CN207598370U - Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down - Google Patents
Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down Download PDFInfo
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- CN207598370U CN207598370U CN201721582149.0U CN201721582149U CN207598370U CN 207598370 U CN207598370 U CN 207598370U CN 201721582149 U CN201721582149 U CN 201721582149U CN 207598370 U CN207598370 U CN 207598370U
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- return line
- cavity volume
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Abstract
Propellant temperature control equipment, the liquid rail attitude control engine technical field being related in space flight Push Technology field before valve after a kind of rail attitude control engine is shut down；Including cavity volume, engine electromagnetic valve, circulating pump and return line before tank, output pipe, valve；Wherein, tank is hollow spheres structure；One end of cavity volume is sequentially communicated before tank, output pipe and valve；Engine electromagnetic valve is fixedly mounted on the top of cavity volume before valve, and is connected with cavity volume before valve；Engine electromagnetic valve is connected with external thrust room；One end of return line is connected with cavity volume before valve；The other end of return line is connected with output pipe；Circulating pump is arranged on return line, and close to the junction of return line and cavity volume before valve；The utility model effectively avoids the propellant caused by shutting down heat and returning the reasons such as leaching, Aerodynamic Heating from overheating, and the propellant supercooling caused by the reasons such as space cryogenic environment cooling is avoided to freeze, to improve the safety of engine, reliability.
Description
Technical field
The utility model is related to the liquid rail attitude control engine technical field in a kind of space flight Push Technology field, particularly
Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down.
Background technology
Rail attitude control engine is mostly using compressed gas squash type method of supplying, i.e., the propellant in tank is in compressed gas
Enter output pipe 2 under the action of pressure, and before being delivered to engine electromagnetic valve.When solenoid valve is opened, propellant enters thrust
Room, engine are started to work.When solenoid valve is closed, engine is shut down.After engine is shut down, propellant stops stream before solenoid valve
It is dynamic, it is influenced at this point, being shut down heat by engine and returning the factors such as leaching, Aerodynamic Heating, the cooling of space cryogenic environment, before valve may being led to
Certain part propellant temperatures are substantially increased or decline.
For rail attitude control engine, propellant temperature is excessively high, and propellant will be caused to gasify or decompose, influence engine
It works normally, explosion accident may occur under extreme case；Propellant temperature is too low, and propellant will be caused to freeze, make engine
It can not start.Therefore, by propellant temperature control in safe range be ensure that rail attitude control engine securely and reliably works must
Want condition.
It is traditional prevent engine shut down after before valve the excessively high method of propellant temperature be to add heat-insulated or radiator, lead to
It crosses the heat-insulated shutdown heat that reduces and returns the heating of leaching or Aerodynamic Heating to propellant before valve, pass through heat dissipation and reduce propellant and correlation before valve
The Wen Sheng of structure.It is traditional prevent engine shut down after before valve the too low method of propellant temperature be to carry out local electrical heating and increasing
If insulating layer.
Successful application was obtained in the development of the above-mentioned in-orbit attitude control engine of conventional method.But in certain special applications fields
(e.g., the temperature of propellant controls in re-generatively cooled thrust chamber cooling duct before valve, for another example, because engine structure and weight limit for conjunction
System can not set heat-insulated or radiator), conventional method can not use.
Utility model content
The purpose of the utility model is to overcome the above-mentioned deficiency of the prior art, provide after a kind of rail attitude control engine shuts down
Propellant temperature control equipment before valve, the utility model are effectively controlled and are promoted (in cavity volume, runner) before valve after engine is shut down
Agent temperature, so as to which the propellant caused by shutting down heat and returning the reasons such as leaching, Aerodynamic Heating be avoided to overheat, and avoid because of space deep cooling ring
Propellant supercooling is freezed caused by the reasons such as border cooling, to improve the safety of engine, reliability.
The above-mentioned purpose of the utility model is achieved by following technical solution：
Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down, including holding before tank, output pipe, valve
Chamber, engine electromagnetic valve, circulating pump and return line；Wherein, tank is hollow spheres structure；Before tank, output pipe and valve
One end of cavity volume is sequentially communicated；Engine electromagnetic valve is fixedly mounted on the top of cavity volume before valve, and is connected with cavity volume before valve；Start
Electromechanical magnet valve is connected with external thrust room；One end of return line is connected with cavity volume before valve；The other end of return line and output
Pipeline connection；Circulating pump is arranged on return line, and close to the junction of return line and cavity volume before valve.
