CN109723572A - A kind of impulse rocket cluster engine - Google Patents
A kind of impulse rocket cluster engine Download PDFInfo
- Publication number
- CN109723572A CN109723572A CN201811561578.9A CN201811561578A CN109723572A CN 109723572 A CN109723572 A CN 109723572A CN 201811561578 A CN201811561578 A CN 201811561578A CN 109723572 A CN109723572 A CN 109723572A
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- CN
- China
- Prior art keywords
- ontology
- cabin
- igniter
- jet pipe
- cluster engine
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Abstract
The invention discloses a kind of impulse rocket cluster engine, solve the problems, such as that installing eight pulsed motor structures in small space is difficult to design.Impulse rocket cluster engine includes ontology, igniter, bracket, powder charge, drug blocking bracket, jet pipe, cabin, screw, ontology is less than or equal to 1/8th cabin sectional areas in cabin axial projective area, ontology is machined with igniter installation screw, the bags, jet pipe installation screw, and igniter is used with ontology and is threadedly coupled；Powder charge is fixed in the ontology bags by bracket and drug blocking bracket；Jet pipe is used with ontology and is threadedly coupled；The pulsed motor octette assembled is installed on cabin.The present invention is suitable for missile attitude control system.
Description
Technical field
The present invention relates to a kind of Missile Attitude Control System Based impulse rocket engines, are primarily adapted for use in solid propellant rocket neck
Domain.
Technical background
High-precision fast-response Guidance and control technology based on lateral force control is the core of precise guidance aircraft of new generation
Technology with strong military requirement and is widely applied.Lateral force is generated for small-bore portable missile control system
Major way has lateral force air bottle, gas generator or lateral force rocket engine etc..Wherein lateral force gas cylinder is bulky
And maintenance cost is higher after long-term storage, gas generator needs to carry out the factors such as traffic organising by valve causes its structure multiple
It is miscellaneous and be restricted in small portable guided missile small space.
Due to solid propellant rocket structure it is simple, it is easy to maintain, can generate in a short time compared with high thrust the advantages of still
It is largely used to the lateral force output demand of various guided missiles.There are two types of the design methods of traditional pulse engine.A kind of mode is whole
Body symmetrical structure, igniter axis, burning chamber axis, nozzle axis are overlapped, the thrust axis and burning chamber axis that jet pipe generates
It is overlapped.It is needed to be evenly distributed in control cabinet body section plane using the impulse rocket engine of this kind of design method, engine
Axis is vertical and passes through cabin axis.The impulse rocket engine is larger in control cabinet radial direction occupied space, and starts
Multiple sector spaces can be left between machine to be made full use of.Another design method is to use Local Symmetric structure, will
Igniter axis, burning chamber axis carry out coincidence design, and nozzle axis is vertical and passes through burning chamber axis.Using the design method
Pulsed motor generally use multiple circumferential arrays, burning chamber axis is parallel with cabin axis, and nozzle axis vertically and passes through
Cabin axis.But this kind of pulsed motor enters jet pipe, institute after needing to carry out right-angle turning due to the combustion gas that charging work generates
Ablation can be generated to jet pipe, prevent actual thrust axis is from vertical bay section axis.Simultaneously because the factor of igniter, in cabin
The axial occupancy installation space of section is larger.
Summary of the invention
To solve the shortcomings of the prior art and defect, the present invention provides a kind of portable missile posture control system pulse
Rocket motor unit.The cluster engine includes eight impulse rocket engines, and Sing plus rocket engine is using blocky non-right
Claim structure, by the vertical design of nozzle axis and burning chamber axis, guarantees that thrust axis vertically and by bay section axis, passes through
Igniter axis is vertical with burning chamber axis to set installation meter, so that cluster engine is in bay section axis direction, radial direction space
Occupied space is minimum.
Realization process of the invention is as follows:
Impulse rocket cluster engine includes eight Sing plus engines, and pulsed motor includes ontology, igniter, branch
Frame, powder charge, drug blocking bracket, jet pipe, cabin, screw.
The ontology is less than or equal to 1/8th cabins in cabin axial projective area using blocky unsymmetric structure, at it
Body section product；Ontology uses 1Cr17Ni2Material (corrosion resistance is good, without surface treatment), processing igniter installation screw, combustion
Room space, jet pipe installation screw are burnt, igniter installation screw axis is vertical and passes through burning chamber axis, jet pipe installation screw axis
It is overlapped with burning chamber axis.
The igniter, using being threadedly coupled, carries out thread seal using sealant with ontology.
