CN105020053B - Mechanical Pasty Propellant Rocket Engine fireproof tempering device - Google Patents
Mechanical Pasty Propellant Rocket Engine fireproof tempering device Download PDFInfo
- Publication number
- CN105020053B CN105020053B CN201510422620.9A CN201510422620A CN105020053B CN 105020053 B CN105020053 B CN 105020053B CN 201510422620 A CN201510422620 A CN 201510422620A CN 105020053 B CN105020053 B CN 105020053B
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- Prior art keywords
- piston
- pasty propellant
- connecting portion
- pasty
- storage tank
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Abstract
The invention discloses a kind of mechanical Pasty Propellant Rocket Engine fireproof tempering device, storage tank connecting portion including being provided with pasty propellant drug passage, the piston being connected with storage tank connecting portion medicine outlet end, outside wall surface and internal face are constituted by the face of cylinder of different-diameter, and the large diameter cylindrical surface of outside wall surface is slidingly sealed the piston of cooperation with piston inwall, it is enclosed on the spring on the small-diameter circular cylinder in piston outer wall face, one end is connected with piston, the other end stretches into piston and is slidingly sealed cooperation with the large diameter cylindrical surface in piston inner wall face, and by the spacing pasty propellant gas generator of the step surface on piston inner wall face between small-diameter circular cylinder and large diameter cylindrical surface, it is fixed on the porose disc seat at pasty propellant gas generator feeding opening end；The principle of the invention is simple, and reliable operation is with low cost, and anti-backfire effect is good, and topology layout rationally, and is easily achieved microminaturization.
Description
Technical field
The invention belongs to rocket engine technical field, particularly a kind of mechanical Pasty Propellant Rocket Engine is prevented back
Fiery device.
Background technology
The power set that current spacecraft or space launch vehicle is used, the overwhelming majority is liquid prpellant rocket
And solid engine.During development liquid rocket engine, encounter and be difficult storage, hypertoxic, strong corruption
Difficulty in terms of erosion, inflammable and explosive, environmental pollution, solid propellant rocket obtains larger hair due to overcoming disadvantage mentioned above
Exhibition, but liquid engine specific impulse is higher, adjustable thrust section, and the advantage that can be repeated in terms of lighting a fire is that solid propellant is difficult to reach
Arrive.Paste propellant causes the great interest of various countries expert as new one important focus of propellant in recent years.It is this kind of
Propellant had both overcome SOLID PROPELLANT COMBUSTION speed and has been difficult to the shortcoming that STOCHASTIC CONTROL, engine are difficult to repeatedly start, and overcame again
Liquid propellant density is low, depot poor shortcoming.Pasty propellant has than leaping high, good manufacturability, easily storage, can be achieved
The advantages of thrust is adjusted and repeatedly started, is increasingly paid attention to by countries in the world.
Realize lotion rocket engine thrust regulation, must just control the flow of propellant, even stop working with again
It is new to start.And when flame-out, it is necessary to prevent that flame from propagating into propellant tank, to prevent danger that propellant tank explodes.
Therefore, fireproof tempering device is necessary safety device on lotion rocket engine.
Anti-backfire is designed or device has two kinds, and a kind of is the anti-backfire radial design propellant energy properties using pasty propellant
Pipeline, when pipe radius is less than anti-backfire radius, shortage of heat is propagated with the continuation of flame support, so as to reach anti-backfire
Purpose.Its advantage is need not to design any special device to can be achieved with anti-backfire；And shortcoming is it is also obvious that because anti-backfire
Radius is usually quite small, and generally only several millimeters, conveying has a substantial amounts of energy expenditure, nor can realize large-scale
Flow-rate adjustment.Another is that special diaphragm of rubber is installed at the slot entrance position of regulating valve, when regulating valve gap increases,
Gap is formed between diaphragm and valve body wall, it is ensured that pasty propellant is continuous, prevent flame from flowing back.Its shortcoming is mainly to rubber
The selection of diaphragm material is more harsh, and anti-backfire effect is not ideal.