Propellant temperature control equipment, the tank include gas before valve after a kind of above-mentioned rail attitude control engine is shut down
Body entrance, air bag and propellant；Wherein, gas access is arranged on the outer wall of tank, and gas access in an axial direction with output pipe
It is symmetrical relative to tank；Air bag is attached to the inner wall of tank；And gas access is corresponded to positioned at the center of air bag；Air bag and gas
Body entrance connects；Propellant is placed in the inside of tank, and between the outside of air bag and the other inner walls of tank.
The propellant temperature control equipment before valve after a kind of above-mentioned rail attitude control engine is shut down, when external compression gas leads to
It crosses gas access and enters air bag, air bag expansion squeezes propellant and flows into output pipe from tank.
The propellant temperature control equipment before valve after a kind of above-mentioned rail attitude control engine is shut down, when circulation pump and hair
When motivation solenoid valve is opened, propellant flows out to outer successively through cavity volume and engine electromagnetic valve before tank, output pipe, valve
Portion's thrust chamber.
The propellant temperature control equipment before valve after a kind of above-mentioned rail attitude control engine is shut down, when engine electromagnetic valve closes
It closes and when circulating pump is opened, for propellant successively through cavity volume and return line before tank, output pipe, valve, cocurrent returns output pipe；
Such iterative cycles.
The propellant temperature control equipment before valve after a kind of above-mentioned rail attitude control engine is shut down, the one of the return line
End is connected with cavity volume before valve；The other end of return line is connected with tank；When engine electromagnetic valve is closed and circulating pump is opened,
Propellant is successively through cavity volume and return line before tank, output pipe, valve, and flow back to tank；Such iterative cycles.
Propellant temperature control equipment, the return line diameter before valve after a kind of above-mentioned rail attitude control engine is shut down
For 10-30mm；The pressure capability of circulating pump is 8kPa-1mPa；Tank maximum volume is 450-550L.
The propellant temperature control equipment before valve after a kind of above-mentioned rail attitude control engine is shut down, in the feelings that circulating pump is opened
Under condition, the maximum flow rate of propellant is 800-1000g/s.
The propellant temperature control equipment before valve after a kind of above-mentioned rail attitude control engine is shut down, when air bag is completely filled with
When, air bag accounts for tank internal capacity more than or equal to 90%.
The utility model has the following advantages that compared with prior art：
(1) the utility model increases circulating pump and return line in conventional tube, after rail attitude control engine is shut down
Propellant temperature control is prevented in safe range because propellant overheat or supercooling cause engine safe thing occur before valve before valve
Therefore or functional fault；
(2) the utility model employs return line, is led for placing propellant overheat or supercooling, simplifies or remove from heat-insulated
Structure, radiator structure, electric heater unit and insulation construction；
(3) the utility model employs circulating pump, the flow velocity of propellant can be adjusted according to actual temperature link,
Increase or the flow velocity for reducing propellant, propellant temperature is controlled in safety before valve after the very effective shutdown by rail attitude control engine
In the range of.
Description of the drawings
For the utility model propellant temperature control device, the first return line connects schematic diagram to Fig. 1；
Fig. 2 connects schematic diagram for second of return line of the utility model propellant temperature control device.
Specific embodiment
The utility model is described in further detail in the following with reference to the drawings and specific embodiments：
The purpose of this utility model：In application scenario as much as possible, propellant before valve after rail attitude control engine is shut down
(including the propellant in re-generatively cooled cooling channel of motor) temperature is controlled in safe range.
Propellant (is sent out including re-generatively cooled before valve after being shut down the utility model proposes a kind of new control rail attitude control engine
Propellant in motivation cooling duct) temperature device, can functionally replace above-mentioned conventional propellant temperature control equipment, and
It is suitable for more application scenarios.The characteristics of this method is by setting circulating pump 5, when engine electromagnetic valve 4 is closed, is started
Circulating pump 5, the propellant 1-3 and propellant 1-3 in output pipe 2 is circulated before making valve, passes through the recycle stream of propellant 1-3
It is dynamic to take away excessive propellant 1-3 before engine electromagnetic valve 4 heat or cold, so as to which propellant temperature control before valve pacified
In gamut.This Method And Principle is simple, is easy to Project Realization.
