CN110053789A - Variable thrust propulsion system and thrust change method - Google Patents
Variable thrust propulsion system and thrust change method Download PDFInfo
- Publication number
- CN110053789A CN110053789A CN201910483928.2A CN201910483928A CN110053789A CN 110053789 A CN110053789 A CN 110053789A CN 201910483928 A CN201910483928 A CN 201910483928A CN 110053789 A CN110053789 A CN 110053789A
- Authority
- CN
- China
- Prior art keywords
- thrust
- voltage regulation
- regulating part
- propulsive medium
- regulation unit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000001141 propulsive effect Effects 0.000 claims abstract description 97
- 238000002309 gasification Methods 0.000 claims abstract description 61
- 230000001105 regulatory effect Effects 0.000 claims abstract description 56
- 239000006200 vaporizer Substances 0.000 claims abstract description 52
- 238000010438 heat treatment Methods 0.000 claims description 35
- 238000001514 detection method Methods 0.000 claims description 24
- 239000007921 spray Substances 0.000 claims description 14
- 230000000087 stabilizing effect Effects 0.000 claims description 10
- 238000007689 inspection Methods 0.000 claims 2
- 239000007788 liquid Substances 0.000 description 7
- 239000007789 gas Substances 0.000 description 5
- 229920006395 saturated elastomer Polymers 0.000 description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010792 warming Methods 0.000 description 2
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 1
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000035807 sensation Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
This application involves spacecraft technical fields, change method more particularly, to a kind of variable thrust propulsion system and thrust, variable thrust propulsion system includes: storage device, gasification unit, voltage regulation unit, regulating part, thrust device；Storage device periodically conveys propulsive medium to gasification unit by the first control valve；Reach the state of being gasified totally at a set temperature into the propulsive medium in gasification unit, adjusts the propulsive medium amount in the open degree adjustment voltage regulation unit of regulating part；Propulsive medium in voltage regulation unit is delivered to thrust device by the second control valve to generate thrust.The regulating part open degree of this variable thrust propulsion system can be continuously adjusted, it can guarantee that the pressure value of the second vaporizer can arbitrarily be set in a certain range, therefore, system can obtain variable thrust, it can be avoided aircraft and run in a manner of pressure by falling, and propulsive medium is made to reach the state of being gasified totally in a manner of preheating, operational reliability is higher, and application range is wider.
Description
Technical field
This application involves spacecraft technical fields, change more particularly, to a kind of variable thrust propulsion system and thrust
Method.
Background technique
Currently, the cold air micromass culture of the arrangements of power system of spacecraft, most of to be subtracted using gaseous medium in outfit
In the case where pressure valve, since pressure reducing valve is locked out pressure ratio, what is obtained is all the gas of steady pressure, is also resulted in below
The thrust that jet pipe obtains is the steady propulsion designed；Minority is using liquefaction gas medium, by directly heating liquefied gas and passing through
Jet pipe sprays, and acquisition is also steady propulsion, and needs to configure extra high heating power, and many microsatellites are not able to satisfy it
Power requirement, and spacecraft is run with a kind of constant thrust, can not be run with the state of variable thrust.
Summary of the invention
The application be designed to provide a kind of variable thrust propulsion system and thrust changes method, with to a certain extent
Solve the technical issues of spacecraft existing in the prior art can not be run with variable thrust.
This application provides a kind of variable thrust propulsion systems, comprising: storage device, gasification unit, voltage regulation unit, adjusting
Part and thrust device；Wherein, the storage device can be pushed away by the first control valve to the gasification unit periodically conveying
Into medium；The gasification unit is used to that the propulsive medium entered in it to be made to reach the state of being gasified totally at a set temperature,
And the open degree that the voltage regulation unit is delivered to by the regulating part, and adjusts the regulating part can be adjusted into it is described steady
Press the propulsive medium amount in unit；The voltage regulation unit passes through second for making the propulsive medium in it reach setting pressure
Control valve is delivered to the thrust device；The thrust device can spray the propulsive medium outward, and generate thrust.
In the above-mentioned technical solutions, further, the gasification unit includes vaporizer and heating device；The heating
Device is for heating the inner space of the vaporizer.
In any of the above-described technical solution, further, the outside of the vaporizer is arranged in the heating device；Or
The inside of the vaporizer is arranged in the heating device.
In any of the above-described technical solution, further, the gasification unit further includes the first detection device；Described first
Detection device is for detecting the indoor pressure of gasification.