The content of the invention
Simple it is an object of the invention to provide a kind of principle, reliable operation is with low cost, and anti-backfire effect is good, structure
It is rationally distributed, and it is easily achieved the mechanical Pasty Propellant Rocket Engine fireproof tempering device of microminaturization.
The technical solution for realizing the object of the invention is：
A kind of mechanical Pasty Propellant Rocket Engine fireproof tempering device, including：
The storage tank connecting portion of pasty propellant drug passage is provided with,
The piston being connected with storage tank connecting portion medicine outlet end,
Outside wall surface and internal face are constituted by the face of cylinder of different-diameter, and outside the large diameter cylindrical surface and piston of outside wall surface
Shell inwall is slidingly sealed the piston of cooperation,
The spring on the small-diameter circular cylinder in piston outer wall face is enclosed on,
One end is connected with piston, and the other end stretches into piston and close with the large diameter cylindrical surface slip in piston inner wall face
Envelope coordinates, and by the spacing pasty propellant of the step surface on piston inner wall face between small-diameter circular cylinder and large diameter cylindrical surface
Gas generator,
It is fixed on the porose disc seat at pasty propellant gas generator feeding opening end；
Wherein, the two ends of spring by the step surface on piston outer wall face between small-diameter circular cylinder and large diameter cylindrical surface and
Pasty propellant gas generator is spacing；Piston has the state for blocking storage tank connecting portion pasty propellant drug passage.
The present invention compared with prior art, its remarkable advantage：
(1) present invention realizes the Pasty Propellant Rocket Engine function of preventing back-fire of complexity using the compression of spring, former
Reason is simple, and reliable operation is with low cost, and anti-backfire effect is good.
(2) piston of the invention is not susceptible to partially by the common constraint of piston and gas generator during piston movement
Move, be easily installed and dismantle.
(3) parts such as gas generator are placed in spring inner by the present invention so that compact conformation, space-consuming is smaller, easily
In realizing microminaturization.
(4) parts of the present invention can be obtained by simply machining, and connection and reasonable arrangement is easily installed.
The present invention is described in further detail below in conjunction with the accompanying drawings.
Brief description of the drawings
Fig. 1 is the structural representation of mechanical Pasty Propellant Rocket Engine fireproof tempering device of the invention.
Embodiment
A kind of mechanical Pasty Propellant Rocket Engine fireproof tempering device of the present invention, including：
The storage tank connecting portion 1 of pasty propellant drug passage is provided with,
The piston 6 being connected with the medicine outlet end of storage tank connecting portion 1,
Outside wall surface and internal face are constituted by the face of cylinder of different-diameter, and outside the large diameter cylindrical surface and piston of outside wall surface
The inwall of shell 6 is slidingly sealed the piston 2 of cooperation,
The spring 4 on the small-diameter circular cylinder of the outside wall surface of piston 2 is enclosed on,
One end is connected with piston 6, and the other end is stretched into piston 2 and slided with the large diameter cylindrical surface of the internal face of piston 2
Dynamic sealing coordinates, and by the spacing lotion of the step surface on the internal face of piston 2 between small-diameter circular cylinder and large diameter cylindrical surface
Propellant gas generator 7,
It is fixed on the porose disc seat 5 at the feeding opening end of pasty propellant gas generator 7；
Wherein, the two ends of spring 4 are by the step surface in the outside wall surface of piston 2 between small-diameter circular cylinder and large diameter cylindrical surface
It is spacing with pasty propellant gas generator 7；Piston 2 has the shape for blocking the pasty propellant drug passage of storage tank connecting portion 1
State.
Pasty propellant gas generator 7 is connected by the flange arrangement on the outside of end and piston 6.
Flange arrangement is connected with piston 6 by pin 8.
The two ends of spring 4 are by small diameter cylinders on the flange arrangement of pasty propellant gas generator 7 and the outside wall surface of piston 2
Step surface between face and large diameter cylindrical surface is spacing.
