CN106121864A - A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket - Google Patents
A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket Download PDFInfo
- Publication number
- CN106121864A CN106121864A CN201610589088.4A CN201610589088A CN106121864A CN 106121864 A CN106121864 A CN 106121864A CN 201610589088 A CN201610589088 A CN 201610589088A CN 106121864 A CN106121864 A CN 106121864A
- Authority
- CN
- China
- Prior art keywords
- oxidant
- powder column
- body portion
- spray
- electromotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
Disclosed in the present invention, a kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket, including electromotor skull, direct current spray panel, front combustion room housing, powder column, oxidant pressure inlet, burning chamber shell, afterburner housing and jet pipe.Wherein, electromotor skull, direct current spray panel, front combustion room housing, burning chamber shell, afterburner housing and electromotor bonnet, it is fixedly linked from front to back.Powder column is arranged in combustion chamber shell body, and the multiple cross section of powder column is provided with the centrifugal spray passage that axis is tangent with powder column inner passage, and powder column outside wall surface and burning chamber shell internal face surround oxidant liquid collecting cavity.During electromotor work, oxidant is centrifuged spray orifice by head direct current spray panel and body portion multizone simultaneously and enters in engine chamber and blend burning with fuel gas.Can ensure that powder column length range oxidant swirl strength is high, near powder column front end face, combustion speed is higher simultaneously, thus is effectively improved solid-liquid rocket entirety combustion speed.
Description
Technical field
The present invention relates to solid-liquid rocket technical field, specifically, be a kind of head body portion combine multizone from
Heart spray solid-liquid rocket structure.
Background technology
Solid-liquid rocket is a kind of new rocket using liquid oxidizer and solid fuel to combine as propellant
Propulsion system.Because of the physical arrangement of its uniqueness, solid-liquid rocket be overcome the most traditional solid propellant rocket and
Liquid-propellant rocket engine is difficult to the shortcoming overcome, and has cost relatively low, and safety is good, simple in construction, and propellant energy is relative
Higher, easily realize thrust regulation and the repeatedly advantage such as startup.It is contemplated that space industry, the most middle-size and small-size sounding rocket, sub-rail
The aspects such as road aircraft and high-altitude high speed cruise flight device have vast potential for future development.
But owing to oxidant and the fuel of solid-liquid rocket are out-phase, non-premix, therefore in its combustor
Burning is a kind of typical diffusive combustion process.Thereby result in the solid fuel grain burning rate of solid-liquid rocket relatively
Low shortcoming.The combustion speed improving solid-liquid rocket is the problem that must solve in the evolution of solid-liquid rocket.
And oxidant eddy flow spray is owing to, after entering engine chamber, can improve the oxidant stream of entrance engine chamber
Turbulivity, strengthens the blending between electromotor gas-liquid two-phase, and the boundary region of compressing solid fuel grain surface is thinning simultaneously, thus increases
Strong heat transfer between engine high-temperature combustion gas and solid fuel powder column.Oxidant eddy flow spray is believed to be effectively improved starts
The combustion speed of machine solid fuel powder column.
But, use the solid-liquid rocket of traditional oxidant head eddy flow spray, owing to oxidant enters in spray
Being affected by frictional resistance and gas-flow resistance after entering engine chamber, its swirl strength can be gradually lowered, so can only
Improve its combustion speed at solid fuel powder column front section, and the impact on solid fuel powder column back segment is the least.Therefore, for combustion
Burning room and the longer solid-liquid rocket of solid fuel grain length, traditional oxidant head eddy flow spray scheme is to starting
The raising inconspicuous of machine solid fuel powder column entirety combustion speed.
Summary of the invention
In order to solve the problems referred to above, the present invention proposes a kind of head body portion and combines multizone and be centrifuged spray solid-liquid rocket
Engine structure, can ensure the swirl strength that oxidant is higher in the range of the whole chamber length of electromotor, in combination with
The fuel powder column leading portion that the scouring effect of electromotor solid fuel powder column leading portion is caused by oxidant head direct current spray mode is high
Combustion speed, it is ensured that electromotor solid fuel powder column can keep higher combustion speed level in whole length range, thus significantly
Improve the overall combustion speed of solid-liquid rocket.
