CN106194502A - A kind of solid-liquid Attitude rocket engine - Google Patents
A kind of solid-liquid Attitude rocket engine Download PDFInfo
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- CN106194502A CN106194502A CN201610562147.9A CN201610562147A CN106194502A CN 106194502 A CN106194502 A CN 106194502A CN 201610562147 A CN201610562147 A CN 201610562147A CN 106194502 A CN106194502 A CN 106194502A
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- electromagnetic valve
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
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Abstract
The open a kind of solid-liquid Attitude rocket engine of the present invention, including: oxidant delivery system, direct-acting electromagnetic valve, honeycomb fashion catalytic bed, combustor and jet pipe.Induction system uses nitrogen squash type supply hydrogen peroxide, direct-acting electromagnetic valve control the quantity delivered of hydrogen peroxide so that solid-liquid attitude control engine can quickly respond；Using the catalysis of honeycomb fashion catalytic bed, oxidant decomposes generation high-temperature oxygen, enters combustor by spray panel；Having 6 passages in the middle of end-burning grain, high-temperature oxygen arrives powder column section through these passages, and the product 13 butadiene generation combustion reaction decomposed with HTPB, electromotor is started working.The present invention uses working in double modes, has had single constituent element attitude control engine simple in construction, reliability height and double elements attitude control engine ratio concurrently and has leapt high, switchs rapid advantage；And simple in construction, low cost, safety is good, the feature of environmental protection is good.
Description
Technical field
The invention belongs to rocket engine design field, relate to a kind of rocket engine, specifically a kind of solid-liquid appearance
Control rocket engine, carries out the gesture stability of spacecraft as a kind of accessory power system.
Background technology
Solid-liquid rocket uses liquid oxidizer and solid fuel, structure has had both liquid-propellant rocket engine with solid
The common feature of body rocket engine, has that safety is good, it is good, easy easily to carry out thrust regulation, powder column good stability, the feature of environmental protection
Shutdown and restart, the advantage such as good economy performance, can be used for the fields such as sounding rocket, rail control electromotor, Variable Thrust Engine.
Meanwhile, solid-liquid rocket there is also that loading density is low, efficiency of combustion is low, oxygen combustion is than lacking of changing
Point.
Hydrogen peroxide is used as the oxidant of solid-liquid rocket, has nontoxic, pollution-free, high density, easily storage, decomposes
Produce the advantage such as big volumetric expansion and heat, be a kind of preferably green propellant.Solid-liquid rocket and hydrogen peroxide
Oxidant with the use of conventional end hydroxy butadiene (HTPB), high density polyethylene (HDPE) (HDPE), lucite (PMMA) etc..
Current single constituent element attitude control engine mainly uses Hydrazine fuel catalytic decomposition, but specific thrust is low, and catalyst comes
Source is limited and it needs to preheat head；The propellant of double elements attitude control engine is limited to hydrazine and N2O4, and structure is multiple
Miscellaneous.
The ignition schemes that hydrogen peroxide solid-liquid rocket is conventional has: catalytic ignition, and solid medicine box is lighted a fire, and sprays into spontaneous combustion
Oxidant is lighted a fire, and igniter motor is lighted a fire.Wherein, solid medicine box ignition security is poor, and it is anti-that medicine box does heat at the indoor needs of front combustion
Protecting, medicine box metal part easily comes off and jet pipe causes potential danger；Suck spontaneous combustion oxidation agent ignition system complicated, need volume
Outer oxidant supply system；Igniter motor igniting easily produces igniting superpressure, and during igniting, temperature is too high.
Summary of the invention
In order to solve the problems referred to above, patent of the present invention proposes a kind of simple in construction, low cost, safety is good, the feature of environmental protection is good
End combustion powder charge solid-liquid Attitude rocket engine, including a kind of solid-liquid Attitude rocket engine, it is characterised in that: include electromagnetism
Valve, catalytic bed, combustor and jet pipe, the most coaxially connect composition；Oxidant is supplied by induction system.