For propellant temperature control device, the first return line connects schematic diagram as shown in Figure 1, as seen from the figure, plants rail appearance
Propellant temperature control equipment before valve after control engine is shut down, including cavity volume 3, engine electromagnet before tank 1, output pipe 2, valve
Valve 4, circulating pump 5 and return line 6；Wherein, tank 1 is hollow spheres structure；Cavity volume 3 before tank 1, output pipe 2 and valve
One end is sequentially communicated；Engine electromagnetic valve 4 is fixedly mounted on the top of cavity volume 3 before valve, and is connected with cavity volume before valve 3；Engine
Solenoid valve 4 is connected with external thrust room；One end of return line 6 is connected with cavity volume before valve 3；The other end of return line 6 with it is defeated
Go out pipeline 2 to connect；Circulating pump 5 is arranged on return line 6, and close to the junction of return line 6 and cavity volume 3 before valve.
Wherein, tank 1 includes gas access 1-1, air bag 1-2 and propellant 1-3；Wherein, gas access 1-1 is arranged on storage
The outer wall of case 1, and gas access 1-1 is symmetrical relative to tank 1 with output pipe 2 in an axial direction；Air bag 1-2 is attached to tank 1
Inner wall；And gas access 1-1 is corresponded to positioned at the center of air bag 1-2；Air bag 1-2 is connected with gas access 1-1；Propellant 1-
3 are placed in the inside of tank 1, and between 1 other inner walls of outside and tank of air bag 1-2.When external compression gas passes through gas
Body entrance 1-1 enters air bag 1-2, and air bag 1-2 expansions squeeze propellant 1-3 and flow into output pipe 2 from tank 1.
When circulating pump 5 is closed and engine electromagnetic valve 4 is opened, propellant 1-3 is successively through tank 1, output pipe 2, valve
Preceding cavity volume 3 and engine electromagnetic valve 4, and flow out to external thrust room.When engine electromagnetic valve 4 is closed and circulating pump 5 is opened,
For propellant 1-3 successively through cavity volume 3 and return line 6 before tank 1, output pipe 2, valve, cocurrent returns output pipe 2；So repeatedly
Cycle.
It is illustrated in figure 2 second of return line connection schematic diagram of propellant temperature control device, as seen from the figure, return duct
The one end on road 6 is connected with cavity volume before valve 3；The other end of return line 6 is connected with tank 1；When engine electromagnetic valve 4 is closed and is followed
When ring pump 5 is opened, propellant 1-3 is successively through cavity volume 3 and return line 6 before tank 1, output pipe 2, valve, and flow back to tank 1；
Such iterative cycles.
Wherein, 6 a diameter of 10-30mm of return line；The pressure capability of circulating pump 5 is 8kPa-1mPa；Tank 1 is maximum to be held
Product is 450-550L.In the case where circulating pump 5 is opened, the maximum flow rate of propellant 1-3 is 800-1000g/s.As air bag 1-2
When being completely filled with, air bag 1-2 accounts for 1 internal capacity of tank more than or equal to 90%.
The embodiment of the utility model is：The suitable position of cavity volume 3 accesses a circulating pump 5 before valve, and passes through one
The outlet of circulating pump 5 is connected to the road output pipe 2 or propellant tank 1 by section propellant return line 6, forms propellant reflux
Road.When engine works, engine electromagnetic valve 4 is opened, and circulating pump 5 is closed, and the propellant in tank 1 is in the extruding of compressed gas
Before being supplied to engine electromagnetic valve 4 by cavity volume 3 before output pipe 2 and valve down, and pass through solenoid valve 4 into thrust chamber.Start
After machine is shut down, engine electromagnetic valve 4 is closed, and circulating pump 5 starts, and propellant enters cycle after cavity volume before valve 3 in output pipe 2
Pump 5, and pass through propellant return line 6 and be back to output pipe 2 or propellant tank 1, propellant carries out closed loop cycle flowing.
It is flowed by the closed loop cycle of propellant, the excessive heat of propellant before valve (or cold) is taken away, thus by propellant before valve
Temperature is controlled in safe range.
When the heat (or cold) that propellant need to be taken away before valve is few, propellant return line 6 can be connected to efferent duct
Road 2；When the heat (or cold) that propellant need to be taken away before valve is more, propellant return line 6 can be connected to propellant
Tank 1.The outlet link position of return line 6 can be determined according to actual needs.
The content not being described in detail in the utility model specification belongs to the known technology of those skilled in the art.
Claims (9)
1. a kind of propellant temperature control equipment before valve after rail attitude control engine is shut down, it is characterised in that：Including tank (1), defeated
Go out cavity volume (3), engine electromagnetic valve (4), circulating pump (5) and return line (6) before pipeline (2), valve；Wherein, during tank (1) is
Empty chondritic；One end of cavity volume (3) is sequentially communicated before tank (1), output pipe (2) and valve；Engine electromagnetic valve (4) is fixed
The top of cavity volume (3) before valve, and connected with cavity volume before valve (3)；Engine electromagnetic valve (4) is connected with external thrust room；
One end of return line (6) is connected with cavity volume before valve (3)；The other end of return line (6) is connected with output pipe (2)；Cycle
Pump (5) is arranged on return line (6), and close to the junction of return line (6) and cavity volume (3) before valve.
