CN107642436A - A kind of hybrid rocket engine thrust gas vector controlled structure and method - Google Patents
A kind of hybrid rocket engine thrust gas vector controlled structure and method Download PDFInfo
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- CN107642436A CN107642436A CN201710686220.8A CN201710686220A CN107642436A CN 107642436 A CN107642436 A CN 107642436A CN 201710686220 A CN201710686220 A CN 201710686220A CN 107642436 A CN107642436 A CN 107642436A
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- injection
- jet pipe
- ejector filler
- secondary injection
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Abstract
The present invention discloses a kind of solid-liquid rocket structure and method suitable for vector controlled, and secondary injection conduction hole is opened up in the preceding combustion room side wall of solid-liquid rocket；The circumference uniform design secondary injection hole at the expansion segment of jet pipe simultaneously, installation ejector filler in secondary injection hole；Above-mentioned secondary injection conduction hole is connected between ejector filler by transfer pipeline；Ejector filler is connected by the spray passage opened up in jet pipe heat insulation layer with jet pipe inside；The mixed gas of preceding combustion chamber is introduced through transfer pipeline by nozzle divergence cone by secondary injection conduction hole and carries out secondary injection.In the present invention, mechanical mechanism designing quality is light, long lifespan, suitable for working long hours；And gas injection sprays in jet pipe, improve engine performance and reduce Specific Impulse Loss caused by thrust regulation.
Description
Technical field
The invention belongs to thruster vector control technical field, designs a kind of hybrid rocket engine thrust gas vector
Control structure and method.
Background technology
The development of thruster vector control technology and aerospace field is closely related.Because it can effectively improve the machine of engine
Dynamic performance, reduces rocket flight resistance and weight, improves stealth capabilities, security and survival ability etc., has become rocket hair
The key technology of motivation development, and it is used as a know-how to be studied.
Mechanical thruster vector control mostly uses hydraulic pressure or mechanical actuation part, passes through jet pipe, flap or folding
Flowing plate course changing control produces thrust vectoring, improves engine weight increase cost.Complicated activation part and structure adds
System complexity, moving component increase under hot environment, cooling require to improve, and system reliability declines.China's engine at present
Increasing with the explosive payload of boost motor, gimbaled nozzle volume and weight containing servo control mechanism accordingly increases, and also needs to roll dress
Put realization and roll control.Low-altitude antimissile guided missile, air-to-air missile equidimension weight are relatively small, and installing space is extremely limited, at present
Use choked flow deflection class (jet vane, combustion gas slurry, spoiler, bias current ring) thrust vectoring simple in construction, technology relative maturity more
Control system, thrust loss is larger and has constant value loss, and rudder face ablation problem protrudes.
In recent years, solid-liquid rocket propulsion system is quickly grown, and this means that the requirement to thrust vector control system
More and more higher.Therefore there is an urgent need to a kind of more advanced simple vector control system to meet the modern times of solid-liquid rocket
Demand.
The content of the invention
In order to solve the above problems, the present invention, which combines solid-liquid rocket itself, can be catalyzed the knot for producing mixed gas
Structure feature, a kind of hybrid rocket engine thrust gas vector controlled structure and method are proposed, have and respond fast, volume
Small, in light weight, the advantages that cost is low, service behaviour is high, easy to operate.
Hybrid rocket engine thrust gas vector controlled structure of the present invention is：In the preceding combustion of solid-liquid rocket
Secondary injection conduction hole is opened up in the side wall of room；Circumference uniform design secondary injection hole, secondary spray at the expansion segment of jet pipe simultaneously
Installation ejector filler in perforation.
Above-mentioned secondary injection conduction hole is connected between ejector filler by transfer pipeline；Ejector filler in jet pipe heat insulation layer by opening
If spray passage and jet pipe inside connect；By secondary injection conduction hole by the mixed gas of preceding combustion chamber through delivery pipe pass
Enter to nozzle divergence cone and carry out secondary injection.
Solid-liquid rocket gas injection vector controlled is realized from there through following manner, is specially：Pass through pressurized bottle
Supercharging, liquid hydrogen peroxide enter head cavity and by the hole on liquid injection panel even into catalytic bed housing by import,
High-temperature gas mixture body is decomposed into by catalyst；Mixed gas is again by gas injection panel even into preceding combustion chamber shell
Body；In the presence of high pressure, mixed gas enters transfer pipeline by the secondary injection conduction hole of preceding combustion room housing side, then
Pass sequentially through ejector filler and spray passage with main flow combustion gas to converge, finally discharged with main flow combustion gas by nozzle exit.