Described electromagnetic valve includes electromagnetic valve body, armature, Venturi tube, base, solenoid and spring.Wherein, electromagnetic valve
Valve rear end end is provided with base；And fluting is wound around solenoid in electromagnetic valve body outer wall circumference.After electromagnetic valve body
Portion is designed with armature cavity volume, and inside arranges armature.Electromagnetic valve body front portion is designed with the oxidant channel connected with armature cavity volume
A, oxidant channel A is internally installed Venturi tube.It is provided with spring between armature front end face and electromagnetic valve body.Base front portion has
Powder column chamber, powder column intracavity portion is provided with annular powder column.Base rear portion has oxidant channel B.Circumference it is also devised with all in armature
The oxidant channel C of cloth.Above-mentioned oxidant channel A, oxidant channel B connect composition oxidant paths with oxidant channel C.Rank
Ferrum back end design has seal head；During solenoid energising, make seal head withstand on base, by oxidant channel B leading section, block
Oxidant supply passageway.
Described catalytic bed is cellular structure, including catalytic bed housing, liquid homogenizing plate, gas injection panel and catalysis
Net.Catalytic bed enclosure interior front end and rear end are respectively mounted liquid homogenizing plate and gas injection panel, liquid homogenizing plate and gas
Catalysis net is installed between spray panel.
The high silica passage of through powder column front/rear end is uniformly offered in the middle part circumference of powder column in described combustor, high
It is coated with by high silica in silica vias inner walls and powder column front end face.
It is an advantage of the current invention that:
1, solid-liquid Attitude rocket engine of the present invention, uses working in double modes, has had single constituent element attitude control engine structure concurrently
Simply, reliability is high and double elements attitude control engine ratio is leapt high, switched rapid advantage；
2, solid-liquid Attitude rocket engine of the present invention, on powder charge designs, uses cigarette burning powder charge medicine shape, can improve
The filling mark of powder column, reduce the slenderness ratio of electromotor, maintain stablizing of oxygen combustion ratio in combustion process, and can reduce and start
The remaining medicine quality of machine；
3, solid-liquid Attitude rocket engine of the present invention, induction system employing two set gas cylinder tanks are as Redundancy Design, permissible
The reliability of raising system；
4, solid-liquid Attitude rocket engine of the present invention, use high-strength hydrogen peroxide and HTPB as propellant, HTPB with
Ethylene propylene diene rubber is directly cast in combustor, and structure is reliable, the feature of environmental protection good；
5, solid-liquid Attitude rocket engine of the present invention, in engine working process, keeps the state of cigarette burning, due to
Combustion zone easily realizes away from catalytic bed and valve, thermal protection；
6, solid-liquid Attitude rocket engine of the present invention, solid-liquid rocket end face fuel when oxidizer flow rate is fixed,
Fuel flow rate does not changes, it is to avoid the Specific Impulse Loss that oxygen combustion causes than change；
7, solid-liquid Attitude rocket engine of the present invention, the flow of solid-liquid rocket fuel along with oxidant change and
Change, it is easy to realized the regulation of motor power by regulation oxidizer flow rate.
Accompanying drawing explanation
Fig. 1 is solid-liquid Attitude rocket engine overall structure schematic diagram of the present invention；
Fig. 2 is electromagnetic valve structure schematic diagram in solid-liquid Attitude rocket engine of the present invention；
Fig. 3 is catalytic bed structural representation in solid-liquid Attitude rocket engine of the present invention；
Fig. 4 is chamber structure schematic diagram in solid-liquid Attitude rocket engine of the present invention.
Fig. 5 is solid-liquid Attitude rocket engine hydrogen peroxide induction system structural representation of the present invention.
In figure:
1-electromagnetic valve 2-catalytic bed 3-combustor
4-jet pipe 5-induction system 101-electromagnetic valve body
102-armature 103-Venturi tube 104-base
105-solenoid 106-case 107-spring
108-oxidant channel A 109-oxidant channel B 110-oxidant channel C
111-seal head 201-catalytic bed housing 202-liquid homogenizing plate
203-gas injection panel 204-catalysis net 301-burning chamber shell
Hands valve is released in the inflation of 302-heat insulation layer 303-powder column 501-helium
502-helium tank 503-throttle solenoid valve 504-hydrogen peroxide tank
505-relief valve 506-isolation solenoid valve
Specific embodiments
Below in conjunction with the accompanying drawings patent of the present invention is described further.