The powder charge is prepared using high burn rate solid propellant, and in pressure 10MPa-20MPa, burn rate is 40mm/s-
80mm/s, whole design are single hole tubular structure.Powder charge free loading propellant is in the ontology bags, by bracket and drug blocking bracket
It is fixed.
The drug blocking bracket uses 1Cr17Ni2Material, plane projection are designed as ring-type, design with propellant contact portion
Powder charge is fixed in four paws, the reserved blast tube in cyclic annular outside, inside.
The jet pipe uses 1Cr17Ni2Material is used with ontology and is threadedly coupled.Jet pipe designs four towards powder charge direction
Rectangular support guarantees that combustion gas passes through；Jet pipe carries out thread seal using sealant, forms Sing plus engine.
The bay section is used for the installation of eight Sing plus engines, forms pulsed motor group.
Working principle of the present invention are as follows: igniter be powered after light a fire to powder charge, powder charge burning generate combustion gas, combustion gas via
Jet pipe flows generation control power outward.
The present invention has following advantages: the configuration of the present invention is simple, assembles quick, easy to maintain.Using asymmetric design knot
Structure, so that pulsed motor minimizes in cabin radical length and axial space volume needs, space utilization rate is high.Using height
Burn rate propellant, operation time export eight impulse forces according to ignition order, and Sing plus thrust parameter is the working time
10ms~20ms, thrust are 150N~200N.
Detailed description of the invention
Fig. 1 is Sing plus engine sectional structure chart, 1- ontology, 2- igniter, 3- bracket, 4- powder charge, 5- drug blocking branch
Frame, 6 jet pipes.
Fig. 2 is igniting rack structural schematic diagram.
Fig. 3 is lance holder structural schematic diagram.
Fig. 4 is pulsed motor group scheme of installation, 7- cabin, 8- screw.
Specific embodiment
Explanation is further explained to the present invention below by specific embodiments and the drawings.
Such as Fig. 1, in Sing plus engine, ontology 1 is designed using unsymmetric structure, in diagram plane vertical direction
Projected area is less than or equal to 1/8th circles, and left view, right view are rectangle.Ontology 1 uses 1Cr17Ni2 material, and design has
The bags, 2 installation screw of igniter, 6 installation screw of jet pipe, 8 installation screw of screw.Jet pipe 6 installs threaded hole design and exists
Bags left end, and jet pipe 6 is installed the axis of thread and is overlapped with bags axis；To reduce installation space, igniter 2
Threaded hole is installed, threaded hole is installed close to jet pipe, and igniter 2 installs screw thread axially bored line vertically and installs threaded hole by jet pipe 6
Axis.Igniter 2, using being threadedly coupled, carries out thread seal using sealant with ontology 1.Powder charge 4 uses high burn rate solid
Propellant preparation, in pressure 10MPa~20MPa, burn rate is 40mm/s~80mm/s, and whole design is single hole tubular structure.
In 1 bags of ontology, right end is fixed 4 free loading propellant of powder charge by bracket 3, and left end is fixed by drug blocking bracket 5,
It is not contacted with 1 bags inner wall of ontology；Bracket 3 uses 1Cr17Ni2Material, plane projection are designed as ring-type, with powder charge 4
Powder charge 4 is fixed in contact portion design four paws.Bracket 5 uses 1Cr17Ni2Material, plane projection are designed as cyclic annular (as schemed
2), four paws structure is designed as with 4 contact portion of powder charge powder charge 4 is fixed.Cyclic annular outside, the reserved blast tube in inside, one
As the cyclic annular outside of design, inside reserve 3~5 times that blast tube area is 6 throat area of jet pipe.Jet pipe 6 uses
1Cr17Ni2 material carries out thread seal using sealant with ontology 1 using being threadedly coupled.Jet pipe 6 is towards 5 side of drug blocking bracket
To four rectangular boss (such as Fig. 3) of design, guarantees that the work of powder charge 4 generates gas flow channel, be typically designed 6 boss of jet pipe and formed
Breathing area be 5 times or more of 6 throat area of jet pipe.The inner profile in jet pipe 6 towards 5 direction of powder charge bracket is designed as restraining
Section, interlude are venturi, are designed as expansion segment backwards to 4 direction of powder charge, when venturi controlled loading of explosive 4 burns pressure with engine operation
Between.Jet pipe 6 designs mounting groove backwards to the end face of powder charge.By operating above, Sing plus engine is completed.Such as Fig. 4, eight lists
One pulsed motor is mounted in cabin 7, is fixed by screw 8, and pulsed motor group is formed.