The medicine outlet end of storage tank connecting portion 1 is connected with piston 6 by screw thread, and piston 6 and piston 2 are connected by storage tank
The step surface of the medicine outlet end of socket part 1 is spacing, and piston 2 has closure when spacing by the step surface of the medicine outlet end of storage tank connecting portion 1
The firmly state of the pasty propellant drug passage of storage tank connecting portion 1.
Pad 3 is provided between small-diameter circular cylinder and large diameter cylindrical surface in spring 4 and the outside wall surface of piston 2.
Its operation principle is：
When engine needs work, the propellant in propellant tank is squeezed, in the presence of extruding force, is promoted
Piston 2, under the constraint of piston 6 and pasty propellant gas generator 7, piston 2 is moved forward, and compresses spring 4, living
Plug 2 is separated with storage tank connecting portion 1, and the pasty propellant drug passage blocked by piston 2 is opened, and pasty propellant is pushed away from lotion
Enter in agent drug passage and flow out, and through piston 2 and porose disc seat 5 and finally flow into pasty propellant gas generator 7.
When pasty propellant stops getting into, extruding force disappears, and the spring 4 now compressed recovers deformation, in deformation force
In the presence of, promote piston 2 to be moved rearwards by, prop up storage tank connecting portion 1, pasty propellant drug passage is blocked by piston 2 again,
Pasty propellant storage tank 1 is separated with pasty propellant gas generator 7, effectively avoids what pasty propellant burning was produced
Flame is back in storage tank, engine is exploded.
Embodiment：
With reference to Fig. 1：
A kind of mechanical Pasty Propellant Rocket Engine fireproof tempering device, including storage tank connecting portion 1, piston 2, pad 3,
Spring 4, porose disc seat 5, piston 6 and pasty propellant gas generator 7；Storage tank connecting portion 1 is stretched into one end of piston 6
Medicine outlet, and be threadedly coupled with storage tank connecting portion 1；The outer wall of piston 2 is constituted with inwall by the different face of cylinder of two sections of diameters,
Piston 2 is placed in piston 6, and large diameter cylindrical surface and the piston 6 of its outside wall surface are slidingly sealed cooperation, and are connected by storage tank
Annular step surface in socket part 1 is spacing, and with the location status for blocking the drug passage of storage tank connecting portion 1；The outside wall surface of piston 2
Small-diameter circular cylinder on be cased with spring 4, the step surface between spring 4 and the large and small diameter face of cylinder of the inwall of piston 2 set
There is pad 3；Flange arrangement is provided with the outside of one end of pasty propellant gas generator 7, flange arrangement passes through pin 8 and piston
Shell 6 is connected, and the other end is stretched into piston 2, and is slidingly sealed cooperation with the large diameter cylindrical surface of the internal face of piston 2, and is lived
The step surface filled between the large and small diameter face of cylinder of 2 internal faces is spacing, and porose disc seat 5 is fixedly connected on pasty propellant combustion gas hair
At the propellant import of raw device 7.
Claims (5)
1. a kind of mechanical Pasty Propellant Rocket Engine fireproof tempering device, it is characterised in that：Including：
The storage tank connecting portion (1) of pasty propellant drug passage is provided with,
The piston (6) being connected with storage tank connecting portion (1) medicine outlet end,
Outside wall surface and internal face are constituted by the face of cylinder of different-diameter, and the large diameter cylindrical surface and piston of outside wall surface
(6) inwall is slidingly sealed the piston (2) of cooperation,
The spring (4) on the small-diameter circular cylinder of piston (2) outside wall surface is enclosed on,
One end and piston (6) are connected, the other end stretch into piston (2) and with the large diameter cylindrical surface of piston (2) internal face
Cooperation is slidingly sealed, and it is spacing by the step surface on piston (2) internal face between small-diameter circular cylinder and large diameter cylindrical surface
Pasty propellant gas generator (7),
It is fixed on the porose disc seat (5) at pasty propellant gas generator (7) feeding opening end；
Wherein, the two ends of spring (4) are by the step surface in piston (2) outside wall surface between small-diameter circular cylinder and large diameter cylindrical surface
It is spacing with pasty propellant gas generator (7)；Piston (2) leads to storage tank connecting portion (1) pasty propellant drug is blocked
The state in road；
The pasty propellant gas generator (7) is connected by the flange arrangement on the outside of end and piston (6)；The bullet
The two ends of spring (4) by small-diameter circular cylinder on the flange arrangement of pasty propellant gas generator (7) and piston (2) outside wall surface with
Step surface between large diameter cylindrical surface is spacing.