The advantage of the invention is that：
1st, hybrid rocket engine thrust gas vector controlled structure of the present invention, mechanical mechanism designing quality is light, the longevity
Life length, suitable for working long hours.
2nd, hybrid rocket engine thrust gas vector controlled structure of the present invention, from gas injection, easily carry out
Heat protection design.
3rd, hybrid rocket engine thrust gas vector control method of the present invention, regulation ratio are controlled by flow, easily
Accurate control is realized, thrust regulation is than big.
4th, hybrid rocket engine thrust gas vector control method of the present invention, gas injection spray in jet pipe, carried
High engine performance and reduce thrust regulation caused by Specific Impulse Loss.
Brief description of the drawings
Fig. 1 is the nozzle structure profile of solid-liquid rocket gas injection vector control method of the present invention.
Combustion-chamber assembly 3- combustion chambers before 1- catalytic bed components 2-
4- after-burner component 5- rear head component 6- jet pipes
7- secondary injection conduction hole 8- secondary injections hole 9- ejector fillers
10- spray passage 101- engine head 102- catalytic bed housings
Burning chamber shell before 103- liquid injection panel 104- gas injection panels 201-
Room heat insulation layer 301- burning chamber shell 302- cast powder columns are fired before 202-
401- after-burning room housing 402- afterburner heat insulation layer 501- rear head housings
502- rear head heat insulation layer 601- jet pipe housing 602- jet pipe heat insulation layers
603- jet pipe pressing plates
Specific embodiment
The present invention is described in further details below in conjunction with the accompanying drawings.
Solid-liquid rocket gas injection vector control method of the present invention, wherein solid-liquid rocket include catalytic bed
Component 1, preceding combustion-chamber assembly 2, combustion chamber 3, after-burner component 4, rear head component 5 and jet pipe 6, as shown in Figure 1.
The catalytic bed component 1 includes engine head 101, catalytic bed housing 102, liquid injection panel 103 and gas
Spray panel 104, it is made of 1Cr18Ni9Ti stainless steels.Wherein, port is coaxially provided with engine head 101, as
The entrance of liquid propellant.Catalyst is filled with catalytic bed housing 102, between catalytic bed housing 102 and engine head 101
Coaxially it is fixedly mounted by bolt and nut, and O-shaped rubber is provided between the head of catalytic bed housing 102 and engine head 101
Sealing ring, realization seal between the two.Liquid injection panel 103 is coaxially fixedly installed in and urged respectively with gas injection panel 104
Change head and the afterbody of bed housing 102, be respectively intended to realize the atomization of liquid hydrogen peroxide and the uniform spray of gas.
The preceding combustion-chamber assembly 2 includes preceding burning chamber shell 201 and preceding combustion room heat insulation layer 202.Combustion chamber 3 includes burning
Room housing 301 and cast powder column 302.Wherein, preceding combustion room housing 201 is made of stainless steel material, is coaxially disposed in catalytic bed
Between the afterbody of housing 102 and the head of burning chamber shell 301.Burning chamber shell 301 is made of 1Cr18Ni9Ti stainless steel materials,
Inside is provided with the cast powder column 302 of high-density polyethylene material.Burning chamber shell 301 passes through screw bolt passes combustion chamber shell
After flange, the outer rim of preceding burning chamber shell 201 and the afterbody of catalytic bed housing 102 of the head design of body 301 design annular boss, by
Nut tightens fixation, realizes catalytic bed housing 102, preceding burning chamber shell 201 and 301 triangular fixation of burning chamber shell.Before
High silica thermal insulation of materials layer is equipped with the inwall of burning chamber shell 201.
The after-burner component 4 includes after-burning room housing 401 and afterburner heat insulation layer 402.After rear head component 5 includes
End socket housing 501 and rear head heat insulation layer 502.After-burning room housing 401 is made of stainless steel material, and inwall is equipped with high silica
The afterburner heat insulation layer 402 of material, is adhesively fixed therebetween with glue.Rear head housing 501 is interior using steel ASTM A572
Wall is equally equipped with the rear head heat insulation layer 502 of high silica material.The method of the afterbody of screw bolt passes burning chamber shell 301 design
After the annular boss that blue, the outer rim of after-burning room housing 401 and the side wall of rear head housing 501 circumferentially design, fixation is tightened by nut,
Realize rear head housing 501, after-burning room housing 401 and 301 triangular fixation of burning chamber shell.
