extent, and reduces the quality of non-payload.Different fire extinguishing rocket projectiles, bullet portion and booster at different targets and situation, can be designed in the outer scope of application and the field that increases fire extinguishing rocket projectile of the present invention to greatest extent.Specifically be divided three classes:
1. different bullet portion: the bullet portion that promptly designs different specification size, geometry and extinguishing chemical useful load.Wherein, different specifications comprise: the external diameter of bullet portion and length etc. characterize size; Geometry comprises: the position of bullet housing geometry, fuse, the type of feed of extinguishing chemical etc.Because bullet portion specification and geometry is different, must cause the variation of extinguishing chemical useful load.Therefore, cause specification, geometry and quality (comprising the extinguishing chemical quality) different of bullet portion, just can select different bullet portions for use, increased applicability of the present invention according to different targets and situation.
2. different booster: be meant different geometries, different propellant loading amount, different engine operating durations, different thrust and revolving force etc.Specifically be exactly to design the booster of various outer diameter and length as requested; What, working time of engine of propellant loading amount in the engine, and motor power and revolving force, all can design as requested; In addition, booster main thrust and the quantity and the position of playing the churning pipe also can be designed as required.Therefore, according to above elaboration, can design different boosters.
3. different fire extinguishing rocket projectile: can be combined into different fire extinguishing rocket projectiles by above-mentioned different bullet portion with booster,, improve the applicability of fire extinguishing rocket projectile of the present invention greatly to adapt to different targets and situation.Here it should be noted that needs a bindiny mechanism between bullet portion and the booster, for the various combination of bullet portion and booster, its interface size, be the size of two-part total coupling part, must coupling with consistent, could guarantee the feasibility of various combinations.
The various fire extinguishing rocket projectile that obtains for above-mentioned different combination all can adopt Fig. 1 or mode shown in Figure 2 to launch.
Emitter
Fig. 4 a and Fig. 4 b show side-looking and the front elevational schematic according to emitter of the present invention respectively.Referring to Fig. 4 a and Fig. 4 b the emitter of fire extinguishing rocket projectile according to the present invention is described.
As shown in Figure 4, emitter is made up of transmitting tube (group) (408 and 409), the support (405) of launching bobbin carriage (407), the governor motion (404) of launching the inclination angle, firing box, launcher base (403) etc. according to the present invention.
The main effect of transmitting tube (group) (408 and 409) is the orientation to an initial flight of fire extinguishing rocket projectile, so be also referred to as finder.The present invention adopts smooth interior thorax, is used to launch the rocket projectile of rotation.
Adopt the tubular type radiation pattern that the fire extinguishing rocket projectile is had many benefits: at first, the transmitting tube that has light-wall pipe to make takes up space little, arrange between transmitting tube and the transmitting tube closely, so that a plurality of (as: tens) transmitting tube can be installed on a launcher, realize the expectation that a time salvo can be launched tens rocket projectiles continuously; Secondly, when rocket projectile moved in pipe, combustion gas was subjected to the constraint of transmitting tube, more smooth-going ground flows backward, disturbance to adjacent fire extinguishing rocket projectile and transmitting tube is all less, therefore can reduce the disturbance to transmitting tube, thereby reduces the initial disturbance to rocket projectile flight.Therefore, among the present invention, the quantity of transmitting tube can be determined according to concrete use needs.
Consider the requirement of the aspects such as repeated use of transmitting tube, adopt metal material or nonmetallic materials to make, in be coated with high-temperature resistant coating.
Emission bobbin carriage (407) is a casing that a plurality of transmitting tubes are fixed together, and also is an intermediary agency that links to each other with transmitting tube support (405), and the transmitting tube support links to each other with the launcher base (403) that plays stabilization again.
The main effect of the governor motion (404) at emission inclination angle is the inclination angle of regulating emission, to reach the purpose of regulating fire extinguishing rocket projectile range, adopts succinct method in the present invention, promptly realizes by one group of gear.In addition, the governor motion (404) at emission inclination angle comprises angle scale and rocking handle etc.
According to emitter of the present invention can be vehicle-mounted or car drag, mobility is good, can arrive at emitting area fast, launch preparation time is short, twice emitting time (shooting) is also short.Have simultaneously simple in structure, size is little, in light weight, at ordinary times easy to maintenance, can long preservation, characteristics such as transportation safety.