Patent of the present invention proposes a kind of solid-liquid Attitude rocket engine, for electromagnetic valve 1, catalytic bed 2, combustor 3 and jet pipe 4
The most coaxially connect composition, and uses induction system 5 to supply oxidant, as shown in Figure 1.
Described electromagnetic valve 1 is direct-acting electromagnetic valve, including electromagnetic valve body 101, armature 102, Venturi tube 103, base
104, solenoid 105, case 106 and spring 107, as shown in Figure 2.Wherein, electromagnetic valve body 101 is column structure, rear end
End is provided with base 104；And slot in electromagnetic valve body 101 outer wall circumference, it is wound with solenoid 105, electromagnetic wire in groove
Circle 105 is sealed by the case 106 of suit on electromagnetic valve body 101 outer wall.The rear portion coaxial design of electromagnetic valve body 101 has rank
Ferrum cavity volume, is coaxially arranged with the armature 102 of column magnetically soft alloy 1J50 material in armature cavity volume, and armature 102 and electromagnetic valve valve
Fluororubber O-type ring is used to seal between body 101, it is ensured that electromagnetic valve 1 and the compatibility of medium.Electromagnetic valve body 101 is anterior
Coaxial design has the oxidant channel A108 connected with armature cavity volume, oxidant channel A108 interior forward end to be coaxially installed with Wen
Pipe 103, fluid (oxidant) is entered by oxidant channel A108 front end, Venturi tube 103 fluid flow is controlled.Oxidation
Agent passage A108 back end design is enlarged diameter section cavity, collectively forms bullet with the perforate of coaxial design in armature 102 front end surface
Spring chamber, is internally provided with spring 107, and the front end of spring 107 is positioned by shoulder in stretching into enlarged diameter section；The rear end of spring 107
Stretch into perforate inner position.Base 104 front portion has powder column chamber, and powder column chamber connects with armature cavity volume, and powder column intracavity portion is provided with ring
Shape powder column 110；Base 104 rear portion has and connects oxidant channel B109 with powder column chamber.It is also devised with circumference in above-mentioned armature 102
Uniform n bar oxidant channel C110, n >=2, and the front end of n bar oxidant channel C110 connect with spring cavity after collecting connection,
N bar oxidant channel C110 rear end connects with powder column chamber；From there through oxidant channel A108, oxidant channel B109 and oxidation
Agent channel C 110 collectively forms oxidant paths, the most oxidized dose of passage A108 of fluid, spring cavity, oxidant channel B109,
After powder column chamber, oxidant channel C110, enter catalytic bed 2.End, armature 102 rear end coaxial design has seal head 111；It is not powered on
Time, armature 102 under spring force, makes seal head withstand on base 104, and by oxidant channel B109 leading section, by
This blocks oxidant supply passageway；Now electromagnetic valve 1 is closed.After energising, in the effect of solenoid 105 magnetic field force
Under, armature 102, by the attraction of electromagnetic valve body 101, overcomes spring force, armature 102 to move forward, now, seal head 111 with
Base 104 separates, and turns on oxidant supply passageway, makes fluid enter oxidant channel C110, and by the outlet stream of electromagnetic valve 1
Go out.After power-off, magnetic force disappears, and makes armature 102 return to initial position by spring force, blocks oxidant supply passageway, electromagnetism
Valve 1 is closed.Above-mentioned electromagnetic valve 1 acts on the side of seal head 111 due to fluid pressure, therefore Packing spring power, opens