The jet pipe housing 601 of the jet pipe 6 uses 30CrMnSi structural alloy steels, and jet pipe heat insulation layer 602 is high silica.Weldering
Connect mouth 18 and use high temperature-resistantungsten tungsten copper alloy.Jet pipe 6 is coaxially disposed with rear head housing 501, and the head of jet pipe 6 is arranged at rear head shell
In the through hole that the end of body 501 opens up, shoulder positions between the two.Jet pipe pressing plate 603 is socketed outside jet pipe housing 601, will by screw
Jet pipe pressing plate 603 is fixed with rear head housing 501, and then realizes the fixation of jet pipe 6.
In the present invention, in the side wall of the preceding combustion room housing 201 of above-mentioned solid-liquid rocket offering secondary injection draws
Discharge orifice 7；Circumference uniform design has 4 secondary injection holes 8, the aperture design in secondary injection hole 8 at the expansion segment of jet pipe 6 simultaneously
For 3mm, for installing ejector filler 9.The ejector filler 9 makees weld with being threadedly coupled between secondary injection hole in junction
Reason, makes the ejection end of ejector filler 9 extend into jet pipe heat insulation layer 602, and is sealed by O-shaped sealing gasket, thus prevents high temperature from mixing
Gas is closed to penetrate into the gap between jet pipe housing 601 and jet pipe heat insulation layer 602.And soldering, spray are carried out in junction
Note device 9 connects with the spray passage 10 opened up in jet pipe heat insulation layer 602, and is connected by spray passage 10 with the inside of jet pipe 6.By
This, introduces nozzle divergence cone through transfer pipeline by the mixed gas of preceding combustion chamber by secondary injection conduction hole 602 and carries out two
Secondary injection.
Solid-liquid rocket gas injection vector controlled is realized from there through following manner, is specially：Pass through pressurized bottle
Supercharging, liquid hydrogen peroxide enter head cavity (cavity between liquid injection panel 103 and engine head 101) by import 601
And decomposed by equally distributed circular hole on liquid injection panel 103 even into catalytic bed housing 102 by catalyst
For high-temperature gas mixture body, including vapor and oxygen.Mixed gas is again by gas injection panel 104 even into preceding combustion chamber
Housing 201.In the presence of high pressure, mixed gas is entered defeated by the secondary injection conduction hole 7 of preceding combustion room housing 201 side
Pipeline is sent, ejector filler 9 and spray passage 10 is then passed sequentially through and converges with main flow combustion gas, finally with main flow combustion gas by jet pipe
The discharge of 6 outlet 604.
Transfer pipeline is connected with four branch lines by a main line and formed in the present invention, and main line draws with secondary injection
Discharge orifice 7 connects, and four Tiao Zhi roads connect with 4 ejector fillers 9 respectively.Because solid-liquid rocket is change propulsive rocket, therefore pass through setting
Adjustable Venturi tube is installed on branch line, at any time control mixed gas flow come influence main flow injection and then control fire
The purpose of arrow direction vector.
The eject position of ejector filler 9 is designed as at 1/4,1/2 or the 3/4 of nozzle divergence cone in the present invention；And spray angle
For the axis of ejector filler 9 and the angle of nozzle axis direction of flow, it is chosen for：30 °, 45 °, 60 °, 90 °, 135 ° and 150 °.Injection
Flow is set to the 2%, 4%, 6%, 8% and 10% of main flow.It is arranged in from there through each gas jetting hole and uniformly circumferentially
Expansion segment is jetted through, effect is to control four, upper and lower, left and right direction vector respectively.In order to be optimal vector controlled performance, lead to
The simulation result for crossing each operating mode determines, optimal eject position nozzle divergence cone central region, i.e., at 1/2, most preferably
Spray angle is set to 90 °, and optimal injection flow is the 6% of main flow.
Claims (6)
- A kind of 1. solid-liquid rocket gas injection vector controlled structure, it is characterised in that：Before solid-liquid rocket Secondary injection conduction hole is opened up in combustion room side wall；The circumference uniform design secondary injection hole at the expansion segment of jet pipe simultaneously, it is secondary Installation ejector filler in spray-hole；Above-mentioned secondary injection conduction hole is connected between ejector filler by transfer pipeline；Ejector filler passes through spray The spray passage opened up in pipe heat insulation layer inside jet pipe with connecting；By secondary injection conduction hole by the mixed gas of preceding combustion chamber Nozzle divergence cone, which is incorporated into, through transfer pipeline carries out secondary injection.
- A kind of 2. solid-liquid rocket gas injection vector controlled structure as claimed in claim 1, it is characterised in that：Ejector filler Ejection end extend into jet pipe heat insulation layer.
- A kind of 3. solid-liquid rocket gas injection vector controlled structure as claimed in claim 1, it is characterised in that：Delivery pipe One main line of route connects composition with n bar branch lines, and main line connects with secondary injection conduction hole；The quantity of branch line N is equal with ejector filler quantity, is connected respectively with each ejector filler；Adjustable Venturi tube is installed on each branch line simultaneously.