The range of fire extinguishing rocket projectile also is an important problem.Range of the present invention improves two kinds of approach: the one, increase booster propellant loading amount; The 2nd, improve the energy of booster propellant loading, that is, adopt more high-octane propellant.But for this no control involved in the present invention and the fire extinguishing rocket projectile of spinning stability, its range should not be too far away, and range too far will cause the putting out a fire divergence of rocket projectile drop point is too big, and the degree of accuracy reduces.
If, range further be improved, except that adopting two kinds of above-mentioned approach, also need correspondingly improve precision, can not sacrifice precision for improving range.For improving precision, just need control the flight of fire extinguishing rocket projectile, increase the control corresponding system, can realize like this, but cost has also correspondingly improved.
Therefore, the present invention is designed to maximum range in the 10km, and it is enough substantially to put out various fire in this scope.If the target area outside emitter 10km, then adopts angle of departure governor motion to regulate.
Shown in Figure 4 is the schematic diagram of multibarreled launcher.Referring to Fig. 4, shown in it is the multibarreled launcher of 4 * 10 transmitting tubes of arranging.
As shown in Figure 4, the emission bobbin carriage (407) of interior dress transmitting tube (408) links to each other by axle with the support (405) of emitter.Launcher governor motion (404) is that a gear mechanism (not shown) links to each other with emitter support (405) again, adjusting by gear mechanism, can regulate the luffing angle of emission bobbin carriage (407), thereby reach the effect of regulating transmitting tube (finder) (408) emission angle.
The method of practical operation is as follows, according to the wind speed and direction at scene, in conjunction with the angle of departure and range table, regulates emission angle by regulating angle of departure governor motion (404).
Be maximum range when the angle of departure is 45 ° in theory, the target within maximum range then needs to regulate the range of fire extinguishing rocket projectile, two kinds of methods is arranged by regulating the angle of departure, reaches the purpose of regulating range, is respectively to heighten or turn down the angle of departure.Situation for firing angle occurred frequently, wind speed and direction will be very big to the trajectory influence of fire extinguishing rocket projectile, further influence the precision of drop point, therefore, except that special circumstances (being subjected to the influence of the place ahead barrier as ballistic trajectory), generally adopt low angle of departure scheme.
Those of ordinary skill in the art can increase or reduce the quantity of the transmitting tube shown in Fig. 4 according to actual needs, therefore, and does not mean that the present invention is confined on 4 * 10 transmitting tubes of arranging.
In addition, emitter of the present invention not only can be selected many transmitting tube emission fire extinguishing rocket projectiles, also can and need at particular case, adopts single transmit pipe emission fire extinguishing rocket projectile.
Fire extinguishing rocket projectile according to the present invention need not additional stability parts such as rear-fin stabilizer, and the stable employing body spinning stability technology of flight had both reduced cost, had increased payload again, simultaneously because the spin of body also helps evenly shedding of extinguishing chemical.Hereinafter will describe the operation principle that the fire extinguishing rocket projectile advances and rotates in detail.
The operation principle that the fire extinguishing rocket projectile advances and rotates
An important attribute of dynamic system is exactly a stability.The flight course of fire extinguishing rocket projectile of the present invention is exactly a dynamics problem, and its stability problem at first will be considered, also is an emphasis of the present invention.
Be familiar with as those of ordinary skill in the art, " barycenter " is the center of whole fire extinguishing rocket projectile quality; " the pressure heart " is that the fire extinguishing rocket projectile is in the process of flight, because the body profile, the power of air effect on body also is known as air force and (just why can flies as aircraft, and do not fall down, be exactly the result of aerodynamic effect) point of making a concerted effort to be acted on.
If we design an aircraft, its barycenter and the pressure heart can overlap on one point to be gone up, with regard to absolute stability, but in fact this is impossible! The barycenter and the pressure heart be not on a point, because lever principle, a lever has a fulcrum, and the another side of lever has a power in effect, this lever overturns certainly or rotates, the problem of stability has just been come out, and therefore for aircraft, wants flight stability, the band wing---wing, aircraft, guided missile all are with the wing, or rotation, and shell, bullet all rotate.
