CN104074628B - Dynamic rocket propulsion - Google Patents
Dynamic rocket propulsion Download PDFInfo
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- CN104074628B CN104074628B CN201310097993.4A CN201310097993A CN104074628B CN 104074628 B CN104074628 B CN 104074628B CN 201310097993 A CN201310097993 A CN 201310097993A CN 104074628 B CN104074628 B CN 104074628B
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Abstract
The invention belongs to rocket field, be specifically related to dynamic rocket propulsion.Dynamic rocket propulsion provided by the invention, adopts solid fuel, and arranges control unit, thus makes to generate the Laval nozzle structure being suitable for rocket flight bottom described rocket body.Described control unit comprises rocket body shell, and when described solid fuel burning, shell lower edge can in company with the dynamic ablation consumption of the firing level of described solid fuel.Like this, in the flight course of rocket, can make bottom described rocket body, dynamically to generate the nozzle structure being suitable for rocket flight, and the Litter produced is sprayed by described nozzle structure as the working medium of booster rocket flight in fact, the unnecessary weight of rocket can be abandoned timely, do not produce the Litter that volume is larger, thus improve the degrees of freedom of rocket flight path design.
Description
Technical field
The invention belongs to rocket field, be specifically related to dynamic rocket propulsion.
Background technique
Rocket sprays backward at a high speed with hot air flow, utilizes the proal jet-propulsion plant of reaction force produced.Its self-contained incendiary agent and oxygenant, does not rely on the oxygen and aiding combustion in air, both can in an atmosphere, again can in outer-space flight.Modern rocket can be used as quick long distance transportation instrument, can be used for launching an artificial satellite and deliver weapon warhead (as bullet).
On the whole traditional rocket is gone up and is made up of rocket envelope, fuel, motor etc.The effect of rocket envelope is protection rocket inner member and supports rocket.The energy produced during rocket fuel burning provides power for rocket flight.The burning of engine control fuel and the injection of flame.
Due to the progressively consumption of fuel in rocket flight process, originally the shell charged progressively can become empty, and unnecessary ghost for the propelling of rocket without any meaning, and will the excess weight carried in rocket flight process be become, therefore for reducing the weight of whole rocket, normally ghost is aloft directly abandoned.Existing way is that rocket is made multistage rocket, and every grade of rocket is all equipped with motor, and the fuel being often finished one-stage rocket just abandons the ghost of one-stage rocket.
Therefore, only consider from abandoning excess weight angle, rocket should manufacture infinitely multistage, accomplishes to try one's best to abandon excess weight timely.But the complexity of the more rockets of rocket progression is larger, and every one-level all will have the motor of oneself, gains in weight so on the contrary, so rocket progression can not be too many.Existing rocket progression is no more than three grades usually.So existing rocket can not accomplish at the right time abandon excess weight.
In addition, the shell that rocket abandons may pound people or the thing on ground, and therefore causing abandoning place can not choose at random, and therefore also can produce restriction to the flight path of rocket to a certain extent.
Existing rocket motor controls fuel combustion and sprays for rocket provides power.The chief component combuster of motor, nozzle.Then fuel produce power by nozzle ejection in firing chamber combustion.Firing chamber and nozzle are all make with high temperature resistant, high-strength material.Sometimes these two parts are also equipped with cooling unit, are not at high temperature burnt to protect this mechanism.It has the following disadvantages: one, and motor needs employing high temperature resistant and the material of high strength is made, and causes the manufacture cost of motor higher like this; Its two, motor as a constituent element of rocket, every one-stage rocket all needs be equipped with motor, because the weight of motor itself is usually heavier, therefore the setting of motor is also in the weight of the whole rocket objectively increased the weight of; Its three, owing to being limited to the temperature capacity of engine material, in-engine flame temperature can not be too high, is unfavorable for the thrust power improving whole rocket like this; Its four, the complex structure of motor, especially liquid-fuel rocket, the many and easy leak liquid of engine pipeline, very easily causes danger; Its five, engine jet pipe opening can not regulate openings of sizes along with ambient pressure usually, make motor lose efficiency.