In any of the above-described technical solution, further, the voltage regulation unit further includes second detection device；Described second
Detection device is used to detect the pressure in the voltage regulation unit.
In any of the above-described technical solution, further, the regulating part is proportioning valve.
In any of the above-described technical solution, further, first control valve is impulse electromagnetic valve.
In any of the above-described technical solution, further, second control valve is solenoid valve.
Present invention also provides a kind of thrusts to change method, comprising the following steps:
S10, starting heating device, preheat the vaporizer of gasification unit, make the indoor temperature liter of gasification
Up to set temperature；
S20, the first control valve is opened, is passed through propulsive medium in Xiang Suoshu vaporizer, and make the indoor propulsion of gasification
Medium reaches the state of being gasified totally at a set temperature；
S30, regulating part is opened, the indoor gaseous propulsive medium of gasification enters in voltage regulation unit, when the pressure stabilizing
Pressure in unit closes the regulating part when reaching predetermined value；
S40, when needing to obtain thrust, be again turned on the regulating part, and the regulating part is kept to continue opening state
State opens the second control valve, and the propulsive medium in the voltage regulation unit sprays from thrust device and generate thrust, and by described
The propulsive medium of regulating part is identical as by the flow of propulsive medium of second control valve, can get steady propulsion；
S50, when needing to change thrust magnitude, adjust the open degree of the regulating part, adjust and enter in the voltage regulation unit
Propulsive medium amount, and then the amount for changing the propulsive medium that the thrust device sprays can be obtained different size of thrust.
In the above-mentioned technical solutions, between step S10 and S20 further include:
S100, signal is controlled the first control valve input pulse, the propulsive medium in storage device is periodical
It is passed through in the gasification unit.
Compared with prior art, the application has the beneficial effect that
Variable thrust propulsion system provided by the present application, comprising: storage device, gasification unit, voltage regulation unit, regulating part with
And thrust device；Wherein, storage device, gasification unit, regulating part, voltage regulation unit and thrust device, which are sequentially connected, connects, so that
Propulsive medium in storage device can circulate in gasification unit, regulating part and voltage regulation unit, most afterwards through thrust device
Jet pipe sprays, and generates thrust, provides power for spacecraft, and single in storage device and gasification by the setting of the first control valve
The on-off of pipeline between member, and the propulsive medium so that in storage device is periodically opened or closed by controlling the first control valve
It can periodically enter into gasification unit, the propulsion in voltage regulation unit can be adjusted by adjusting the open degree of regulating part
The amount of medium after enabling propulsive medium that can reach scheduled pressure value in voltage regulation unit, sprays generation through thrust device and pushes away
Power.
Specifically, when in use, propulsive medium is stored in storage device this variable thrust propulsion system, most of to promote
Medium exists with liquid, and a small amount of propulsive medium exists through gasifying with gaseous state, opens the first control valve, the part liquid in storage device
State propulsive medium and/or part gaseous state propulsive medium are periodically passed through in gasification unit with certain frequency, and propulsive medium is
It is warming up to set temperature in Unit one and is gasified totally at this temperature, in a small amount of multiple entrance gasification unit of propulsive medium,
Propulsive medium is set to be gasified totally with small-power in a manner of preheating；The thrust according to needed for spacecraft calculates voltage regulation unit
Domestic demand pressure value to be achieved opens regulating part, and the gaseous state propulsive medium in gasification unit enters in voltage regulation unit, when pressure stabilizing list
When pressure in member reaches target value, regulating part is closed, the pressure in voltage regulation unit no longer changes at this time, finally, reopening
Regulating part opens the second control valve, and starts thrust device, and gasification unit continues to convey gaseous state into voltage regulation unit and promote to be situated between
Matter, the propulsive medium in voltage regulation unit is sprayed through thrust device generates thrust, and flows through the propulsive medium of regulating part and through thrust
Flowing to for the propulsive medium that device sprays is identical, therefore the pressure in voltage regulation unit is constant, the thrust that thrust device generates
Be it is constant, when system needs different thrust magnitudes, the pressure in voltage regulation unit is calculated according to new required thrust, adjustment is adjusted
The open degree of part is saved, i.e., the pressure in changeable voltage regulation unit obtains different thrust in turn.
