CN204900103U - Mechanical type lotion propellant rocket engine flame arrestor - Google Patents
Mechanical type lotion propellant rocket engine flame arrestor Download PDFInfo
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- CN204900103U CN204900103U CN201520523429.9U CN201520523429U CN204900103U CN 204900103 U CN204900103 U CN 204900103U CN 201520523429 U CN201520523429 U CN 201520523429U CN 204900103 U CN204900103 U CN 204900103U
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- piston
- storage tank
- pasty propellant
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Abstract
The utility model discloses a mechanical type lotion propellant rocket engine flame arrestor, including being provided with the storage tank connecting portion that the lotion propellant goes out the medicine passageway, go out the piston shell that the medicine end linked firmly with the storage tank connecting portion, outer wall and internal face are formed by the face of cylinder of different diameters, and the major diameter face of cylinder of outer wall and piston shell inner wall sliding sealed fit's piston, spring on the minor diameter face of cylinder of cover wall outside the piston, one end links firmly with the piston shell, the other end stretch into in the piston and with the major diameter face of cylinder sliding sealed fit of inner surface of the piston face, and by the spacing lotion propellant gas generator of the step face between the minor diameter face of cylinder on the inner surface of the piston face and the major diameter face of cylinder, fix the porose disc seat that advances medicine mouth end at lotion propellant gas generator, the utility model discloses the principle is simple, the reliable operation, and low cost, the anti -backfire is effectual, and structural configuration is reasonable, and easily realizes microminiaturization.
Description
Technical field
The utility model belongs to rocket motor technical field, particularly a kind of mechanical type Pasty Propellant Rocket Engine fireproof tempering device.
Background technique
The power plant that current astrovehicle or space launch vehicle use, the overwhelming majority is liquid prpellant rocket and solid engine.In the process of development liquid rocket motor, encounter the difficulty of the aspects such as not easily storage, severe toxicity, deep-etching, inflammable and explosive, environmental pollution, solid propellant rocket obtains large development owing to overcoming above shortcoming, but liquid engine specific impulse is higher, adjustable thrust saves, and the advantage of the aspects such as energy relight is but that solid propellant is unapproachable.Paste propellant agent, as novel propellant agent important focus in recent years, causes the great interest of various countries expert.This kind of propellant agent had both overcome that SOLID PROPELLANT COMBUSTION speed is difficult to STOCHASTIC CONTROL, motor is difficult to the shortcoming that repeatedly starts, overcame again the shortcoming of low, the depot difference of liquid propellant density.Pasty propellant has than leaping high, and good manufacturability, easily stores, and can realize thrust and regulate and the repeatedly advantage such as startup, more and more be subject to the attention of countries in the world.
The thrust realizing lotion rocket motor regulates, and just must control the flow of propellant agent, stops working even and restarts.And when flame-out, must prevent flame from propagating in propellant tank, the danger of exploding to prevent propellant tank.Therefore, fireproof tempering device is safety installations necessary on lotion rocket motor.
Backfireproof design or device have two kinds, and a kind of is the backfireproof radial design propellant energy properties pipeline utilizing pasty propellant, and when pipe radius is less than backfireproof radius, shortage of heat is propagated with the continuation of flame support, thus reaches anti-backfire object.Its advantage does not need any special device of design just can realize backfireproof; And shortcoming also clearly, because backfireproof radius is general all very little, usually only have several millimeters, conveying has a large amount of energy ezpenditure, nor can realize large-scale Flow-rate adjustment.Another kind installs special diaphragm of rubber in the gap inlet location of modulating valve, when modulating valve gap increases, between diaphragm and valve body wall, forms gap, ensures that pasty propellant is continuous, stops flame backflow.Its shortcoming is mainly comparatively harsh to the selection of diaphragm of rubber material, and backfireproof effect is not ideal.
Model utility content
It is simple that the purpose of this utility model is to provide a kind of principle, reliable operation, and with low cost, backfireproof is effective, and topology layout is reasonable, and is easy to the mechanical type Pasty Propellant Rocket Engine fireproof tempering device realizing microminaturization.
The technical solution realizing the utility model object is:
A kind of mechanical type Pasty Propellant Rocket Engine fireproof tempering device, comprising:
Be provided with the storage tank joint of pasty propellant drug passage,
The piston be connected with storage tank joint medicine outlet end,
Outer wall and internal face form by the cylndrical surface of different-diameter, and the piston that the large diameter cylindrical surface of outer wall coordinates with the slipper seal of piston inwall,
Be enclosed within the spring on the small-diameter circular cylinder in piston outer wall face,
One end and piston are connected, and the other end to stretch in piston and coordinates with the large diameter cylindrical surface slipper seal 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,
Be fixed on the porose disc seat of pasty propellant gas generator feeding opening end;
Wherein, spring two ends by the step surface on piston outer wall face between small-diameter circular cylinder and large diameter cylindrical surface and pasty propellant gas generator spacing; Piston has the state blocking storage tank joint pasty propellant drug passage.