Open electromagnetic force influenced by fluid pressure less.In the present invention, electromagnetic valve body 101 uses rustless steel 1Cr18NI9Ti and soft magnetism
After alloy 1J50 welding, polish forms, and increases the magnetic force with armature 102 in the case of being energized,
Described catalytic bed 2 is cellular structure, including catalytic bed housing 201, liquid homogenizing plate 202, gas injection panel
203 with catalysis net 204, as it is shown on figure 3, all use stainless steel.Wherein, catalytic bed housing 201 is tubular structure, and front end has
There is joint, with the outlet of electromagnetic valve 1.Catalytic bed housing 201 interior forward end and rear end are coaxially installed with liquid current-sharing respectively
Plate 202 and gas injection panel 203, be provided with catalysis net 204 between liquid homogenizing plate 202 and gas injection panel 203.The present invention
Middle catalysis net 204 selects honeycomb type integer catalyzer bed, and the carrier of catalyst is cordierite honeycomb ceramic, the catalytic bed after optimization
2 start delay times can arrive 100ms.In the present invention, liquid homogenizing plate 202 uses shower nozzle type spray scheme, makes hydrogen peroxide uniform
Enter catalytic bed, make full use of catalytic bed 2 performance, avoid hot-spot to cause hydrogen peroxide to explode simultaneously.Thus, through electromagnetic valve
1 hydrogen peroxide flowed out, enters in catalytic bed housing 201, in the uniform spray of liquid homogenizing plate 202 to catalysis net 204, is urging
It is decomposed into the gentle oxygen of water under the effect of agent, and discharges substantial amounts of heat, produce high-temperature water vapor and the mixture of oxygen, and lead to
Cross after gas injection panel 204 makes catalysis high-temperature gas even into combustor 3.
Described combustor 3 includes burning chamber shell 301, heat insulation layer 302 and powder column 303, as shown in Figure 4.Wherein, combustor
Housing 301 uses stainless steel, front end to connect with catalytic bed housing 1 rear end.Burning chamber shell 301 is internally provided with powder column
303, powder column 303 uses end hydroxy butadiene (HTPB).On burning chamber shell 301 inwall, heat insulation layer 302, heat insulation layer are installed
302 use ethylene propylene diene rubber；And heat insulation layer take not uniform thickness design, thickness is gradually reduced to rear end by combustion chamber shell front end,
Thus can save the cost of material, and alleviate the quality of electromotor.Burning chamber shell 301 rear end and the spray of niobium tungsten alloy material
Between pipe 4 front end, the cooperation of circumference shoulder positions and fixes, and joint is provided with high silica heat-insulating shield 305, plays heat insulation effect.
Uniformly offering the high silica passage 304 of 6 through powder column 303 front/rear ends in the middle part of above-mentioned powder column 303 in circumference, high silica leads to
It is coated with by high silica on road 304 inwall and powder column 303 front end face, is possible to prevent in high silica passage 304 to produce side combustion, with
Time height silica dish still prevent heat disturbance and enter in catalytic bed 2.Thus, in entering combustor 3, high-temperature oxygen is by powder column 303
Front end face enters in high silica passage 304, flows into the afterburner formed between powder column 303 rear end and combustor 3 rear end, powder column 303
Decompose under the effect of high temperature, produce 1-3 butadiene (C4H8), in powder column 303 rear end face and oxygen generation combustion reaction, and protect
Holding the state of end combustion, final high-temperature fuel gas produces thrust by jet pipe 4 ejection.