As it can be seen that regulating part open degree can be continuously adjusted, it can guarantee that the pressure value in voltage regulation unit can be in certain model
Interior any setting is enclosed, therefore, system can obtain variable thrust, can be avoided and transport in a manner of pressure in end of lifetime aircraft to fall
Row, can also meet whole star and become the rail time roughly, can also meet and become the needs of rail precision is high, thrust requirements are small, with preheating
Mode to propulsive medium carry out heating reach the state of being gasified totally, system operation reliability is higher, and application range is wider.
Thrust provided by the present application changes method, can control the pressure in voltage regulation unit by adjusting the open degree of regulating part
Power, and then variable thrust can be obtained, aircraft is operated normally in end of lifetime, securely and reliably, is had a wide range of application.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the application specific embodiment or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the application, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram of variable thrust propulsion system provided by the embodiments of the present application；
Fig. 2 is the another structural schematic diagram of variable thrust propulsion system provided by the embodiments of the present application；
Fig. 3 is the flow chart that thrust provided by the embodiments of the present application changes method；
Fig. 4 is the another flow chart that thrust provided by the embodiments of the present application changes method.
Appended drawing reference:
1- storage device, 2- gasification unit, 201- vaporizer, 202- heating device, 3- voltage regulation unit, 4- regulating part, 5-
Thrust device, the first detection device of 6-, 7- second detection device, the first control valve of 8-, the second control valve of 9-.
Specific embodiment
It is clearly and completely described below in conjunction with technical solution of the attached drawing to the application, it is clear that described implementation
Example is some embodiments of the present application, instead of all the embodiments.
The component of the embodiment of the present application for usually describing and showing in attached drawing here can be with a variety of different configurations
To arrange and design.Therefore, the detailed description of the embodiments herein provided in the accompanying drawings is not intended to limit below and is wanted
The scope of the present application of protection is sought, but is merely representative of the selected embodiment of the application.
Based on the embodiment in the application, those of ordinary skill in the art are obtained without making creative work
The every other embodiment obtained, shall fall in the protection scope of this application.
In the description of the present application, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for describe the application and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present application, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in application.
Variable thrust propulsion system and thrust according to the application some embodiments are described referring to Fig. 1 to Fig. 4
Change method.
Referring to figure 1 and figure 2, embodiments herein provides a kind of variable thrust propulsion system, comprising: storage dress
Set 1, gasification unit 2, voltage regulation unit 3, regulating part 4 and thrust device 5；Wherein, storage device 1 can pass through the first control valve
8 periodically convey propulsive medium to gasification unit 2；The propulsive medium that gasification unit 2 is used to make to enter in it is at a set temperature
Reach the state of being gasified totally, and voltage regulation unit 3 be delivered to by regulating part 4, and the open degree for adjusting regulating part 4 can adjust into
Enter the amount of the propulsive medium in voltage regulation unit 3；Voltage regulation unit 3 passes through for making the propulsive medium in it reach setting pressure
Second control valve 9 is delivered to thrust device 5；Thrust device 5 can spray propulsive medium outward, and generate thrust.
Variable thrust propulsion system provided by the present application, comprising: storage device 1, voltage regulation unit 3, is adjusted gasification unit 2
Part 4 and thrust device 4；Wherein, storage device 1, gasification unit 2, regulating part 4, voltage regulation unit 3 and thrust device 4 be sequentially
It is connected, the propulsive medium in storage device 1 is circulated in gasification unit 2, regulating part 4 and voltage regulation unit 3, most
It is sprayed by the jet pipe of thrust device 4, generates thrust, provide power for spacecraft, and exist by the setting of the first control valve 8
The on-off of pipeline between storage device 1 and gasification unit 2, and periodically opened or closed by control the first control valve 8 so that
Propulsive medium in storage device 1 can periodically enter into gasification unit 2, and the open degree by adjusting regulating part 4 can
It is adjusted into the amount of the propulsive medium in voltage regulation unit 3, enables propulsive medium that can reach predetermined pressure in voltage regulation unit 3
After value, is sprayed through thrust device 5 and generate thrust.