A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket, including electromotor skull, direct current spray
Panel, front combustion room housing, powder column, burning chamber shell, afterburner housing, electromotor bonnet and engine jet pipe.Wherein, electromotor
Skull, direct current spray panel, front combustion room housing, burning chamber shell, afterburner housing and electromotor bonnet, the most solid
Fixed connected.Oxidant liquid collecting head cavity is formed between electromotor skull and direct current spray panel.Simultaneously at front combustion room housing and afterburner
Inner walls is bonded with heat insulation layer；Powder column is installed in burning chamber shell 5；Engine jet pipe is installed on electromotor bonnet center and leads to
In hole.
Described powder column stage casing is body portion, forms oxidant body portion liquid collecting cavity between powder column body portion and burning chamber shell inwall；With
Time powder column body portion outer wall circumference be equipped with centrifugal spray passage, oxidant body portion liquid collecting cavity is connected with powder column inner passage.On
Stating in the outside wall surface of burning chamber shell, symmetric position is provided with two oxidant pressure inlet A；Two oxidant pressure inlet A and oxygen
The liquid collecting cavity connection of agent body portion；Oxidant pressure inlet B is installed on motor head lid；Oxidant pressure inlet B and oxidant liquid collecting
Head cavity connects；Oxidant pressure inlet A is used to be connected oxidant delivery system with oxidant pressure inlet B.
Thus, oxidant is simultaneously entered by oxidant pressure inlet A and oxidant pressure inlet B and fills oxidant body respectively
Portion's liquid collecting cavity and oxidant liquid collecting head cavity；Oxidant body portion's liquid collecting cavity and oxidant liquid collecting head cavity at electromotor have been filled
After, oxidant can be centrifuged spray passage by the oxidant on powder column and enter electromotor combustion with the spray simultaneously of direct current spray panel
Burn in room.Wherein, by the oxidant of direct current spray panel spray enter after engine chamber for linear motion, and by aoxidizing
Agent is centrifuged the oxidant of spray passage spray and then makees centrifugal motion after entering engine chamber.Oxidant and the pyrolysis of powder column
Gas burns after blending, and high-temperature high-pressure fuel gas is expanded by engine jet pipe and accelerates ejection afterwards, produces retroaction and pushes away
Power.
It is an advantage of the current invention that:
1, head body portion of the present invention combines multizone and is centrifuged spray solid-liquid rocket, at the solid fuel medicine of electromotor
Multiple cross section, shaft portion arranges oxidant and is centrifuged spray orifice, it is ensured that in the whole length range of engine chamber, oxidant
It is held in higher swirl strength level, so that the turbulivity of oxidant is the strongest, is effectively improved electromotor solid
Fuel powder column entirety combustion speed, particularly the combustion speed of solid fuel powder column part the most rearward；
2, head body portion of the present invention combines multizone and is centrifuged spray solid-liquid rocket, is using oxidant body portion multi-region
While territory is centrifuged spray mode, combining the head direct current spray of oxidant, the head direct current spray of oxidant can make to send out
Motivation solid fuel powder column leading portion, particularly the combustion speed near fuel powder column front end face significantly improve, and effectively overcome oxidant many
The electromotor leading portion solid fuel grain burning rate phase that zonal centrifugation spray mode causes due to the more difficult flow upstream of oxidant
Raising and the raising of combustion speed distributing homogeneity to relatively low shortcoming, beneficially solid fuel powder column entirety combustion speed；
3, head body portion of the present invention combines multizone and is centrifuged in spray solid-liquid rocket, utilizes solid fuel powder column shape
The design of shape, outside solid fuel powder column and inside motor combustion chamber case between define an oxidant liquid collecting cavity,
Can ensure that the oxidant uniform spray in body portion, the most additionally increase the complexity of engine structure, with general solid-liquid
The mutual replaceability of rocket engine is good；
4, head body portion of the present invention combines multizone and is centrifuged in spray solid-liquid rocket, and engine body portion oxidant is defeated
Send the mode using two-way symmetry feed liquor, can effectively shorten the engine body portion oxidant liquid collecting cavity filling time, it is ensured that start
The changeover portion time in machine start-up course is shorter, and the spray symmetry of changeover portion oxidant is preferable.
Accompanying drawing explanation
Fig. 1 is that head body portion of the present invention combines multizone and is centrifuged spray solid-liquid rocket overall structure schematic diagram；
Fig. 2 is that head body portion of the present invention combines multizone and is centrifuged in spray solid-liquid rocket on powder column centrifugal spray and leads to
Road design schematic diagram.