2. mechanical Pasty Propellant Rocket Engine fireproof tempering device according to claim 1, it is characterised in that：It is described
Flange arrangement is connected with piston (6) by pin (8).
3. mechanical Pasty Propellant Rocket Engine fireproof tempering device according to claim 1 or 2, it is characterised in that：
The medicine outlet end of the storage tank connecting portion (1) is connected with piston (6) by screw thread, and piston (6) and piston (2) are stored up
The step surface of the medicine outlet end of case connecting portion (1) is spacing, and piston (2) is spacing by the step surface of storage tank connecting portion (1) medicine outlet end
When there is the state of storage tank connecting portion (1) pasty propellant drug passage of blocking.
4. mechanical Pasty Propellant Rocket Engine fireproof tempering device according to claim 1 or 2, it is characterised in that：
Pad (3) is provided between small-diameter circular cylinder and large diameter cylindrical surface in the spring (4) and piston (2) outside wall surface.
5. mechanical Pasty Propellant Rocket Engine fireproof tempering device according to claim 3, it is characterised in that：It is described
Pad (3) is provided between small-diameter circular cylinder and large diameter cylindrical surface in spring (4) and piston (2) outside wall surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510422620.9A CN105020053B (en) | 2015-07-17 | 2015-07-17 | Mechanical Pasty Propellant Rocket Engine fireproof tempering device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510422620.9A CN105020053B (en) | 2015-07-17 | 2015-07-17 | Mechanical Pasty Propellant Rocket Engine fireproof tempering device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105020053A CN105020053A (en) | 2015-11-04 |
| CN105020053B true CN105020053B (en) | 2017-08-04 |
Family
ID=54410281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510422620.9A Expired - Fee Related CN105020053B (en) | 2015-07-17 | 2015-07-17 | Mechanical Pasty Propellant Rocket Engine fireproof tempering device |
Country Status (1)
| Country | Link |
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| CN (1) | CN105020053B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109209682B (en) * | 2018-09-19 | 2020-06-19 | 南京理工大学 | Motor-driven pasty propellant rocket engine backfire preventing device |
| CN111486022B (en) * | 2020-04-20 | 2021-07-23 | 西安宸极探索空间科技有限公司 | Anti-backfire device and combustion system |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2318963A (en) * | 1940-11-28 | 1943-05-11 | Arthur L Parker | Valve assembly |
| US2916046A (en) * | 1956-06-20 | 1959-12-08 | Clement J Turansky | Chatter-free check valve |
| EP2092183A4 (en) * | 2006-12-04 | 2013-03-27 | Firestar Engineering Llc | Spark-integrated propellant injector head with flashback barrier |
| WO2011005875A1 (en) * | 2009-07-07 | 2011-01-13 | Firestar Engineering Llc | Detonation wave arrestor |
| WO2013103427A2 (en) * | 2011-10-14 | 2013-07-11 | Firestar Engineering, Llc | Linear detonation wave diverter |
| CN204900103U (en) * | 2015-07-17 | 2015-12-23 | 南京理工大学 | Mechanical type lotion propellant rocket engine flame arrestor |
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2015
- 2015-07-17 CN CN201510422620.9A patent/CN105020053B/en not_active Expired - Fee Related
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| Publication number | Publication date |
|---|---|
| CN105020053A (en) | 2015-11-04 |
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Granted publication date: 20170804 Termination date: 20190717 |