Described conveyer device 5 uses helium squash type conveyer device, has two set gas cylinder tank induction systems 5, two set gas
The bottle defeated induction system of tank is mutually redundant, and all can realize the oxidant conveying of solid-liquid Attitude rocket engine, improve conveyer device
Reliability, as shown in Figure 5.Described gas cylinder tank induction system includes that hands valve 501, helium tank 502, throttling are released in helium inflation
Electromagnetic valve 503, hydrogen peroxide tank 504, relief valve 505 and isolation solenoid valve 506.Wherein, helium tank 502 top is by inflation
Pipeline connects helium inflation and releases hands valve 501, and helium is poured in helium tank 502 by loading line, releases hands by helium inflation
Valve 501 controls being filled with and releasing helium to helium tank 502.Pass through to be provided with between helium tank 502 and hydrogen peroxide tank 504 to contain
The pipeline of the throttle solenoid valve 503 of restricting orifice is connected；Pressure gauge P1 is installed on hydrogen peroxide tank 504, is used for gathering oxygen
Change pressure in cryostat hydrogen tank 504, according to pressure in hydrogen oxide tank 504, control throttle solenoid valve switch, and then maintain hydrogen peroxide
Pressure in tank 504 is steady.Connect also by pipeline on hydrogen oxide tank 504 and have relief valve 505, when hydrogen oxide tank 504
During superpressure, carry out pressure release by opening relief valve 505.It is connected with transfer pipeline bottom hydrogen peroxide tank 504, on transfer pipeline
Isolation solenoid valve 506 is installed, is used for controlling the break-make of transfer pipeline.Transfer pipeline in above-mentioned two set gas cylinder tank induction systems
Connected with the front end of oxidant channel A108 in electromagnetic valve body 101 by main pipe rail.Thus open when isolation solenoid valve 506
Time, the hydrogen peroxide in hydrogen peroxide tank 504 can enter in electromagnetic valve body 101.Bellows selected by above-mentioned hydrogen oxide tank 504
Tank, has the advantages such as emptying efficiency is high, the compatibility is good.
Claims (8)
1. a solid-liquid Attitude rocket engine, it is characterised in that: include electromagnetic valve, catalytic bed, combustor and jet pipe, by front extremely
The most coaxially connect composition；Oxidant is supplied by induction system；
Described electromagnetic valve includes electromagnetic valve body, armature, Venturi tube, base, solenoid and spring；Wherein, electromagnetic valve body
End, rear end is provided with base；And fluting is wound around solenoid in electromagnetic valve body outer wall circumference；The rear portion of electromagnetic valve body sets
In respect of armature cavity volume, inside arranges armature；Electromagnetic valve body front portion is designed with the oxidant channel A connected with armature cavity volume, oxygen
Agent passage A is internally installed Venturi tube；It is provided with spring between armature front end face and electromagnetic valve body；Base front portion has powder column
Chamber, powder column intracavity portion is provided with annular powder column；Base rear portion has oxidant channel B；Circumference it is also devised with all in above-mentioned armature
The oxidant channel C of cloth；Above-mentioned oxidant channel A, oxidant channel B connect composition oxidant paths with oxidant channel C；Rank
Ferrum back end design has seal head；During solenoid energising, make seal head withstand on base, by oxidant channel B leading section, block
Oxidant supply passageway；
Described catalytic bed is cellular structure, including catalytic bed housing, liquid homogenizing plate, gas injection panel and catalysis net；Urge
Change bed enclosure interior front end and be respectively mounted liquid homogenizing plate and gas injection panel, liquid homogenizing plate and gas injection face with rear end
Catalysis net is installed between plate；
The high silica passage of through powder column front/rear end, high silica is uniformly offered in the middle part circumference of powder column in described combustor
It is coated with by high silica in vias inner walls and powder column front end face.
2. a kind of solid-liquid Attitude rocket engine, it is characterised in that: it is provided with on burning chamber shell inwall
The heat insulation layer being gradually reduced from front to back.
3. a kind of solid-liquid Attitude rocket engine, it is characterised in that: before burning chamber shell rear end and jet pipe
End joint is provided with high silica heat-insulating shield.
4. a kind of solid-liquid Attitude rocket engine, it is characterised in that: catalysis net selects honeycomb type entirety to urge
Agent bed, the carrier of catalyst is cordierite honeycomb ceramic.
5. a kind of solid-liquid Attitude rocket engine, it is characterised in that: electromagnetic valve body uses rustless steel
After 1Cr18NI9Ti welds with magnetically soft alloy 1J50, polish forms.
6. a kind of solid-liquid Attitude rocket engine, it is characterised in that: powder column uses terminal hydroxy group polybutadiene
Alkene.