Specifically, when in use, propulsive medium is stored in storage device 1 this variable thrust propulsion system, is largely pushed away
Exist into medium with liquid, a small amount of propulsive medium exists through gasifying with gaseous state, opens the first control valve 8, the portion in storage device 1
Liquid separation state propulsive medium and/or part gaseous state propulsive medium are periodically passed through in gasification unit 2 with certain frequency, propulsive medium
It is warming up to set temperature in first unit and is gasified totally at this temperature, a small amount of multiple entrance gasification unit of propulsive medium
In 2, propulsive medium is set to be gasified totally with small-power in a manner of preheating；The thrust according to needed for spacecraft calculates pressure stabilizing
3 domestic demand of unit pressure value to be achieved opens regulating part 4, and the gaseous state propulsive medium in gasification unit 2 enters in voltage regulation unit 3,
When the pressure in voltage regulation unit 3 reaches target value, regulating part 4 is closed, the pressure in voltage regulation unit 3 no longer changes at this time, most
Afterwards, regulating part 4 is reopened, opens the second control valve 9, and start thrust device 4, gasification unit 2 continues into voltage regulation unit 3
Gaseous state propulsive medium is conveyed, the propulsive medium in voltage regulation unit 3 is sprayed through thrust device 4 generates thrust, and flows through regulating part 4
Flowing to for propulsive medium and the propulsive medium sprayed through thrust device 4 is identical, therefore the pressure in voltage regulation unit 3 is constant, thrust
It is the thrust that device 4 generates and constant, when system needs different thrust magnitudes, pressure stabilizing is calculated according to new required thrust
Pressure in unit 3, adjusts the open degree of regulating part 4, i.e., the pressure in changeable voltage regulation unit 3 obtains different push away in turn
Power.
As it can be seen that 4 open degree of regulating part can be continuously adjusted, it can guarantee that the pressure value in voltage regulation unit 3 can be certain
It is arbitrarily set in range, therefore, system can obtain variable thrust, can be avoided and transported in a manner of pressure in end of lifetime aircraft by falling
Row, can also meet whole star and become the rail time roughly, can also meet and become the needs of rail precision is high, thrust requirements are small, with preheating
Mode to propulsive medium carry out heating reach the state of being gasified totally, system operation reliability is higher, and application range is wider.
Wherein, optionally, there is same reason, therefore this variable thrust propulsion system for the gesture stability of aircraft
By change thrust can also change of flight device operation posture.
Wherein, optionally, gasification unit 2 and voltage regulation unit 3 are voltage-stablizer common in the art, certainly, no
It is only limitted to this.
Wherein, optionally, storage device 1 is that tank common in the art is not limited only to this certainly.
Wherein, optionally, propulsive medium is the common liquid medium of the prior art, such as liquid nitrogen, liquid ammonia, certainly, not only
It is limited to this, those skilled in the art are fully able to understand, details are not described herein.
In one embodiment of the application, it is preferable that as shown in Figure 1, gasification unit 2 includes vaporizer 201 and adds
Thermal 202；Heating device 202 is for heating the inner space of vaporizer 201.
In this embodiment, the inner hollow of gasification unit 2 forms vaporizer 201, and heating device 202 is to vaporizer 201
Inner space is preheated, so that temperature is increased to set temperature in vaporizer 201, the propulsive medium in storage device 1 can
The state that can have with liquid or gaseous state or both enters in vaporizer 201, and propulsive medium heats up in vaporizer 201 have been reached
Enter in voltage regulation unit 3 after full gaseous state.
Wherein, optionally, saturated vapour pressure of the propulsive medium under 201 set temperature of vaporizer is calculated, guarantees vaporizer
Pressure in 201, which is less than the saturated vapour pressure of propulsive medium at the set temperature, can guarantee that the propulsion in vaporizer 201 is situated between
Matter is gasified totally.
In one embodiment of the application, it is preferable that as depicted in figs. 1 and 2, heating device 202 is arranged in vaporizer
201 outside；Or the inside of vaporizer 201 is arranged in heating device 202.
In this embodiment, heating device 202 is not limited to that vaporizer 201 is arranged in either internally or externally, when heating fills
Set 202 vaporizer 201 is set inside when can inner space directly to vaporizer 201 and propulsive medium disposed within
It is heated, heating effect is more preferable, and heat source utilization rate is high；When the outside of vaporizer 201 is arranged in heating device 202, can set
It sets between the shell and vaporizer 201 of gasification unit 2, also can be set on the outer surface of 201 shell of vaporizer, make to bring about the desired sensation
The each wall surface for changing room 201 can be heated, so that 201 inner space of vaporizer is heated evenly.
Wherein, optionally, heating device 202 is heater common in the art, and those skilled in the art completely may be used
To understand, details are not described herein.
In one embodiment of the application, it is preferable that as shown in Fig. 2, gasification unit 2 further includes the first detection device 6；
First detection device 6 is used to detect the pressure in vaporizer 201.