The utility model compared with prior art, its remarkable advantage:
(1) the utility model utilizes the compression of spring to realize complicated Pasty Propellant Rocket Engine function of preventing back-fire, and principle is simple, and reliable operation, with low cost, backfireproof is effective.
(2) piston of the present utility model is subject to the common constraint of piston and gas generator, not easily offsets during piston movement, is convenient to installation and removal.
(3) parts such as gas generator are placed in spring inner by the utility model, make compact structure, take up room less, are easy to realize microminaturization.
(4) the utility model component can be obtained by simple machining, connection and reasonable arrangement, are convenient to install.
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model mechanical type Pasty Propellant Rocket Engine fireproof tempering device.
Embodiment
A kind of mechanical type Pasty Propellant Rocket Engine of the utility model fireproof tempering device, comprising:
What be provided with pasty propellant drug passage comprises storage tank joint 1,
The piston 6 be connected with storage tank joint 1 medicine outlet end,
Outer wall and internal face form by the cylndrical surface of different-diameter, and the piston 2 that the large diameter cylindrical surface of outer wall coordinates with the slipper seal of piston 6 inwall,
Be enclosed within the spring 4 on the small-diameter circular cylinder of piston 2 outer wall,
One end and piston 6 are connected, the other end to stretch in piston 2 and coordinates with the large diameter cylindrical surface slipper seal of piston 2 internal face, and by the spacing pasty propellant gas generator 7 of the step surface on piston 2 internal face between small-diameter circular cylinder and large diameter cylindrical surface
Be fixed on the porose disc seat 5 of pasty propellant gas generator 7 feeding opening end;
Wherein, spring 4 two ends by the step surface in piston 2 outer wall between small-diameter circular cylinder and large diameter cylindrical surface and pasty propellant gas generator 7 spacing; Piston 2 has the state blocking storage tank joint 1 pasty propellant drug passage.
Pasty propellant gas generator 7 is connected by the flange arrangement outside end and piston 6.
Flange arrangement and piston 6 are connected by pin 8.
The two ends of spring 4 are spacing by the step surface on the flange arrangement of pasty propellant gas generator 7 and piston 2 outer wall between small-diameter circular cylinder and large diameter cylindrical surface.
Medicine outlet end and the piston 6 of storage tank joint 1 are connected by screw thread, piston 6 and piston 2 are all spacing by the step surface of the medicine outlet end of storage tank joint 1, and piston 2 has the state blocking storage tank joint 1 pasty propellant drug passage when spacing by the step surface of storage tank joint 1 medicine outlet end.
Spring 4 and piston 2 outer wall are provided with pad 3 between small-diameter circular cylinder and large diameter cylindrical surface.
Its working principle is:
When motor needs work, propellant agent in propellant tank is squeezed, under the effect of extruding force, promote piston 2, under the constraint of piston 6 and pasty propellant gas generator 7, piston 2 moves forward, spring 4 is compressed, and piston 2 is separated with storage tank joint 1, is opened by the pasty propellant drug passage that piston 2 blocks, pasty propellant flows out from pasty propellant drug passage, and through piston 2 and porose disc seat 5 also final inflow pasty propellant gas generator 7.
When pasty propellant stops getting into, extruding force disappears, now recovered deformation by the spring 4 compressed, under the effect of deformation force, promote piston 2 and move backward, prop up storage tank joint 1, pasty propellant drug passage is again by piston 2 shutoff, pasty propellant storage tank 1 and pasty propellant gas generator 7 are separated, the flame effectively avoiding pasty propellant burning generation is back in storage tank, and motor is blasted.
Embodiment:
Composition graphs 1:
A kind of mechanical type Pasty Propellant Rocket Engine fireproof tempering device, comprises storage tank joint 1, piston 2, pad 3, spring 4, porose disc seat 5, piston 6 and pasty propellant gas generator 7; Storage tank joint 1 medicine outlet is stretched in one end of piston 6, and is threaded with storage tank joint 1; The outer wall of piston 2 and inwall are by the different cylndrical surface composition of two sections of diameters, piston 2 is placed in piston 6, the large diameter cylindrical surface of its outer wall coordinates with piston 6 slipper seal, and spacing by the annular table terrace in storage tank joint 1, and there is the location status blocking storage tank joint 1 drug passage; On the small-diameter circular cylinder of piston 2 outer wall, cover has spring 4, and the step surface between spring 4 and the large and small diameter circle cylinder of piston 2 inwall is provided with pad 3; One end arranged outside of pasty propellant gas generator 7 has flange arrangement, flange arrangement is connected by pin 8 and piston 6, the other end stretches in piston 2, and coordinate with the large diameter cylindrical surface slipper seal of piston 2 internal face, and spacing by the step surface between the large and small diameter circle cylinder of piston 2 internal face, porose disc seat 5 is fixedly connected on the propellant agent inlet of pasty propellant gas generator 7.