This pulsed motor group after the assembly is completed, is successively powered to igniter, and powder charge is lighted in igniter ignition, powder charge according to
Designed combustion generates combustion gas, and combustion gas is compressed through jet pipe, flowing generates eight impulse forces outward for expansion.After measured, Sing plus
Thrust parameter is working time 10ms~20ms, and thrust is 150N~200N.
Claims (6)
1. a kind of impulse rocket cluster engine, it is characterised in that including eight Sing plus engines, pulsed motor includes this
Body (1), igniter (2), bracket (3), powder charge (4), drug blocking bracket (5), jet pipe (6), cabin (7), screw (8)；The ontology
(1) it is unsymmetric structure, is machined with igniter installation screw, combustion chamber, jet pipe installation screw, igniter (2), jet pipe (6) point
Not Tong Guo igniter installation screw, jet pipe installation screw be threadedly coupled with ontology (1), powder charge (4) is by bracket (3) and drug blocking bracket
(5) it is fixed in ontology (1) combustion chamber；The pulsed motor octette assembled is installed in cabin by screw (8)
(7)。
2. impulse rocket cluster engine according to claim 1, it is characterised in that the ontology (1) is blocky unsymmetrical knot
Structure is less than or equal to 1/8th cabin sectional areas in cabin axial projective area.
3. impulse rocket cluster engine according to claim 1, it is characterised in that the Sing plus motor power axis
Line is vertical and passes through cabin axis.
4. impulse rocket cluster engine according to claim 1, it is characterised in that igniter (2) axis and single arteries and veins
It is vertical and vertical with cabin axis to rush motor power axis.
5. impulse rocket cluster engine according to claim 1, it is characterised in that the powder charge (4) pressure 10MPa~
Burn rate is 40mm/s~80mm/s when 20MPa.
6. impulse rocket cluster engine according to claim 1, it is characterised in that eight pulses of operation time Sequential output
Thrust, Sing plus thrust parameter are working time 10ms~20ms, and thrust is 150N~200N.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811561578.9A CN109723572A (en) | 2018-12-20 | 2018-12-20 | A kind of impulse rocket cluster engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811561578.9A CN109723572A (en) | 2018-12-20 | 2018-12-20 | A kind of impulse rocket cluster engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109723572A true CN109723572A (en) | 2019-05-07 |
Family
ID=66296907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811561578.9A Pending CN109723572A (en) | 2018-12-20 | 2018-12-20 | A kind of impulse rocket cluster engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109723572A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110195665A (en) * | 2019-06-21 | 2019-09-03 | 北京理工大学 | A kind of air storing type solid propellant power device of reloading |
| CN110778416A (en) * | 2019-09-26 | 2020-02-11 | 湖北三江航天红林探控有限公司 | Pulse type attitude control thruster based on shared combustion chamber |
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| CN107472512A (en) * | 2017-08-01 | 2017-12-15 | 西华酷农无人机产业园运营有限公司 | A kind of reinforced propeller of unmanned plane |
| CN108590885A (en) * | 2018-05-10 | 2018-09-28 | 北京理工大学 | A kind of multi-functional modularization solid propellant rocket combination spray pipe structure |
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|---|---|---|---|---|
| US3280566A (en) * | 1962-07-19 | 1966-10-25 | Onera (Off Nat Aerospatiale) | Solid propellant rocket motors |
| CN200964906Y (en) * | 2006-10-13 | 2007-10-24 | 中国北方工业公司 | Terminal guided fodder impulse correction engine |
| CN101054932A (en) * | 2007-04-18 | 2007-10-17 | 陈久斌 | Nuclear power engine and aerocraft produced thereby and spacecraft |
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| CN101240757A (en) * | 2007-12-28 | 2008-08-13 | 中国航天科技集团公司第六研究院第十一研究所 | Heavy caliber asymmetric layout swinging hose |
| RU2449155C2 (en) * | 2010-07-29 | 2012-04-27 | Открытое акционерное общество Научно-производственное объединение "Искра" | Solid propellant rocket engine |
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| CN105804889A (en) * | 2016-02-04 | 2016-07-27 | 北京航空航天大学 | Method for starting main engine by solid-liquid ignition engine through multiple times of catalysis and ignition control device thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110195665A (en) * | 2019-06-21 | 2019-09-03 | 北京理工大学 | A kind of air storing type solid propellant power device of reloading |
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| CN110778416A (en) * | 2019-09-26 | 2020-02-11 | 湖北三江航天红林探控有限公司 | Pulse type attitude control thruster based on shared combustion chamber |
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Application publication date: 20190507 |