Spin fire extinguishing rocket projectile of the present invention, it presses the heart before barycenter, and therefore, turning torque will be ordered about bullet axle rate of departure direction in flight course, make the fire extinguishing rocket projectile in flight course, overturn, the precision of the range and the drop point of rocket projectile in case the upset generation can't guarantee to put out a fire.For the kinetic stability that makes described fire extinguishing rocket projectile its bullet axle in flight course on velocity attitude, the fire extinguishing rocket projectile is rotated at a high speed around the bullet axle, to produce the gyroscopic couple turning torque of contending with, keep the stability of bullet axle.The power that causes the high speed rotation is due to the guiding moment of gas that angled nozzle sprays of fire extinguishing rocket projectile booster of the present invention, just the thrust that angled nozzle produced tilts, this inclination thrust produces two component, first component is axial along fire extinguishing rocket projectile body, and this component produces to advance to described fire extinguishing rocket provides thrust; The secondth, component is axially vertical with described fire extinguishing rocket projectile body, and with the tangent power of described fire extinguishing rocket projectile body hoop, be known as revolving force, under the driving of this component, described fire extinguishing rocket projectile body rotates vertically.Therefore, fire extinguishing rocket projectile of the present invention adopts a plurality of angled nozzles, so that turning moment is provided, makes described fire extinguishing rocket projectile in the rotation of flight course high speed, reaches the purpose of flight stability.
In the present invention, except that described fire extinguishing rocket projectile spin keeps the stability of flight, the rotation of fire extinguishing rocket projectile also has other favourable aspect, can eliminate the thrust eccentric that described fire extinguishing rocket projectile is produced exactly in manufacturing and assembling process, and the influence factor of the aspects such as aerodynamic force off-centre that in flight course, produced, therefore, can improve the closeness of described fire extinguishing rocket projectile, reduce the distribution of fire extinguishing rocket projectile, improve fire accuracy.
Relevant with its body length according to the required rotating speed of stablizing of fire extinguishing rocket projectile of the present invention with its flight maximal rate.
Fire extinguishing rocket projectile according to the present invention has adopted the spinning stability scheme, compares with the fire extinguishing rocket projectile scheme of other type to have the following advantages:
1. described fire extinguishing rocket projectile body contour dimension is smaller, and is greatly convenient aspect transportation of fire extinguishing rocket projectile and firing operation;
2. in the present invention, it is shorter to launch the required transmitting tube (finder) (408) of described fire extinguishing rocket projectile, can make emitter design lightly, flexible;
3. the closeness of fire extinguishing rocket projectile of the present invention can keep higher level, generally speaking, all is higher than finned rocket;
4. fire extinguishing rocket projectile of the present invention can also carry out simple and easy shooting.
In the present invention, described fire extinguishing rocket projectile has two kinds of jet pipe group designs, shown in Fig. 3 b, a kind of is by a main jet pipe (not shown) and an a plurality of scheme that is constituted around the inclination multi nozzle group (312) of elastomer axis on axis, the main jet pipe produces the thrust that described fire extinguishing rocket projectile flight is advanced, a plurality of inclination multi nozzles then produce the required revolving force of described fire extinguishing rocket projectile body spinning stability, and are the required thrust except that main thrust of described fire extinguishing rocket projectile flight; Another kind is that the dereliction jet pipe is only by a plurality of schemes that constituted around the inclination multi nozzle group (312) of elastomer axis, the angled nozzle of described fire extinguishing rocket projectile, except that provide with the tangent revolving force of the hoop of described fire extinguishing rocket projectile body, the required flying power of described fire extinguishing rocket projectile, all the axial thrust load by the thrust that angled nozzle produced is provided.In actual applications, these two kinds of schemes can be selected for use at concrete actual conditions.
The above is the preferred embodiments of the present invention only, is not limited to the present invention, and for a person skilled in the art, the present invention can have various changes and variation.Within the spirit and principles in the present invention all, any modification of being done, be equal to replacement, improvement etc., all should be included within the claim scope of the present invention.
Claims (10)
1. the fire extinguishing rocket projectile of a spinning stability comprises: bullet portion and booster and bindiny mechanism thereof, wherein:
Described bullet portion comprises: fuse (301), bullet portion housing (302), extinguishing chemical (303),
Described booster comprises: bindiny mechanism, igniter, motor body, engine powder charge, grate and the jet pipe group of described booster and described bullet portion.
2. fire extinguishing rocket projectile as claimed in claim 1, wherein
Described bullet portion housing adopts composite to make.
3. fire extinguishing rocket projectile as claimed in claim 2, wherein
On described bullet portion housing, set in advance the weakening groove, make described bullet portion housing be explosion type and open by reservation shape.