Summary of the invention
Technical problem to be solved by this invention is to provide dynamic rocket propulsion, uses and reduces following problem:
1, to produce Litter volume excessive and cannot abandon the unnecessary weight of rocket in time for existing rocket;
2, manufacture cost is too high;
3, fuel energy utilization ratio is low.
Dynamic rocket propulsion provided by the invention is achieved in that
Dynamic rocket propulsion, comprise rocket body, fill solid fuel in described rocket body and described rocket body is provided with and dynamically makes to generate the control unit being suitable for the Laval nozzle structure of rocket flight bottom described rocket body in company with during solid fuel burning, described control unit comprises the described solid fuel of parcel and its edge, lower end can in company with the shell of the dynamic ablation consumption of the burning of described solid fuel when described solid fuel burning.
Particularly, be provided with some electrodes in described rocket body and control the discharge control system of each described electrode discharge state and/or the cooling channel of at least one injection freezing mixture.
Particularly, described shell is the memory shell be made up of shape-memory material, and the cross sectional area of described memory shell memory is less than the cross sectional area of described rocket body.
Particularly, the inside that described memory case surface is provided with horizontal cut and/or forms described memory sheathing material is provided with traverse fiber material.
Particularly, described control unit also comprises to be located in described rocket body and the tubular member be made up of memory material, and the cross sectional area of described tubular member memory is greater than the cross sectional area of tubular member.
Particularly, described tubular member surface is provided with horizontal cut and/or its material internal is provided with traverse fiber material.
Particularly, described control unit also comprises the jet pipe generation component of the below being located at the inner solid fuel of described rocket body; Described jet pipe generate in component run through from top to bottom have at least one bar shaped as the first passage of Laval nozzle and/or as described in jet pipe generate component outer wall and outer casing inner wall forms the second channel of shape as Laval nozzle jointly.
Particularly, described dynamic rocket propulsion inside is provided with and connects the traction climbing device that described jet pipe generates component.
Particularly, described jet pipe generates in component and is provided with cooling unit, and described jet pipe generation component surface is provided with the cooling material be communicated with described cooling unit and exports.
Beneficial effect of the present invention is: dynamic rocket propulsion provided by the invention, adopts solid fuel, and arranges control unit, thus makes to generate the Laval nozzle structure being suitable for rocket flight bottom described rocket body.Described control unit comprises rocket body shell, and when described solid fuel burning, shell lower edge can in company with the dynamic ablation consumption of the firing level of described solid fuel.Like this, in the flight course of rocket, can make bottom described rocket body, dynamically to generate the Laval nozzle structure being suitable for rocket flight, and the Litter produced is sprayed by described Laval nozzle structure as the working medium of booster rocket flight in fact, the unnecessary weight of rocket can be abandoned timely, do not produce the Litter that volume is larger, thus improve the degrees of freedom of rocket flight path design.In addition, because this propeller structure is simple, so can manufacture cost be reduced.Because propulsion device is operationally by the part of shell as jet pipe, so this propulsion device easily generates larger-size Laval nozzle structure, and larger Laval nozzle structure is conducive to the energy utilization efficiency improving fuel.
Accompanying drawing explanation
Fig. 1 is the structural representation of dynamic rocket propulsion embodiment one provided by the invention;
Fig. 2 is the structural representation of dynamic rocket propulsion embodiment two provided by the invention;
Fig. 3 is the structural representation of dynamic rocket propulsion embodiment three provided by the invention.
Embodiment
In order to make technical problem to be solved by this invention, technological scheme and beneficial effect clearly understand, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
embodiment one
Please refer to Fig. 1, dynamic rocket propulsion, comprise rocket body, fill solid fuel 1a in described rocket body and described rocket body is provided with and dynamically makes to generate the control unit 2a being suitable for the Laval nozzle structure 3a of rocket flight bottom described rocket body in company with during solid fuel 1a burning, described control unit 2a comprises the described solid fuel of parcel and its edge, lower end can in company with the shell 21a of the dynamic ablation consumption of the burning of described solid fuel when described solid fuel burning.