Claims (9)
1. a mechanical type Pasty Propellant Rocket Engine fireproof tempering device, is characterized in that: comprising:
Be provided with the storage tank joint (1) of pasty propellant drug passage,
The piston (6) be connected with storage tank joint (1) medicine outlet end,
Outer wall and internal face form by the cylndrical surface of different-diameter, and the piston (2) that the large diameter cylindrical surface of outer wall coordinates with piston (6) inwall slipper seal,
Be enclosed within the spring (4) on the small-diameter circular cylinder of piston (2) outer wall,
One end and piston (6) are connected, the other end to stretch in piston (2) and coordinates with the large diameter cylindrical surface slipper seal of piston (2) internal face, and by the spacing pasty propellant gas generator (7) of the step surface on piston (2) internal face between small-diameter circular cylinder and large diameter cylindrical surface
Be fixed on the porose disc seat (5) of pasty propellant gas generator (7) feeding opening end;
Wherein, spring (4) two ends by the step surface in piston (2) outer wall between small-diameter circular cylinder and large diameter cylindrical surface and pasty propellant gas generator (7) spacing; Piston (2) has the state blocking storage tank joint (1) pasty propellant drug passage.
2. mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 1, is characterized in that: described pasty propellant gas generator (7) is connected by the flange arrangement outside end and piston (6).
3. mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 2, is characterized in that: described flange arrangement and piston (6) are connected by pin (8).
4. the mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to Claims 2 or 3, is characterized in that: the two ends of described spring (4) are spacing by the step surface on the flange arrangement of pasty propellant gas generator (7) and piston (2) outer wall between small-diameter circular cylinder and large diameter cylindrical surface.
5. the mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 1 or 2 or 3, it is characterized in that: medicine outlet end and the piston (6) of described storage tank joint (1) are connected by screw thread, piston (6) and piston (2) are all spacing by the step surface of the medicine outlet end of storage tank joint (1), and piston (2) has the state blocking storage tank joint (1) pasty propellant drug passage when spacing by the step surface of storage tank joint (1) medicine outlet end.
6. mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 4, it is characterized in that: medicine outlet end and the piston (6) of described storage tank joint (1) are connected by screw thread, piston (6) and piston (2) are all spacing by the step surface of the medicine outlet end of storage tank joint (1), and piston (2) has the state blocking storage tank joint (1) pasty propellant drug passage when spacing by the step surface of storage tank joint (1) medicine outlet end.
7. the mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 1 or 2 or 3 or 6, is characterized in that: described spring (4) and piston (2) outer wall are provided with pad (3) between small-diameter circular cylinder and large diameter cylindrical surface.
8. mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 4, is characterized in that: described spring (4) and piston (2) outer wall are provided with pad (3) between small-diameter circular cylinder and large diameter cylindrical surface.
9. mechanical type Pasty Propellant Rocket Engine fireproof tempering device according to claim 5, is characterized in that: described spring (4) and piston (2) outer wall are provided with pad (3) between small-diameter circular cylinder and large diameter cylindrical surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520523429.9U CN204900103U (en) | 2015-07-17 | 2015-07-17 | Mechanical type lotion propellant rocket engine flame arrestor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520523429.9U CN204900103U (en) | 2015-07-17 | 2015-07-17 | Mechanical type lotion propellant rocket engine flame arrestor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204900103U true CN204900103U (en) | 2015-12-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520523429.9U Withdrawn - After Issue CN204900103U (en) | 2015-07-17 | 2015-07-17 | Mechanical type lotion propellant rocket engine flame arrestor |
Country Status (1)
| Country | Link |
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| CN (1) | CN204900103U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105020053A (en) * | 2015-07-17 | 2015-11-04 | 南京理工大学 | Anti-backfire device for mechanical pasty propellant rocket engine |
| CN106526066A (en) * | 2016-11-07 | 2017-03-22 | 南京理工大学 | A hot-start experiment apparatus for a paste gas generator |
| CN113390291A (en) * | 2021-05-21 | 2021-09-14 | 上海新力动力设备研究所 | BPN tablet type porous ignition integrated structure of front medicine baffle of fuel gas generator |
-
2015
- 2015-07-17 CN CN201520523429.9U patent/CN204900103U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105020053A (en) * | 2015-07-17 | 2015-11-04 | 南京理工大学 | Anti-backfire device for mechanical pasty propellant rocket engine |
| CN106526066A (en) * | 2016-11-07 | 2017-03-22 | 南京理工大学 | A hot-start experiment apparatus for a paste gas generator |
| CN113390291A (en) * | 2021-05-21 | 2021-09-14 | 上海新力动力设备研究所 | BPN tablet type porous ignition integrated structure of front medicine baffle of fuel gas generator |
| CN113390291B (en) * | 2021-05-21 | 2023-07-14 | 上海新力动力设备研究所 | BPN tablet type porous ignition integrated structure of front baffle plate of gas generator |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20151223 Effective date of abandoning: 20170804 |
|
| AV01 | Patent right actively abandoned |