In figure:
Room housing is fired before 1-electromotor skull 2-direct current spray panel 3-
4-powder column 5-burning chamber shell 6-afterburner housing
7-electromotor bonnet 8-transmitter jet pipe 9-oxidant liquid collecting head cavity
10-oxidant body portion liquid collecting cavity 11-oxidant is centrifuged spray passage 12-oxidant pressure inlet A
13-oxidant pressure inlet B 14-heat insulation layer 15-jet pipe gland
Detailed description of the invention
The present invention will be further described below in conjunction with the accompanying drawings.
Head body portion of the present invention combines multizone and is centrifuged spray solid-liquid rocket, including electromotor skull 1, direct current spray
Note panel 2, front combustion room housing 3, powder column 4, burning chamber shell 5, afterburner housing 6, electromotor bonnet 7 and engine jet pipe 8, as
Shown in Fig. 1.Wherein, electromotor skull 1, direct current spray panel 2, front combustion room housing 3, burning chamber shell 5, rear so room housing 6 with
Electromotor bonnet 7, is fixedly linked from front to back.Electromotor skull 1, direct current spray panel 2, front combustion room housing 3 and combustion chamber shell
Connect fixing by stay bolt between the front outer of body 5, and two-by-two between to use O RunddichtringO to ensure airtight.Electromotor bonnet
It is 7, same between the rear end outer rim of afterburner housing 6 and burning chamber shell 5 that to use stay bolt to connect fixing, and two-by-two between use O
RunddichtringO ensures airtight.Oxidant liquid collecting head cavity 9 is formed between above-mentioned electromotor skull 1 and direct current spray panel 2；Simultaneously front
Combustion room housing 3 is bonded with, with afterburner housing 6 inwall, the heat insulation layer 14 that heat insulation composite material is made, with to front combustion room housing 3 and
Afterburner housing 6 forms good thermal protection effect.
Described powder column 4 is centrifuged spray solid fuel, generally tubular structure for multizone, is coaxially installed on burning chamber shell
In 5.Powder column 4 stage casing is body portion, and diameter is less than powder column 4 two ends diameter, powder column 4 two ends outer wall and burning chamber shell 5 inwall patch and,
Thus make to be formed between powder column 4 body portion and burning chamber shell 5 inwall oxidant body portion liquid collecting cavity 10.Powder column 4 body portion outer wall is extremely simultaneously
At few 2 sectional positions, it is equipped with oxidant along powder column 4 body portion circumference and is centrifuged spray passage 11, by oxidant body portion liquid collecting cavity
10 connect with powder column 4 inner passage, and as in figure 2 it is shown, each oxidant to be centrifuged the axis of spray passage 11 all internal with powder column 4
Channel cross-section is tangent, it is achieved the multizone of oxidant is centrifuged spray, and can ensure electromotor by oxidant body portion liquid collecting cavity 10
In the middle of work process, the oxidant spray flow that each oxidant is centrifuged spray passage 11 is substantially suitable, makes oxidant start
Spray in machine combustor is the most uniform.
In the outside wall surface of above-mentioned burning chamber shell 5, symmetric position is welded with two oxidant pressure inlet A12；Two oxidations
Agent pressure inlet A12 connects with oxidant body portion liquid collecting cavity 10, is used for connecting oxidant delivery system, oxidant is filled with oxidant
In body portion liquid collecting cavity 10.After oxidant body portion liquid collecting cavity 10 has been filled, oxidant is by the centrifugal spray of the oxidant on powder column 4
Note passage 11 enters in engine chamber, makees centrifugal motion in engine combustion indoor and the pyrolysis gas with powder column 4 blends
Rear participation is burnt.
The central coaxial of above-mentioned electromotor skull 1 is welded with oxidant pressure inlet B13；Oxidant pressure inlet B13 and oxidation
Agent liquid collecting head cavity 9 connects, and is used for connecting oxidant delivery system, is filled with by oxidant in oxidant liquid collecting head cavity 9.At oxidant
After liquid collecting head cavity 9 has been filled, oxidant enters engine chamber by the direct current spray orifice spray on direct current spray panel 2
In, participate in burning after blending with the pyrolysis gas of powder column 4.
Described engine jet pipe 8 is coaxially installed in the through hole that electromotor bonnet 7 center is offered, and is coordinated by shoulder and sends out
Motivation bonnet 7 positions, and is fixed by the jet pipe gland 15 of engine jet pipe 8 overcoat.Engine jet pipe 8 is received for leading portion
Hold back, the Laval nozzle of back segment expansion, it is ensured that the expansion of engine high-temperature combustion gas and accelerate ejection, ideal to produce
Thrust.