Dynamic rocket propulsion provided by the invention, adopt inner rocket body of filling solid fuel 1a, and control unit 2a is set on described solid fuel 1a, thus make to generate bottom described rocket body to be suitable for the nozzle structure 3a of rocket flight, be also provided with the described solid fuel 1a of parcel in the surface of described solid fuel 1a and its lower edge can in company with the shell 21a of described rocket body together ablation when described solid fuel 1a burning simultaneously.Like this, in the flight course of rocket, can make bottom described solid fuel 1a, dynamically to generate the nozzle structure 3a being suitable for rocket flight, and the Litter produced is sprayed by described nozzle structure 3a as the working medium of booster rocket flight in fact, the unnecessary weight of rocket can be abandoned timely, do not produce the Litter that volume is larger, thus improve the degrees of freedom of rocket flight path design.
In the present embodiment, be provided with some electrode 5a in described solid fuel 1a and control the discharge control system of each described electrode 5a discharge condition and/or the cooling channel 6a of at least one injection freezing mixture 7a.Here, controlled the velocity of combustion of described solid fuel 1a by the discharge condition of cooling channel 6a injection freezing mixture 7a and control electrode 5a, and then reach the object regulating firing level 4a shape.When velocity of combustion is too fast, by strengthening the injection amount of freezing mixture 7a, reaching and described firing level 4a cooling is even extinguished.Described electrode 5a to described firing level 4a lower end radiation electric arc, thus can accelerate the burning of solid fuel on described firing level 4a, or accelerates the velocity of combustion of some special position, or lights solid fuel.In addition, the freezing mixture 7a that the gaseous environment needed for described electrode 5a electric discharge can be injected by described cooling channel 6a gasifies and provide.In addition, it is to be noted, the cooling channel 6a that the present invention adopts and electrode 5a is all can in company with the dynamic ablation of propelling of firing level 4a on described solid fuel 1a, and the gas that cooling channel 6a, electrode 5a and the freezing mixture 7a that injected by cooling channel 6a produce after gasifying all can be sprayed by described nozzle structure 3a in company with the gas produced described in solid fuel 1a combustion gasification together, that is the gas produced after described cooling channel 6a, electrode 5a and the freezing mixture 7a injected by cooling channel 6a gasify should be considered as a part for the working medium promoting rocket flight.More specifically, described electrode 5a and cooling channel 6a all along the axial direction of described solid fuel 1a and be parallel to described solid fuel 1a axis arrange.In addition, in the present embodiment, also by the mechanical strength of each described electrode 5a of suitable enhancing, thus the mechanical strength of described solid fuel 1a is strengthened.
In addition, by increasing the inductance detection equipment of the described electrode 5a inductance of detection on described rocket body, thus learn the length of electrode, and then converse the surplus of solid fuel 1a.By detecting the resistance detection equipment of the resistance of described electrode 5a, thus learn the temperature of flame combustion, so converse solid fuel 1a burn speed and this rocket propulsion whether shut down.
In addition, by controlling the distance of liquid level apart from described firing level 4a of freezing mixture 7a on described cooling channel 6a, the size of described firing level 4a is regulated and controled.Specifically such, when described freezing mixture 7a is far away apart from described firing level 4a, burning flame on described firing level 4a by lighting, described cooling channel 6a does not have the part of freezing mixture 7a, in this case, described cooling channel 6a does not have the part of freezing mixture 7a also become a part of described firing level 4a, thus the Area comparison making described firing level 4a total is large.Therefore, by adjusting described freezing mixture 7a apart from described firing level 4a distance, the area of described firing level 4a can be regulated.
In an embodiment, described shell 21a is the memory shell be made up of shape-memory material, and the cross sectional area of described memory shell memory is less than the cross sectional area of described solid fuel 1a.The concrete production method of described memory shell can be as follows: first make described memory shell remember the shape that a cross section is less relative to the cross section of described solid fuel 1a, again the cross section of described memory shell is expanded into the structure can wrapping up described solid fuel 1a, thus completes the process that memory shell is set on described solid fuel 1a.