In this embodiment, the first detection device 6 is arranged on the pipeline between storage device 1 and gasification unit 2, storage
Device 1 is connected with gasification unit 2, by measuring the pressure value in pipeline between the two, can be obtained in vaporizer 201
Pressure value, by the pressure value of first pressure detection device detection display and propulsive medium under the set temperature in vaporizer 201
Saturated vapour pressure difference, can judge whether the propulsive medium in vaporizer 201 is gasified totally.
Wherein, optionally, the first detection device 6 is gas pressure sensor common in the art, is not only limited certainly
In this.
In one embodiment of the application, it is preferable that as shown in Fig. 2, voltage regulation unit 3 further includes second detection device 7；
Second detection device 7 is used to detect the pressure in voltage regulation unit 3.
In this embodiment, second detection device 7 is arranged on the pipeline between regulating part 4 and voltage regulation unit 3, for surveying
It measures and shows the pressure in voltage regulation unit 3, the scheduled pressure value in voltage regulation unit 3 is calculated according to required thrust, when pressure stabilizing list
The ejection propulsive medium generation thrust of thrust device 4 can be opened by reaching scheduled pressure value inside member 3.
In addition, 3 inner hollow of voltage regulation unit, forms pressure stabilizing chamber, by configuring vaporizer 201 and vaporizer, the two is logical
The connection of part 4 is overregulated, as long as detection vaporizer 201 and the indoor pressure of pressure stabilizing, so that it may adjust working condition, meet system and want
It asks, thus the pressure requirements of vaporizer 201 is reduced, system robustness is more preferable.
Wherein, optionally, second detection device 7 is gas pressure sensor common in the art, is not only limited certainly
In this.
In one embodiment of the application, it is preferable that as depicted in figs. 1 and 2, regulating part 4 is proportioning valve.
In this embodiment, by allocation ratio valve, instead of the common pressure reducing valve of the prior art, the unlatching of Russia day proportioning valve
Degree is continuously adjustable, hereby it is ensured that the pressure value of pressure stabilizing chamber can arbitrarily be set in a certain range, therefore, system can obtain can
Change propulsive, rather than pressure mode simply is fallen, such system thrust is more accurate, more beneficial to whole star.
In one embodiment of the application, it is preferable that as shown in Fig. 2, the first control valve 8 is impulse electromagnetic valve.
In this embodiment, the first control of cyclical intermission control by way of to 8 input pulse signal of the first control valve
The on-off of valve 8 processed, so that the propulsive medium in storage device 1 periodically enters in gasification unit 2, by the gasification unit of preheating
2 pairs of propulsive medium heating, avoid disposably flowing into a large amount of propulsive mediums, need high-power heating and heating time is long.
It wherein, optionally, is 10ms-30ms to the time range of 8 input pulse signal of the first control valve, certainly, not only
Be limited to this, according in vaporizer 201 volume and existing pressure exchange time and the number of whole pulse signal.
In one embodiment of the application, it is preferable that as shown in Fig. 2, the second control valve 9 is solenoid valve.
In this embodiment, the second control valve 9 is opened, thrust medium enters thrust device 4 and from the jet pipe of thrust device 4
It sprays, generates thrust.
Wherein, optionally, thrust device 4 is thruster common in the art, and those skilled in the art completely can be with
Understand, details are not described herein.
As shown in figure 3, embodiments herein also provides a kind of thrust change method, comprising the following steps:
S10, starting heating device 202, preheat the vaporizer 201 of gasification unit 2, make in vaporizer 201
Temperature is increased to set temperature；
S20, the first control valve 8 is opened, propulsive medium is passed through into vaporizer 201, and the propulsion in vaporizer 201 is made to be situated between
Matter reaches the state of being gasified totally at a set temperature；
S30, regulating part 4 is opened, gaseous propulsive medium enters in voltage regulation unit 3 in vaporizer 201, when voltage regulation unit 3
Interior pressure closes regulating part 4 when reaching predetermined value；
S40, when needing to obtain thrust, herein open regulating part 4, and by regulating part 4 keep continue open state, open
Second control valve 9, the propulsive medium in voltage regulation unit 3 spray from thrust device 5 and generate thrust, and pushing away by regulating part 4
It is identical as by the flow of propulsive medium of the second control valve 9 into medium, it can get steady propulsion；
S50, when needing to change thrust magnitude, adjust regulating part 4 open degree, adjust enter voltage regulation unit 3 in propulsion
The amount of medium, and then the amount for changing the propulsive medium that thrust device 5 sprays can be obtained different size of thrust.