Head body portion in the present invention combine multizone be centrifuged spray solid-liquid rocket work time, oxidant passes through
Oxidant pressure inlet A12 and oxidant pressure inlet B13 simultaneously enters and fills oxidant body portion liquid collecting cavity 10 and oxidant respectively
Liquid collecting head cavity 9.After the oxidant body portion liquid collecting cavity 10 of electromotor and oxidant liquid collecting head cavity 9 have been filled, oxidant is permissible
It is centrifuged spray passage 11 by the oxidant on powder column 4 to enter in engine chamber with the spray simultaneously of direct current spray panel.Its
In, by the oxidant of direct current spray panel 2 spray enter after engine chamber for linear motion, and by the centrifugal spray of oxidant
The oxidant of note passage spray then makees centrifugal motion after entering engine chamber.The pyrolysis gas of oxidant and powder column 4 is mixed
Burning after Hun, high-temperature high-pressure fuel gas is expanded by engine jet pipe 8 and accelerates ejection afterwards, produces reaction thrust.
Claims (4)
1. head body portion combines multizone and is centrifuged a spray solid-liquid rocket, including electromotor skull, direct current spray face
Plate, front combustion room housing, powder column, burning chamber shell, afterburner housing, electromotor bonnet and engine jet pipe；Wherein, motor head
Lid, direct current spray panel, front combustion room housing, burning chamber shell, afterburner housing and electromotor bonnet, the most coaxially fix
It is connected；Oxidant liquid collecting head cavity is formed between electromotor skull and direct current spray panel；Simultaneously at front combustion room housing and afterburner shell
Internal wall is bonded with heat insulation layer；Powder column is installed in burning chamber shell 5；Engine jet pipe is installed on electromotor bonnet central through hole
In；It is characterized in that:
Described powder column stage casing is body portion, forms oxidant body portion liquid collecting cavity between powder column body portion and burning chamber shell inwall；Medicine simultaneously
Shaft portion outer wall circumference is equipped with centrifugal spray passage, is connected with powder column inner passage by oxidant body portion liquid collecting cavity；Above-mentioned combustion
Burning in the outside wall surface of room housing, symmetric position is provided with two oxidant pressure inlet A；Two oxidant pressure inlet A and oxidant
The liquid collecting cavity connection of body portion；Oxidant pressure inlet B is installed on motor head lid；Oxidant pressure inlet B and oxidant liquid collecting head cavity
Connection；Oxidant pressure inlet A is used to be connected oxidant delivery system with oxidant pressure inlet B.
2. a kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket, it is characterised in that:
Centrifugal spray passage is offered at least 2 sectional positions of powder column.
3. a kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket, it is characterised in that:
The axis that oxidant is centrifuged spray passage is tangent with cross section, powder column inner passage circle.
4. a kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket, it is characterised in that:
Engine jet pipe is leading portion convergence, the Laval nozzle of back segment expansion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610589088.4A CN106121864A (en) | 2016-07-22 | 2016-07-22 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610589088.4A CN106121864A (en) | 2016-07-22 | 2016-07-22 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106121864A true CN106121864A (en) | 2016-11-16 |
Family
ID=57290650
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610589088.4A Pending CN106121864A (en) | 2016-07-22 | 2016-07-22 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106121864A (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762228A (en) * | 2017-01-19 | 2017-05-31 | 北京航空航天大学 | The high-strength hydrogen peroxide catalytic bed that solid-liquid rocket works long hours |
| CN106837609A (en) * | 2017-04-07 | 2017-06-13 | 北京航空航天大学 | A kind of change propulsive solid-liquid rocket two-way centrifugal injector 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 |