The shape-memory material that the described memory shell of above-mentioned making adopts can be memory alloy or macromolecule material contracting with heat.Make the shell of described solid fuel 1a of shape-memory material, this material is that the structural material of rocket body provides mechanical support for rocket body, and this material also dynamically generates Laval nozzle structure simultaneously, is also consumable material simultaneously, is also a kind of propulsive working medium simultaneously.
Wherein, the one in described memory alloy is following formula Au-Cd, Ag-Cd, Cu-Zn, Cu-Zn-Al, Cu-Zn-Sn, Cu-Zn-Si, Cu-Sn, Cu-Zn-Ga, In-Ti, Au-Cu-Zn, NiAl, Fe-Pt, Ti-Ni, Ti-Ni-Pd, Ti-Nb, U-Nb and Fe-Mn-Si.Described macromolecule material contracting with heat also known as polymer shape memory material, to be macromolecular material with radiation processing technology the intersect a kind of intelligent material combined.Common high molecular materials is as the normally linear structure such as polyethylene, PVC＝polyvinyl chloride, after the radiation effects of the radioactive sources such as electron accelerator becomes reticular structure, these materials will possess unique " memory effect ", and the material of expansion, cooling and shaping again can shrink and return to the original form after being heated.The memory performance of material contracting with heat can be used for making heat-shrinkable pipe, film material and special section; key property is that heat shrink is coated on external surface of objects; the effect such as can play insulation, protection against the tide, seal, protect and continue, the radial shrinkage ratio of necked material can reach 50% ~ 80%.
Rocket in flight course, the solid fuel on described solid fuel 1a by bottom it along with its firing level 4a gradually on move, the Laval nozzle structure that described memory shell will be conventional in dynamic formation rocket nozzle.Many described known, Laval nozzle is made up of three parts, and the trunnion 32a being respectively collapsible tube 31a, expanding duct 33a and connection collapsible tube 31a and expanding duct 33a forms.
Introduce the process that described memory shell forms each pipeline section of Laval nozzle structure below.Due to the difference of described memory shell various piece heated time, from described firing level 4a more away from the portion temperature of memory shell higher, from described firing level 4a more close to the portion temperature of memory shell lower.The memory housing parts nearer apart from firing level is heated and carries out shrinking and forming described collapsible tube 31a; Distance firing level is comparatively far away and to connect the memory housing parts heated time of described collapsible tube 31a more relative to described collapsible tube 31a heated time, forms described trunnion 32a in fully shrinking; Farther and the memory housing parts connecting described trunnion 32a of distance firing level due to heated time longer, in soft state, and the impact of the pressure of pressurized gas produced due to the working medium that is subject to described firing level 4a burns, the memory shell of this part will be expanded laterally thus form described expanding duct 33a.Therefore, in the present embodiment, in the process that described solid fuel 1a burns, described memory shell is along with the drive-in step of described solid fuel 1a firing level 4a, and its underpart will present Laval nozzle structure conventional in rocket nozzle structure.In addition, along with the propelling of described firing level 4a, described collapsible tube 31a will progressively become trunnion 32a, and described trunnion 32a progressively will become softening expanding duct 33a, and expanding duct 33a is along with the raising of its temperature, will start fusing or gasify and depart from described memory shell.As can be seen here, in the present embodiment, in the combustion process of described solid fuel 1a, memory shell on it is by dynamic formation Laval nozzle structure, and the memory shell that memory material is made can be formed and dynamic burnout dynamically along with the propelling of firing level 4a described on described solid fuel 1a, the Litter not having volume larger in whole combustion process all the time occurs.
In order to prevent occurring in ablation process that the ablation of described enlarged portion 33a end is uneven because of described memory shell and cause the Laval nozzle structure of generation not good, further improve as the present embodiment, described memory case surface is provided with horizontal cut and/or described memory sheathing material inside is provided with traverse fiber material.Like this, the ablation of described memory shell can be made more even.
In addition, further improve as the present embodiment, described solid fuel 1a center is provided with a stick-like or tubular element 22a.Because the cross sectional area of described trunnion 32a is less, and described stick-like or tubular element 22a occupy described trunnion 32a cross sectional area comparatively greatly, can be reduced by the breathing area of described trunnion 32a, make by the air-flow of trunnion 32a faster.Like this, effectively can reduce the contractility needed for memory material making described memory shell, thus reduce the manufacture difficulty of described memory shell.