In this embodiment, heating device 202 preheats 201 inner space of vaporizer, so that in vaporizer 201
Temperature is increased to set temperature, and the propulsive medium in storage device 1 enters in vaporizer 201, and heating is opened after reaching complete gaseous state
Regulating part 4 is opened, gaseous state propulsive medium can enter in voltage regulation unit 3, calculate the pressure in voltage regulation unit 3 according to the thrust magnitude
Value opens the second control valve 9 when the pressure in voltage regulation unit 3 reaches calculated target value, and propulsive medium enters thrust dress
It sets in 4 and is sprayed from its jet pipe and generate thrust, when the pressure offset target value in voltage regulation unit 3, adjust the unlatching of regulating part 4
Degree is passed through the pressure in appropriate propulsive medium increase voltage regulation unit 3 to target value, i.e., according in voltage regulation unit 3 to voltage regulation unit 3
The open degree of pressure change humidity adjustment regulating part 4 be pressure in adjustable voltage regulation unit 3, and then adjust thrust device 4
The thrust of generation enables thrust device 4 to generate variable thrust.
As shown in figure 4, the thrust that embodiments herein provides changes method, between step S10 and S20 further include:
S100, signal is controlled 8 input pulse of the first control valve, the propulsive medium in storage device 1 is periodically passed through gasification unit 2
It is interior.
In this embodiment, the first control of cyclical intermission control by way of to 8 input pulse signal of the first control valve
The on-off of valve 8 processed, so that the propulsive medium in storage device 1 periodically enters in gasification unit 2, by the gasification unit of preheating
But 2 pairs of propulsive medium heating, reach the shape that is gasified totally with the propulsive medium that lesser power is heated i.e. in gasification unit 2
State, safety are higher, additionally it is possible to shorten heating time.
The thrust that embodiments herein provides changes method, between step S20 and S30 further include:
S200, the pressure in the first detection device 6 detection vaporizer 201 is used；
Between step S30 and S40 further include:
S300, the pressure in voltage regulation unit 3 is detected using second detection device 7.
Saturation of the pressure and propulsive medium detected by the first detection device 6 in vaporizer 201 under set temperature
Vapour pressure comparison, it is desirable that the pressure in vaporizer 201 is less than the saturated vapour pressure of propulsive medium at the set temperature, it is ensured that
Propulsive medium is in the state of being gasified totally at the set temperature；
The pressure that should reach in voltage regulation unit 3 is calculated according to required thrust, is detected and be can be read by second detection device 7
Pressure in voltage regulation unit 3 adjusts the open degree of regulating part 4 according to pressure change, may make the pressure stabilizing when needing steady propulsion
Pressure is stablized in unit 3, and then obtains steady propulsion.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the application, rather than its limitations；To the greatest extent
Pipe is described in detail the application referring to foregoing embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, each embodiment technology of the application that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (10)
1. a kind of variable thrust propulsion system characterized by comprising storage device, gasification unit, voltage regulation unit, regulating part
And thrust device；
Wherein, the storage device can periodically convey propulsive medium to the gasification unit by the first control valve；
The gasification unit is used to that the propulsive medium entered in it to be made to reach the state of being gasified totally at a set temperature, and leads to
It crosses the regulating part and is delivered to the voltage regulation unit, and the open degree for adjusting the regulating part can be adjusted into the pressure stabilizing list
Propulsive medium amount in member；
The voltage regulation unit is delivered to described push away for making the propulsive medium in it reach setting pressure, and by the second control valve
Power device；
The thrust device can spray the propulsive medium outward, and generate thrust.
2. variable thrust propulsion system according to claim 1, which is characterized in that the gasification unit include vaporizer with
And heating device；The heating device is for heating the inner space of the vaporizer.
3. variable thrust propulsion system according to claim 2, which is characterized in that the heating device is arranged in the gas
Change the outside of room；
Or the inside of the vaporizer is arranged in the heating device.
4. variable thrust propulsion system according to claim 2, which is characterized in that the gasification unit further includes the first inspection
Survey device；First detection device is for detecting the indoor pressure of gasification.
5. variable thrust propulsion system according to claim 3, which is characterized in that the voltage regulation unit further includes the second inspection
Survey device；The second detection device is used to detect the pressure in the voltage regulation unit.
6. variable thrust propulsion system according to claim 1, which is characterized in that the regulating part is proportioning valve.
7. variable thrust propulsion system according to claim 1, which is characterized in that first control valve is pulse electromagnetic
Valve.