Propellant temperature control equipment, feature before valve after 2. a kind of rail attitude control engine according to claim 1 is shut down
It is：The tank (1) includes gas access (1-1), air bag (1-2) and propellant (1-3)；Wherein, gas access (1-1)
The outer wall of tank (1) is arranged on, and gas access (1-1) is symmetrical relative to tank (1) with output pipe (2) in an axial direction；Air bag
(1-2) is attached to the inner wall of tank (1)；And gas access (1-1) is corresponding positioned at the center of air bag (1-2)；Air bag (1-2)
It is connected with gas access (1-1)；Propellant (1-3) is placed in the inside of tank (1), and positioned at the outside of air bag (1-2) and tank
(1) between other inner walls.
Propellant temperature control equipment, feature before valve after 3. a kind of rail attitude control engine according to claim 2 is shut down
It is：When external compression gas by gas access (1-1) into air bag (1-2), air bag (1-2) expansion squeezes propellant (1-
3) output pipe (2) is flowed into from tank (1).
Propellant temperature control equipment, feature before valve after 4. a kind of rail attitude control engine according to claim 3 is shut down
It is：When circulating pump (5) is closed and engine electromagnetic valve (4) is opened, propellant (1-3) is successively through tank (1), output pipe
(2), cavity volume (3) and engine electromagnetic valve (4) before valve, and flow out to external thrust room.
Propellant temperature control equipment, feature before valve after 5. a kind of rail attitude control engine according to claim 4 is shut down
It is：When engine electromagnetic valve (4) is closed and circulating pump (5) is opened, propellant (1-3) is successively through tank (1), output pipe
(2), cavity volume (3) and return line (6) before valve, cocurrent return output pipe (2)；Such iterative cycles.
Propellant temperature control equipment before valve after 6. a kind of rail attitude control engine according to one of claim 1-5 is shut down,
It is characterized in that：One end of the return line (6) is connected with cavity volume before valve (3)；The other end and tank of return line (6)
(1) it connects；When engine electromagnetic valve (4) is closed and circulating pump (5) is opened, propellant (1-3) is successively through tank (1), output
Cavity volume (3) and return line (6) before pipeline (2), valve, and flow back to tank (1)；Such iterative cycles.
Propellant temperature control equipment, feature before valve after 7. a kind of rail attitude control engine according to claim 6 is shut down
It is：The a diameter of 10-30mm of the return line (6)；The pressure capability of circulating pump (5) is 8kPa-1mPa；Tank (1) is maximum
Volume is 450-550L.
Propellant temperature control equipment, feature before valve after 8. a kind of rail attitude control engine according to claim 7 is shut down
It is：In the case where circulating pump (5) is opened, the maximum flow rate of propellant (1-3) is 800-1000g/s.
Propellant temperature control equipment, feature before valve after 9. a kind of rail attitude control engine according to claim 8 is shut down
It is：When air bag (1-2) is completely filled with, air bag (1-2) accounts for tank (1) internal capacity more than or equal to 90%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721582149.0U CN207598370U (en) | 2017-11-23 | 2017-11-23 | Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721582149.0U CN207598370U (en) | 2017-11-23 | 2017-11-23 | Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207598370U true CN207598370U (en) | 2018-07-10 |
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ID=62760571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721582149.0U Active CN207598370U (en) | 2017-11-23 | 2017-11-23 | Propellant temperature control equipment before valve after a kind of rail attitude control engine is shut down |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207598370U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107795407A (en) * | 2017-11-23 | 2018-03-13 | 北京航天动力研究所 | Propellant temperature control device before valve after a kind of rail attitude control engine is shut down |
| CN110274312A (en) * | 2019-06-28 | 2019-09-24 | 彭从文 | Type of respiration outdoor machine of air-conditioner |
-
2017
- 2017-11-23 CN CN201721582149.0U patent/CN207598370U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107795407A (en) * | 2017-11-23 | 2018-03-13 | 北京航天动力研究所 | Propellant temperature control device before valve after a kind of rail attitude control engine is shut down |
| CN110274312A (en) * | 2019-06-28 | 2019-09-24 | 彭从文 | Type of respiration outdoor machine of air-conditioner |
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