In the present embodiment, dynamically generate and burn Laval nozzle structure tool and have the following advantages:
1, the memory shell adopting memory material to be made reduces the heat resistant requirements of memory material.
In the present embodiment, dynamic rocket propulsion dynamic in flight course generates firing chamber.When described burning room temperature high pressure is large, described memory shell is by melted by heat or gasification within a short period of time, and now described Laval nozzle structure is the shorter and trunnion 32a comparatively tubbiness of entirety.Otherwise when described burning room temperature low-pressure hour, described Laval nozzle structure will be longer and trunnion 32a is elongated in entirety.Meanwhile, the form of Laval nozzle structure also has impact to temperature in described firing chamber 4a, discharges resistance greatly compared with long Laval nozzle structure and its gas of elongated throat tubular construction, thus is conducive to improving chamber temperature.It is little that short Laval nozzle structure and tubbiness throat tubular construction gas discharge resistance, and be conducive to reducing chamber temperature, low chamber temperature is conducive to protection Laval nozzle structure, thus reduces the requirement to the memory shell heat resistance forming Laval nozzle structure.
2, its trunnion of the Laval nozzle structure 32a openings of sizes self adaption dynamically generated, is conducive to improving kinetic transformation rate.
In the present embodiment, whole Laval nozzle structure dynamics generates.Ambient pressure is the key factor affecting described nozzle structure 3a openings of sizes.When rocket is in low-latitude flying, because ambient pressure is comparatively large, by making, the opening of described nozzle structure 3a is less, will described nozzle structure 3a be made to spray the higher gas of pressure like this.When rocket is in high-altitude flight, ambient pressure is little, and described nozzle structure 3a is subject to less ambient pressure, and its opening is comparatively large, will described nozzle structure 3a be made to spray the lower gas of pressure like this.As can be seen here, the structural described nozzle structure 3a openings of sizes of Laval nozzle dynamically generated in the present embodiment can regulate the output state of its kinetic energy automatically according to ambient pressure, is conducive to the conversion ratio improving kinetic energy.
3, remember shell gasification and produce kinetic energy, improve the kinetic transformation rate of burning working medium.
Some or all ofly when shell is ablated be vaporized, gas produces kinetic energy from the ejection of rocket body afterbody.This part kinetic energy is actual is that the using waste heat from tail gas of rocket is transformed, and is equivalent to improve rocket flame kinetic transformation rate.
4, make the structure of whole rocket propulsion simple, cost is low, safe and reliable.
Because the dynamic rocket propulsion each several part of the present embodiment bears several functions all as far as possible, thus its structure becomes simple, and the simple favourable reduction manufacture cost of structure, and appearance foozle between various piece and the probability that affects whole performance declines, thus improve its Security.
5, rocket vibrations are little
Rocket vibrations are mainly from the rough burning of fuel in combustion chamber, and excessive vibrations easily affect the Security of rocket and affect the safety of people or the thing transported.In the present embodiment, in the flight course of rocket, because described memory shell is in the condition of high temperature, its Laval nozzle structure formed is in a more soft state or elastomeric rubbery state, and this state can effective damping vibration.In addition, some solid fuel itself is also rubber-like high elasticity material, and itself also has damping vibration ability.
6, generate large jet pipe, improve rocket kinetic transformation rate
Existing rocket, due to reasons such as jet pipe weight and manufacturing process, can not produce larger-size jet pipe, make rocket kinetic energy conversion ratio not high.With the dynamic rocket propulsion that the present embodiment provides, rocket nozzle can be generated by described shell 21a, and can generate the larger jet pipe of volume, is conducive to more exhaust heat-energies to be converted to kinetic energy.
embodiment two
Please refer to Fig. 2, the present embodiment is relative to embodiment one, and its difference is, the set-up mode of control unit is different.In the present embodiment, described control unit 2b comprises the described solid fuel of parcel and the shell 21b that its edge, lower end can consume in company with the dynamic ablation of the burning of described solid fuel when described solid fuel 1b burns, also comprise and being located in described rocket body and the tubular member 22b be made up of memory material, the cross sectional area that described tubular member 22b remembers is greater than the cross sectional area of tubular member 22b.When the solid fuel 1b on described rocket body burns, the passing along with firing level 4b is recovered original memory cross section by described tubular member 22b gradually, and beginning its underpart forms the swelling state of larger sectional area.Like this, described tubular member 22b will together form Laval nozzle structure with described shell 21b.