8. variable thrust propulsion system according to claim 1, which is characterized in that second control valve is solenoid valve.
9. a kind of thrust changes method, which comprises the following steps:
S10, starting heating device, preheat the vaporizer of gasification unit, are increased to the indoor temperature of gasification
Set temperature；
S20, the first control valve is opened, is passed through propulsive medium in Xiang Suoshu vaporizer, and make the indoor propulsive medium of gasification
Reach the state of being gasified totally at a set temperature；
S30, regulating part is opened, the indoor gaseous propulsive medium of gasification enters in voltage regulation unit, when the voltage regulation unit
Interior pressure closes the regulating part when reaching predetermined value；
S40, when needing to obtain thrust, be again turned on the regulating part, and the regulating part is kept to continue open state, beat
The second control valve is opened, the propulsive medium in the voltage regulation unit sprays from propulsive force device and generate thrust, and passes through the tune
The propulsive medium for saving part is identical as by the flow of propulsive medium of second control valve, can get steady propulsion；
S50, when needing to change thrust magnitude, adjust the open degree of the regulating part, adjust and enter pushing away in the voltage regulation unit
Into the amount of medium, and then the amount for changing the propulsive medium that the thrust device sprays can be obtained different size of thrust.
10. thrust according to claim 9 changes method, which is characterized in that between step S10 and S20 further include:
S100, signal is controlled the first control valve input pulse, the propulsive medium in storage device is periodically passed through
In the gasification unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910483928.2A CN110053789A (en) | 2019-06-05 | 2019-06-05 | Variable thrust propulsion system and thrust change method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910483928.2A CN110053789A (en) | 2019-06-05 | 2019-06-05 | Variable thrust propulsion system and thrust change method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110053789A true CN110053789A (en) | 2019-07-26 |
Family
ID=67325573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910483928.2A Pending CN110053789A (en) | 2019-06-05 | 2019-06-05 | Variable thrust propulsion system and thrust change method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110053789A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110963086A (en) * | 2019-12-10 | 2020-04-07 | 上海空间推进研究所 | Variable thrust chilled air propulsion system and method for drag-free satellites |
| CN110979748A (en) * | 2019-12-25 | 2020-04-10 | 西安交通大学 | Buffering method and device based on liquid-phase carbon dioxide phase change and aircraft |
| CN111003218A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | Propelling method and propelling device based on liquid carbon dioxide phase change |
| CN111003217A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | Sustainable propulsion method and device based on liquid-phase carbon dioxide phase change and aircraft |
| CN111003219A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | High-voltage discharge-based propulsion method and propulsion device for liquid-phase carbon dioxide phase change |
| CN111003216A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | Electric heating-based propulsion method and propulsion device for liquid-phase carbon dioxide phase change |
| CN110979748B (en) * | 2019-12-25 | 2024-07-09 | 西安交通大学 | Buffering method and device based on liquid-phase carbon dioxide phase change and aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101943082A (en) * | 2010-07-23 | 2011-01-12 | 北京航空航天大学 | Heating gasification device for liquefied gas micro-propulsion system |
| KR20120062288A (en) * | 2010-12-06 | 2012-06-14 | (주)쎄트렉아이 | Fuel supplying system of space vehicles and method of using the same |
| CN106134395B (en) * | 2012-02-07 | 2014-09-03 | 西安航天动力研究所 | Cold air micro thrust precise control device and method |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
| CN210027983U (en) * | 2019-06-05 | 2020-02-07 | 北京宇航天驰空间科技有限公司 | Variable thrust propulsion system and aircraft |
-
2019
- 2019-06-05 CN CN201910483928.2A patent/CN110053789A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101943082A (en) * | 2010-07-23 | 2011-01-12 | 北京航空航天大学 | Heating gasification device for liquefied gas micro-propulsion system |
| KR20120062288A (en) * | 2010-12-06 | 2012-06-14 | (주)쎄트렉아이 | Fuel supplying system of space vehicles and method of using the same |
| CN106134395B (en) * | 2012-02-07 | 2014-09-03 | 西安航天动力研究所 | Cold air micro thrust precise control device and method |
| CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
| CN210027983U (en) * | 2019-06-05 | 2020-02-07 | 北京宇航天驰空间科技有限公司 | Variable thrust propulsion system and aircraft |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110963086A (en) * | 2019-12-10 | 2020-04-07 | 上海空间推进研究所 | Variable thrust chilled air propulsion system and method for drag-free satellites |
| CN110963086B (en) * | 2019-12-10 | 2024-04-26 | 上海空间推进研究所 | Variable thrust cold air propulsion system and method for a drag-free satellite |
| CN110979748A (en) * | 2019-12-25 | 2020-04-10 | 西安交通大学 | Buffering method and device based on liquid-phase carbon dioxide phase change and aircraft |
| CN111003218A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | Propelling method and propelling device based on liquid carbon dioxide phase change |
| CN111003217A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | Sustainable propulsion method and device based on liquid-phase carbon dioxide phase change and aircraft |
| CN111003219A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | High-voltage discharge-based propulsion method and propulsion device for liquid-phase carbon dioxide phase change |
| CN111003216A (en) * | 2019-12-25 | 2020-04-14 | 西安交通大学 | Electric heating-based propulsion method and propulsion device for liquid-phase carbon dioxide phase change |
| WO2021128448A1 (en) * | 2019-12-25 | 2021-07-01 | 西安交通大学 | Propulsion method based on liquid carbon dioxide phase transition and propulsion apparatus thereof |
| US11858666B2 (en) | 2019-12-25 | 2024-01-02 | Xi'an Jiaotong University | Propulsion method based on liquid carbon dioxide phase change and propulsion device thereof |
| CN111003218B (en) * | 2019-12-25 | 2024-04-05 | 西安交通大学 | Propelling method and propelling device based on liquid carbon dioxide phase change |
| CN110979748B (en) * | 2019-12-25 | 2024-07-09 | 西安交通大学 | Buffering method and device based on liquid-phase carbon dioxide phase change and aircraft |
| CN111003216B (en) * | 2019-12-25 | 2024-07-09 | 西安交通大学 | Electric heating-based liquid-phase carbon dioxide phase change propulsion method and propulsion device thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110053789A (en) | Variable thrust propulsion system and thrust change method | |
| EP1703102B1 (en) | Liquefied natural gas power plant and operation method thereof | |
| CN104828262B (en) | Low-pressure liquefied gas thrust generating method for spacecraft | |
| US20130014514A1 (en) | Systems and methods for bulk temperature variation reduction of a gas turbine through can-to-can fuel temperature modulation | |
| CN111197695B (en) | Fluid bypass method and system for controlling temperature of non-petroleum fuels | |
| CN108490775A (en) | Spacecraft temperature stability control device and control method | |
| US9158312B2 (en) | Method and device for controlling outlet water temperature of water heater | |
| US11746711B2 (en) | Pulse width modulation drive for staged fuel manifolds | |
| CN111570124A (en) | Icing wind tunnel spraying equipment and water supply pressure quick response device and method thereof | |
| US6986245B2 (en) | Fuel supply system and an associated operating method | |
| CN107132037B (en) | Test device for testing flow of low-temperature nozzle | |
| CN109004250A (en) | A kind of device and method of quick adjusting pipeline gas temperature humidity | |
| EP2645020B1 (en) | Heat Pump System | |
| CN205827259U (en) | Gas temperature adjusting means | |
| CN212493555U (en) | Icing wind tunnel spraying equipment and water supply pressure quick response device thereof | |
| CN210027983U (en) | Variable thrust propulsion system and aircraft | |
| CN106091376A (en) | The broken empty heat blower of vacuum glass equipment | |
| US10854895B2 (en) | Thermal regulation system for a fuel cell | |
| Martinez et al. | Fermilab SRF cryomodule operational experience | |
| JP4957273B2 (en) | Steam supply device | |
| Dankanich et al. | Advanced Xenon Feed System (AXFS) Development and Hot-fire Texting | |
| JPS6138300A (en) | Liquefied gas vaporizer | |
| RU2651703C1 (en) | Supply block of a working fluid to a jet engine of a spacecraft | |
| JP2002081598A (en) | Method and device for manufacturing city gas | |
| Wang et al. | Operational experience from LCLS-II cryomodule testing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230920 Address after: Room 139, 1st Floor, Building 23, Wenzhou National University Science and Technology Park, No. 89 Fengfang Road, Ouhai Economic Development Zone, Wenzhou City, Zhejiang Province, 325036 Applicant after: Aerospace Science and Technology Co.,Ltd. (Wenzhou) Address before: 100094 0075, 4 / F, block a, building 24, yard 68, Beiqing Road, Haidian District, Beijing Applicant before: Beijing Yuhang Tianchi Power Technology Co.,Ltd. |