7. a kind of solid-liquid Attitude rocket engine, it is characterised in that: conveyer device uses helium squash type
Conveyer device, including helium inflation release hands valve, helium tank, containing restricting orifice electromagnetic valve, hydrogen peroxide tank, relief valve with every
From electromagnetic valve；Wherein, hands valve, helium tank and hydrogen peroxide tank are released by loading line connection helium inflation in helium tank top
Between be connected by being provided with pipeline containing restricting orifice electromagnetic valve；On hydrogen peroxide tank, Pressure gauge is installed；Hydrogen peroxide is store
Connect also by pipeline on case and have relief valve；Be connected with transfer pipeline bottom hydrogen peroxide tank, transfer pipeline is provided with every
From electromagnetic valve；Transfer pipeline connects with oxidant paths entrance in electromagnetic valve body.
8. a kind of solid-liquid Attitude rocket engine, it is characterised in that: induction system uses two sets, each other
Redundancy.
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| CN106837605A (en) * | 2017-02-23 | 2017-06-13 | 北京航空航天大学 | A kind of hydrogen peroxide propeller |
| CN106837610A (en) * | 2017-04-05 | 2017-06-13 | 北京航空航天大学 | A kind of close-coupled work long hours solid-liquid rocket catalysis bed structure |
| CN106870205A (en) * | 2017-01-19 | 2017-06-20 | 北京航空航天大学 | A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber |
| CN107218857A (en) * | 2017-08-03 | 2017-09-29 | 北京航空航天大学 | Micro missile |
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| CN108657465A (en) * | 2018-05-10 | 2018-10-16 | 北京航空航天大学 | It is a kind of take off vertically, the sub- In-Orbit Plane of horizontal landing |
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| CN108895921A (en) * | 2018-07-03 | 2018-11-27 | 北京航空航天大学 | Hydrogen peroxide attitude control system for solid-liquid hybrid power carrier rocket |
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| CN106870205A (en) * | 2017-01-19 | 2017-06-20 | 北京航空航天大学 | A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber |
| CN106837605A (en) * | 2017-02-23 | 2017-06-13 | 北京航空航天大学 | A kind of hydrogen peroxide propeller |
| CN106837610B (en) * | 2017-04-05 | 2019-08-06 | 北京航空航天大学 | A kind of close-coupled works long hours solid-liquid rocket catalysis bed structure |
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| CN108657465A (en) * | 2018-05-10 | 2018-10-16 | 北京航空航天大学 | It is a kind of take off vertically, the sub- In-Orbit Plane of horizontal landing |
| CN108869100A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | Separation pushes away solid-liquid rocket and rocket auxiliary braking system with counter |
| CN108895921A (en) * | 2018-07-03 | 2018-11-27 | 北京航空航天大学 | Hydrogen peroxide attitude control system for solid-liquid hybrid power carrier rocket |
| CN109099800A (en) * | 2018-08-22 | 2018-12-28 | 北京航空航天大学 | The triggering method of fire extinguisher bomb and fire extinguisher bomb |
| CN109184955A (en) * | 2018-09-18 | 2019-01-11 | 上海新力动力设备研究所 | A kind of nested structure of double combustion chamber's gas generator |
| CN110439708A (en) * | 2019-08-30 | 2019-11-12 | 南京理工大学 | A kind of part cladding without jet pipe propeller powder column |
| CN110439708B (en) * | 2019-08-30 | 2021-11-05 | 南京理工大学 | Partially-coated spray-pipe-free propeller explosive column |
| CN113090414A (en) * | 2020-01-08 | 2021-07-09 | 星河动力(北京)空间科技有限公司 | Attitude control engine |
| CN112392629A (en) * | 2021-01-04 | 2021-02-23 | 北京航空航天大学 | Solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft |
| CN113107710A (en) * | 2021-05-10 | 2021-07-13 | 苏州旗磐科技有限公司 | Low-thrust double-component attitude control engine |
| CN113107710B (en) * | 2021-05-10 | 2023-10-20 | 苏州旗磐科技有限公司 | Low-thrust double-component attitude control engine |
| CN113389658A (en) * | 2021-07-21 | 2021-09-14 | 北京航空航天大学 | Pin type self-adaptive variable-thrust solid-liquid rocket engine head structure |
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| CN106194502B (en) | 2018-03-02 |
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