| CN106968837A (en) * | 2017-04-01 | 2017-07-21 | 北京航空航天大学 | A kind of secondary spray structure of hydrogen peroxide hybrid rocket engine afterburner |
| CN107327356A (en) * | 2017-08-11 | 2017-11-07 | 北京航空航天大学 | A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner |
| CN107461277A (en) * | 2017-10-11 | 2017-12-12 | 北京航空航天大学 | A kind of ground experiment modularization hybrid rocket engine |
| CN107642436A (en) * | 2017-08-11 | 2018-01-30 | 北京航空航天大学 | A kind of hybrid rocket engine thrust gas vector controlled structure and method |
| CN109162832A (en) * | 2018-10-09 | 2019-01-08 | 北京航空航天大学 | Engine head structure, hybrid rocket engine and rocket |
| CN109441666A (en) * | 2018-10-30 | 2019-03-08 | 北京航空航天大学 | Tail portion vortex centrifugal jetting type hybrid rocket engine |
| CN109763916A (en) * | 2018-05-15 | 2019-05-17 | 湖北航天化学技术研究所 | A kind of solid rocket motor nozzle component connection sealing structure |
| CN113339161A (en) * | 2021-06-25 | 2021-09-03 | 中国科学院力学研究所 | Solid-liquid rocket engine grain based on novel metal fuel adding method |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
| CN114017208A (en) * | 2021-12-09 | 2022-02-08 | 北京航空航天大学 | Solid-liquid rocket engine catalytic bed and cooling and preheating system and method thereof |
| CN114263548A (en) * | 2021-12-22 | 2022-04-01 | 宁波天擎航天科技有限公司 | Solid-liquid mixed engine and aircraft |
| CN114856863A (en) * | 2022-06-14 | 2022-08-05 | 中国科学院力学研究所 | Injector for spirally nested type explosive column |
| CN115045777A (en) * | 2022-06-14 | 2022-09-13 | 中国科学院力学研究所 | Variable thrust solid-liquid rocket engine based on combined explosive columns |
| CN115263607A (en) * | 2022-06-14 | 2022-11-01 | 中国科学院力学研究所 | Combustion control method for solid-liquid rocket engine and variable-thrust solid-liquid rocket engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102943719A (en) * | 2012-11-06 | 2013-02-27 | 北京航空航天大学 | Turbulence device for postcombustion chamber of hybrid rocket engine |
| CN102996284A (en) * | 2012-11-27 | 2013-03-27 | 北京航空航天大学 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
| CN103557094A (en) * | 2013-09-18 | 2014-02-05 | 北京航空航天大学 | High-concentration hydrogen peroxide catalysis bed structure used for ground test of solid-liquid hybrid rocket motor |
| CN104806381A (en) * | 2015-04-03 | 2015-07-29 | 北京航空航天大学 | Solid-liquid rocket engine igniter and head wire-outgoing method thereof |
-
2016
- 2016-07-22 CN CN201610589088.4A patent/CN106121864A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102943719A (en) * | 2012-11-06 | 2013-02-27 | 北京航空航天大学 | Turbulence device for postcombustion chamber of hybrid rocket engine |
| CN102996284A (en) * | 2012-11-27 | 2013-03-27 | 北京航空航天大学 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
| CN103557094A (en) * | 2013-09-18 | 2014-02-05 | 北京航空航天大学 | High-concentration hydrogen peroxide catalysis bed structure used for ground test of solid-liquid hybrid rocket motor |
| CN104806381A (en) * | 2015-04-03 | 2015-07-29 | 北京航空航天大学 | Solid-liquid rocket engine igniter and head wire-outgoing method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 宋志兵: "固液混合火箭发动机工作过程研究", 《中国博士学位论文全文数据库》 * |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762228A (en) * | 2017-01-19 | 2017-05-31 | 北京航空航天大学 | The high-strength hydrogen peroxide catalytic bed that solid-liquid rocket works long hours |
| 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 |
| CN106968837A (en) * | 2017-04-01 | 2017-07-21 | 北京航空航天大学 | A kind of secondary spray structure of hydrogen peroxide hybrid rocket engine afterburner |
| CN106837609A (en) * | 2017-04-07 | 2017-06-13 | 北京航空航天大学 | A kind of change propulsive solid-liquid rocket two-way centrifugal injector structure |
| CN106837609B (en) * | 2017-04-07 | 2018-03-09 | 北京航空航天大学 | A kind of change propulsive solid-liquid rocket two-way centrifugal injector structure |
| CN107327356A (en) * | 2017-08-11 | 2017-11-07 | 北京航空航天大学 | A kind of method for improving solid-liquid rocket efficiency of combustion in afterburner |
| CN107642436A (en) * | 2017-08-11 | 2018-01-30 | 北京航空航天大学 | A kind of hybrid rocket engine thrust gas vector controlled structure and method |
| CN107461277A (en) * | 2017-10-11 | 2017-12-12 | 北京航空航天大学 | A kind of ground experiment modularization hybrid rocket engine |