4. fire extinguishing rocket projectile as claimed in claim 2, wherein
Described bullet portion housing is divided into several lobes in advance, opens used in order to mechanical type.
5. fire extinguishing rocket projectile as claimed in claim 1, wherein,
Described bindiny mechanism adopts separate type, and it is behind the booster end-of-job, and delayed igniting blast is separated described booster from fire extinguishing rocket projectile body.
6. fire extinguishing rocket projectile as claimed in claim 1, wherein,
Described bindiny mechanism adopts monolithic construction, and it is connected to become an overall structure with bullet portion and booster, in the whole process of described fire extinguishing rocket projectile work, links together all the time and does not separate.
7. fire extinguishing rocket projectile according to claim 1 is characterized in that:
Described extinguishing chemical (303) is opened under the effect of fuse (301), and is shed the target area.
8. according to one of any described fire extinguishing rocket projectile of claim 1 to 7, it is characterized in that:
The physical state of described extinguishing chemical can be one of following three kinds: liquid, gas or solid.
9. fire extinguishing rocket projectile according to claim 1 is characterized in that:
Described fuse adopts the contact fuze mode.
10. fire extinguishing rocket projectile according to claim 1 is characterized in that:
Described fuse adopts the time faze mode.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101438583A CN101363699A (en) | 2007-08-06 | 2007-08-06 | Spinning stability fire-fighting rocket bomb, launching set thereof and system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101438583A CN101363699A (en) | 2007-08-06 | 2007-08-06 | Spinning stability fire-fighting rocket bomb, launching set thereof and system |
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| CN101363699A true CN101363699A (en) | 2009-02-11 |
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| CNA2007101438583A Pending CN101363699A (en) | 2007-08-06 | 2007-08-06 | Spinning stability fire-fighting rocket bomb, launching set thereof and system |
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| CN102080607A (en) * | 2009-11-30 | 2011-06-01 | 贵州航天风华精密设备有限公司 | Motor for forest fire extinguishing bomb |
| CN102080607B (en) * | 2009-11-30 | 2014-06-18 | 贵州航天风华精密设备有限公司 | Motor for forest fire extinguishing bomb |
| CN102155878A (en) * | 2010-12-20 | 2011-08-17 | 吉林保利科技中试有限公司 | 130 mm PL59A type base bleed and rocket composite range-enhanced high explosive projectile of howitzer |
| CN102620603A (en) * | 2012-03-31 | 2012-08-01 | 中国人民解放军济南军区72465部队 | Installation structure of initial-speed measuring coils and time setting coil of air-defense antiaircraft gun muzzle |
| CN102620604A (en) * | 2012-03-31 | 2012-08-01 | 中国人民解放军济南军区72465部队 | Time-fuze gun muzzle setter of air-defense antiaircraft gun |
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| CN103016208A (en) * | 2012-12-12 | 2013-04-03 | 北京航空航天大学 | Wheel-shaped charging device for hybrid rocket engine |
| CN103016208B (en) * | 2012-12-12 | 2015-02-11 | 北京航空航天大学 | Wheel-shaped charging device for hybrid rocket engine |
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| CN104492018A (en) * | 2014-11-28 | 2015-04-08 | 崔景军 | Fire extinguishing method and fire extinguishing system in air mode |
| CN106075785A (en) * | 2016-06-28 | 2016-11-09 | 成都启源电子信息技术有限公司 | Intelligent fire fighting discharger |
| CN109502053A (en) * | 2018-12-14 | 2019-03-22 | 中国飞行试验研究院 | A kind of amphibious aircraft fire extinguishing task system Flight Test Method |
| CN109443115A (en) * | 2018-12-14 | 2019-03-08 | 江苏溧航航空科技有限公司 | A kind of fire extinguisher bomb system with the compound time-delay fuze of electronics |
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| CN112198895A (en) * | 2020-08-03 | 2021-01-08 | 北京理工大学 | Guidance and guidance battle cooperation system based on unmanned aerial vehicle and control method |
| EP4200032A4 (en) * | 2020-08-20 | 2024-10-02 | Syler A Colaco | Fire suppression device |
| CN112197655A (en) * | 2020-09-25 | 2021-01-08 | 中国航天空气动力技术研究院 | Rolling control method and control device for rotating missile |
| CN112781890A (en) * | 2020-12-24 | 2021-05-11 | 中国飞行试验研究院 | Fire-fighting aircraft drop test ground adhesion density measurement method |
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