- 4. solid-liquid rocket gas injection vector controlled structure as claimed in claim 1, it is characterised in that：The spray of ejector filler Penetrate Position Design be nozzle divergence cone 1/4,1/2 or 3/4 at；And spray angle is ejector filler axis and nozzle axis incoming side To angle, be chosen for：30 °, 45 °, 60 °, 90 °, 135 ° or 150 °；Injection flow be set to main flow 2%, 4%, 6%, 8% or 10%.
- 5. solid-liquid rocket gas injection vector controlled structure as claimed in claim 1, it is characterised in that：Eject position exists At the 1/2 of nozzle divergence cone, spray angle is set to 90 °, and injection flow is the 6% of main flow.
- A kind of 6. solid-liquid rocket gas injection vector control method, it is characterised in that：It is pressurized by pressurized bottle, liquid mistake Hydrogen oxide enters head cavity and by the hole on liquid injection panel even into catalytic bed housing by import, is urged by catalyst Change is decomposed into high-temperature gas mixture body；Mixed gas is again by gas injection panel even into preceding burning chamber shell；In high pressure Under effect, mixed gas enters transfer pipeline by the secondary injection conduction hole of preceding combustion room housing side, subsequently enters and is installed on Ejector filler in nozzle divergence cone circumference, sprayed, converged with main flow combustion gas, finally by the spray passage opened up on jet pipe heat insulation layer Discharged with main flow combustion gas by nozzle exit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710686220.8A CN107642436A (en) | 2017-08-11 | 2017-08-11 | A kind of hybrid rocket engine thrust gas vector controlled structure and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710686220.8A CN107642436A (en) | 2017-08-11 | 2017-08-11 | A kind of hybrid rocket engine thrust gas vector controlled structure and method |
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| CN107642436A true CN107642436A (en) | 2018-01-30 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139299A (en) * | 2018-09-10 | 2019-01-04 | 北京航空航天大学 | Double pump solid-liquid rocket |
| 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 |
| CN114857620A (en) * | 2022-04-28 | 2022-08-05 | 湖北航天技术研究院总体设计所 | Solid vector thrust device of large gas quantity gas supply mode |
| CN115807720A (en) * | 2022-11-22 | 2023-03-17 | 西北工业大学 | Variable thrust expansion compensation rocket engine based on vortex valve and plug type spray pipe |
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| US20020078680A1 (en) * | 2000-05-24 | 2002-06-27 | Lockhead Martin Corporation | Hybrid injection thrust vector control |
| US20050284128A1 (en) * | 2004-06-29 | 2005-12-29 | Anderson Morris G | Rocket motor nozzle throat area control system and method |
| US20110167793A1 (en) * | 2010-01-11 | 2011-07-14 | Korea Advanced Institute Of Science And Technology | Hybrid rocket using catalytic decomposition of oxidizer |
| 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 |
| CN103899432A (en) * | 2014-03-31 | 2014-07-02 | 西北工业大学 | Improved pneumatic vectoring nozzle structure with function of injecting double secondary flow branches |
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
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Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20020078680A1 (en) * | 2000-05-24 | 2002-06-27 | Lockhead Martin Corporation | Hybrid injection thrust vector control |
| US20050284128A1 (en) * | 2004-06-29 | 2005-12-29 | Anderson Morris G | Rocket motor nozzle throat area control system and method |
| US20110167793A1 (en) * | 2010-01-11 | 2011-07-14 | Korea Advanced Institute Of Science And Technology | Hybrid rocket using catalytic decomposition of oxidizer |
| 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 |
| CN103899432A (en) * | 2014-03-31 | 2014-07-02 | 西北工业大学 | Improved pneumatic vectoring nozzle structure with function of injecting double secondary flow branches |
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139299A (en) * | 2018-09-10 | 2019-01-04 | 北京航空航天大学 | Double pump solid-liquid rocket |
| 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 |
| CN114857620A (en) * | 2022-04-28 | 2022-08-05 | 湖北航天技术研究院总体设计所 | Solid vector thrust device of large gas quantity gas supply mode |
| CN114857620B (en) * | 2022-04-28 | 2023-06-20 | 湖北航天技术研究院总体设计所 | Solid vector thrust device of large-gas-quantity gas supply mode |
| CN115807720A (en) * | 2022-11-22 | 2023-03-17 | 西北工业大学 | Variable thrust expansion compensation rocket engine based on vortex valve and plug type spray pipe |
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Application publication date: 20180130 |
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