It is pointed out that in the present embodiment, described shell 21b also can adopt memory material to make, so that generate described Laval nozzle structure.Certainly, in the present embodiment, with to remember shell described in embodiment one similar, described tubular member 22b surface is provided with horizontal cut and/or its material internal is provided with traverse fiber material.Like this, described tubular member 22b ablation can be made more even.
embodiment three
Please refer to Fig. 3, the present embodiment is relative to embodiment one or implement two, and its difference is: the set-up mode of control unit is different.In the present embodiment, described control unit 2c comprises the described solid fuel of parcel and the shell 21c that its edge, lower end can consume in company with the dynamic ablation of the burning of described solid fuel 1c when described solid fuel 1c burns, and also comprises the jet pipe be located at below the inner solid fuel 1c of described rocket body and generates component 22c; Described jet pipe generate in component 22c run through from top to bottom have at least one bar shaped as the first passage 221c of Laval nozzle and/or as described in jet pipe generate component 22c outer wall and as described in shell 21c inwall jointly form the second channel 222c of shape as Laval nozzle.Like this, in the flight course of rocket, the gas produced in described solid fuel 1c combustion process sprays by shape first passage 221c and/or second channel 222c as described in Laval nozzle.
Further improve as the present embodiment, described dynamic rocket propulsion inside is provided with and connects the traction climbing device 23c that described jet pipe generates component 22c.Along with the consumption of described solid fuel 1c, firing level 4c moves, it is up that described traction climbing device 23c draws described jet pipe generation component 22c, thus ensure that Laval nozzle structure is positioned at the bottom of described rocket body all the time.
Further, described jet pipe generates in component 22c and is provided with cooling unit, and described jet pipe generation component 22c surface is provided with the cooling material be communicated with described cooling unit and exports.
Introduce the working principle of the present embodiment below:
In the flight course of rocket, the gas that on described firing level 4c, burning generates generates component 2c through described jet pipe, and the area passed through due to gas is herein less, and the speed of gas by rising sharply, and exceedes velocity of sound.The gas continuation exceeding velocity of sound is the part continuation acceleration generation thrust of the lower end of expansion to described shell 21c.Along with solid-fuelled consumption on described solid fuel 1c, firing level 4c moves, it is up that described traction climbing device 23c draws described jet pipe generation component 22c.Meanwhile, described shell 21c lower end is also consumed by tail gas ablation simultaneously gradually.In addition, the cooling liquid of described cooling unit can be stored in described jet pipe generation component 22c or by conveyance conduit and come from the conveying of rocket leading portion.Wherein, cooling liquid can be discharged from described cooling material outlet by the gas generated after thermal evaporation, also can provide the partial power of rocket flight.
In addition, it is pointed out that in the present embodiment, the control mode of electrode and the cooling channel addressed in embodiment one also can be set on described solid fuel 1c; The design also can addressed in similar embodiment one, arranges horizontal cut on the housing and/or described sheathing material inside is provided with traverse fiber material, and therefore not to repeat here.
In addition, in the present embodiment, described shell 21c also can adopt memory material to be made, and the internal diameter of memory material memory is greater than the external diameter of described solid fuel 1c.Like this, in the flight course of rocket, along with the passing of described firing level 4c, the lower end of described shell 21c will expand automatically, thus form the expansion pipeline section being beneficial to spout and being formed.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, all any amendments done within the spirit and principles in the present invention, equivalent replacement and improvement etc., all should be included within protection scope of the present invention.