| CN109763916A (en) * | 2018-05-15 | 2019-05-17 | 湖北航天化学技术研究所 | A kind of solid rocket motor nozzle component connection sealing structure |
| CN109162832A (en) * | 2018-10-09 | 2019-01-08 | 北京航空航天大学 | Engine head structure, hybrid rocket engine and rocket |
| CN109441666A (en) * | 2018-10-30 | 2019-03-08 | 北京航空航天大学 | Tail portion vortex centrifugal jetting type hybrid rocket engine |
| CN109441666B (en) * | 2018-10-30 | 2021-04-20 | 北京航空航天大学 | Tail vortex centrifugal injection type solid-liquid hybrid rocket engine |
| CN113339161A (en) * | 2021-06-25 | 2021-09-03 | 中国科学院力学研究所 | Solid-liquid rocket engine grain based on novel metal fuel adding method |
| CN113357051A (en) * | 2021-06-25 | 2021-09-07 | 中国科学院力学研究所 | Internal spiral injection type solid-liquid engine explosive column |
| CN114017208A (en) * | 2021-12-09 | 2022-02-08 | 北京航空航天大学 | Solid-liquid rocket engine catalytic bed and cooling and preheating system and method thereof |
| CN114263548A (en) * | 2021-12-22 | 2022-04-01 | 宁波天擎航天科技有限公司 | Solid-liquid mixed engine and aircraft |
| CN114856863A (en) * | 2022-06-14 | 2022-08-05 | 中国科学院力学研究所 | Injector for spirally nested type explosive column |
| CN115045777A (en) * | 2022-06-14 | 2022-09-13 | 中国科学院力学研究所 | Variable thrust solid-liquid rocket engine based on combined explosive columns |
| CN115263607A (en) * | 2022-06-14 | 2022-11-01 | 中国科学院力学研究所 | Combustion control method for solid-liquid rocket engine and variable-thrust solid-liquid rocket engine |
| CN115045777B (en) * | 2022-06-14 | 2022-12-23 | 中国科学院力学研究所 | Variable thrust solid-liquid rocket engine based on combined explosive columns |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106121864A (en) | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket | |
| CN112879178B (en) | Solid rocket ramjet based on detonation combustion | |
| CN103967653B (en) | A kind of axially injection end combustion solid-liquid rocket structure | |
| CN111664022B (en) | Combustion chamber of rotary detonation ramjet engine with fuel injection | |
| US6601380B2 (en) | Hybrid rocket engine and method of propelling a rocket | |
| CN110469428A (en) | Double atomization pintle ejector filler suitable for high-viscous liquid | |
| CN103670797B (en) | A kind of solid-liquid scramjet engine | |
| CN108843462B (en) | It is classified pressurized combustion solid propellant rocket | |
| CN107956601A (en) | One group of major diameter rocket thrust chamber with discharge re-generatively cooled partition plate | |
| CN109139298A (en) | A kind of space double elements precise tracking based on two-way single injector centrifugation ejector filler | |
| CN108894893A (en) | Rocket punching press combined engine Film cooling Rocket ejector motor power room | |
| CN102943719A (en) | Turbulence device for postcombustion chamber of hybrid rocket engine | |
| CN110131074B (en) | Bipropellant air turbine rocket propulsion system | |
| CN108895484A (en) | A kind of cooling combustion chamber of gas oxygen/kerosene vortex | |
| CN108590885B (en) | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure | |
| CN106870205B (en) | A kind of diplopore shape segmentation rotation powder charge solid-liquid rocket thrust chamber | |
| CN109505711A (en) | It is a kind of for generating the gas-gas mouse device of high temperature ultrasonic quick burning gas | |
| CN110700963B (en) | Compact layout type solid rocket gas scramjet engine based on axial symmetry | |
| CN105715409A (en) | Annular solid-liquid catalytic ignition engine | |
| CN108953002A (en) | With the rocket series thrust chamber on single flow head and cooling discharge partition | |
| CN116025484B (en) | Continuous detonation solid rocket engine system based on solid powder | |
| CN107642436A (en) | A kind of hybrid rocket engine thrust gas vector controlled structure and method | |
| CN109404165B (en) | The continuous pinking rocket base engine and aircraft of thruster vector control | |
| CN109441666A (en) | Tail portion vortex centrifugal jetting type hybrid rocket engine | |
| US2518881A (en) | Fuel feeding and cooling construction for rotating combustion chambers |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161116 |
|
| RJ01 | Rejection of invention patent application after publication |