Claims (8)
1. dynamic rocket propulsion, comprise rocket body, fill solid fuel in described rocket body and described rocket body is provided with and dynamically makes to generate the control unit being suitable for the Laval nozzle structure of rocket flight bottom described rocket body in company with during solid fuel burning, described control unit comprises the described solid fuel of parcel and the shell that its edge, lower end can consume in company with the dynamic ablation of the burning of described solid fuel when described solid fuel burning, described shell is the memory shell be made up of shape-memory material, and the cross sectional area of described memory shell memory is less than the cross sectional area of described rocket body.
2. dynamic rocket propulsion according to claim 1, is characterized in that: be provided with some electrodes in described rocket body and control the discharge control system of each described electrode discharge state and/or the cooling channel of at least one injection freezing mixture.
3. dynamic rocket propulsion according to claim 1 and 2, is characterized in that: the inside that described memory case surface is provided with horizontal cut and/or forms described memory sheathing material is provided with traverse fiber material.
4. dynamic rocket propulsion according to claim 1 and 2, it is characterized in that: described control unit also comprises to be located in described rocket body and the tubular member be made up of memory material, the cross sectional area of described tubular member memory is greater than the cross sectional area of tubular member.
5. dynamic rocket propulsion according to claim 4, is characterized in that: described tubular member surface is provided with horizontal cut and/or its material internal is provided with traverse fiber material.
6. dynamic rocket propulsion according to claim 1, is characterized in that: the jet pipe that described control unit also comprises the below being located at the inner solid fuel of described rocket body generates component; Described jet pipe generate in component run through from top to bottom have at least one bar shaped as the first passage of Laval nozzle and/or as described in jet pipe generate component outer wall and outer casing inner wall forms the second channel of shape as Laval nozzle jointly.
7. dynamic rocket propulsion according to claim 6, is characterized in that: described dynamic rocket propulsion inside is provided with and connects the traction climbing device that described jet pipe generates component.
8. dynamic rocket propulsion according to claim 6, is characterized in that: described jet pipe generates in component and is provided with cooling unit, and described jet pipe generation component surface is provided with the cooling material be communicated with described cooling unit and exports.
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| CN201310097993.4A CN104074628B (en) | 2013-03-25 | 2013-03-25 | Dynamic rocket propulsion |
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| CN201310097993.4A CN104074628B (en) | 2013-03-25 | 2013-03-25 | Dynamic rocket propulsion |
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| CN104074628B true CN104074628B (en) | 2016-02-24 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4574700A (en) * | 1984-11-15 | 1986-03-11 | The United States Of America As Represented By The Secretary Of The Air Force | Solid rocket motor with nozzle containing aromatic amide fibers |
| US4936092A (en) * | 1988-11-28 | 1990-06-26 | The United States Of America As Represented By The Secretary Of The Navy | Propellant grain design |
| US4981033A (en) * | 1990-05-04 | 1991-01-01 | Yang Lien C | Gage for rocket motor data acquisition |
| US7210282B1 (en) * | 2002-01-04 | 2007-05-01 | Floyd Brian A | Case burning rocket |
| CN101915182A (en) * | 2010-06-09 | 2010-12-15 | 北京航空航天大学 | Solid-propellant rocket engine |
| CN203201685U (en) * | 2013-03-25 | 2013-09-18 | 刘志伟 | Dynamic rocket booster |
-
2013
- 2013-03-25 CN CN201310097993.4A patent/CN104074628B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4574700A (en) * | 1984-11-15 | 1986-03-11 | The United States Of America As Represented By The Secretary Of The Air Force | Solid rocket motor with nozzle containing aromatic amide fibers |
| US4936092A (en) * | 1988-11-28 | 1990-06-26 | The United States Of America As Represented By The Secretary Of The Navy | Propellant grain design |
| US4981033A (en) * | 1990-05-04 | 1991-01-01 | Yang Lien C | Gage for rocket motor data acquisition |
| US7210282B1 (en) * | 2002-01-04 | 2007-05-01 | Floyd Brian A | Case burning rocket |
| CN101915182A (en) * | 2010-06-09 | 2010-12-15 | 北京航空航天大学 | Solid-propellant rocket engine |
| CN203201685U (en) * | 2013-03-25 | 2013-09-18 | 刘志伟 | Dynamic rocket booster |
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