CN114414425B - Propellant use efficiency measuring device and method for simulating capillary transport - Google Patents
Propellant use efficiency measuring device and method for simulating capillary transport Download PDFInfo
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- CN114414425B CN114414425B CN202111565730.2A CN202111565730A CN114414425B CN 114414425 B CN114414425 B CN 114414425B CN 202111565730 A CN202111565730 A CN 202111565730A CN 114414425 B CN114414425 B CN 114414425B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N5/00—Analysing materials by weighing, e.g. weighing small particles separated from a gas or liquid
- G01N5/04—Analysing materials by weighing, e.g. weighing small particles separated from a gas or liquid by removing a component, e.g. by evaporation, and weighing the remainder
Abstract
The invention provides a propellant use efficiency measuring device and method for simulating capillary transport, comprising the following steps: a weighing balance (207), an electrospray thruster propellant storage tank (206), a propellant absorber (204), a propellant collection plate (203) and a bracket (205); one end of the propellant absorber (204) extends into the electrospray thruster propellant reservoir (206), and the other end of the propellant absorber (204) is connected to the propellant collection plate (203). The invention calculates the use efficiency of the propellant by utilizing the mass difference measured before and after the propellant transportation, provides a clear scheme for measuring the use efficiency of the passive liquid supply propellant of the electric spraying thruster, can accelerate the supply rate of the propellant, then measures the utilization rate of the propellant, and greatly shortens the measurement time.
Description
Technical Field
The invention relates to the field of electric propulsion, in particular to a device and a method for measuring the use efficiency of a propellant for simulating capillary transport.
Background
The electric spraying thruster is a novel electric thruster adopting ionic liquid as propellant, and generally adopts a passive liquid supply type propellant supply mode, wherein a spongy absorber with certain porosity is generally used as a transport medium, and the transport medium is connected with a storage tank and an emitter for propellant transport, and the propellant supply mode is shown in figure 1. The propellant is transported into the projectile under the effect of the laplace pressure against the resistance of the absorber to its flow. In practical operation, because capillary transport is limited, the propellant in the storage tank cannot be transported to the emitter in hundred percent in the transport process, the propellant injected into the storage tank cannot be completely used for the ignition task of the thruster, and therefore the use efficiency of the propellant in the storage tank needs to be measured to estimate the actual propellant quantity required to meet certain task requirements.
Patent document CN103017852B provides a tank liquid propellant quantity measuring method comprising the steps of: step S1: measuring initial pressure and temperature of the storage tank and the gas cylinder, and predicting initial gas volume V0 and residual liquid propellant quantity ml0 in the storage tank by utilizing a propellant quantity static measurement method; step S2: establishing a heat and mass transfer mathematical model of a storage tank open system pressurizing process, and performing simulation calculation by using measured initial conditions to obtain the change relation of gas phase temperature, gas phase pressure along with time and the propellant quantity in the storage tank; step S3: the pressurized gas is injected into the storage tank through the gas cylinder, the maintenance time is consistent with the simulation time, and the pipeline is kept to have good tightness; step S4: measuring the gas pressure and the gas temperature of a gas part in the storage tank at a preset moment, and comparing the gas pressure and the gas temperature with a simulation result; step S5: and fitting out the actual propellant flow according to the simulation result and the experimental result, and calculating the residual propellant quantity in the storage tank at any moment through a formula under the condition of knowing the initial propellant quantity. However, this patent document does not address how to measure the efficiency of propellant use.
The time required for measuring the propellant using efficiency by the operation of the thruster to the limit state is longer, generally hundreds of hours, because the flow rate of the thruster is very small, the volume of the projectile is small and the quantity of the propellant which can be maintained is very limited on the order of 10-13kg/s, so that the propellant transporting process needs to be simulated firstly when the propellant using efficiency is measured, the propellant supply rate is accelerated, and then the propellant using efficiency is measured.
At present, no clear method exists for measuring the use efficiency of the passive liquid supply propellant of the electric spraying thruster, and the invention provides a propellant use efficiency test method for simulating the propellant transportation process of the electric spraying thruster.
Disclosure of Invention
In view of the shortcomings in the prior art, it is an object of the present invention to provide a device and method for measuring the efficiency of propellant use simulating capillary transport.
According to the invention, a propellant use efficiency measuring device for simulating capillary transport comprises: a weighing balance 207, an electrospray thruster propellant tank 206, a propellant absorber 204, a propellant collection plate 203, a bracket 205;
the electrospray thruster propellant reservoir 206 is placed on a weighing balance 207;
the propellant collection plate 203 is placed on a carrier 205;
one end of the propellant absorber 204 extends into an electrospray thruster propellant reservoir 206, and the other end of the propellant absorber 204 is connected to a propellant collection plate 203.
Preferably, the propellant is effective when the capillary transport is simulatedThe rate measuring device is arranged in a vacuum chamber, and the vacuum chamber is opened to draw the vacuum degree to 10 -2 After Pa-magnitude, capillary action of the propellant absorber 204 transports the propellant from the electrospray thruster propellant reservoir 206 to the propellant collection plate 203.
Preferably, the propellant collection plate 203 is used with a pore size of 1-10 um as the emitter pore size, the propellant collection plate 203 having an area of 50 times the emitter area.
Preferably, the propellant absorber 204 is spongy, the propellant absorber 204 having pores larger than the pores of the propellant collection plate 203.
According to the propellant use efficiency measuring method for simulating capillary transport, which is provided by the invention, a measuring device is built for simulating capillary transport, and the propellant use efficiency is calculated by utilizing the quality difference measured before and after propellant transport.
Preferably, the propellant using efficiency measuring device simulating capillary transport is adopted.
Preferably, the propellant using efficiency measuring device simulating capillary transport is placed in a vacuum cabin;
first, the mass m of the empty electrospray thruster propellant reservoir 206 is measured 1 The mass m of the propellant reservoir 206 of the electrospray thruster with propellant is then measured 2 Obtaining mass m of the injected propellant 2 -m 1 ；
The propellant absorber 204 is then placed on a weighing scale 207, the mass of the propellant absorber 204 being measured as m 3 One end of a propellant absorber 204 is placed into a propellant storage tank 206 of an electrospray thruster provided with propellant, the other end is connected to a propellant collection plate 203, a vacuum chamber is opened, and the propellant is transported to the propellant collection plate 203 by capillary action of the propellant absorber 204;
measuring the mass m of the electrospray thruster propellant reservoir 206 and the propellant absorber 204 after transport is completed at this time 4 The mass m of the residual propellant can be obtained 4 -m 3 -m 1 ；
The mass utilization efficiency of the propellant can be obtained according to the mass of the propellant measured in the front and back.
Preferably the vacuum is drawn to 10 -2 Of the order of Pa.
Preferably, after the propellant collection plate 203 is saturated, the propellant collection plate 203 is replaced until no propellant is collected on the propellant collection plate 203.
Preferably, the efficiency of use of the propellant is calculated according to the formula:
wherein: m is m 4 -total mass of electrospray thruster propellant reservoir 206 and propellant absorber 204 after propellant transport is completed;
m 3 -the mass of the propellant absorber 204 prior to propellant transport;
m 2 -total mass of propellant and electrospray thruster propellant reservoir 206 prior to propellant transport;
m 1 -mass of electrospray thruster propellant reservoir 206 prior to propellant transport;
η—efficiency of use of the propellant.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention calculates the use efficiency of the propellant by utilizing the mass difference measured before and after the propellant is transported, and provides a clear scheme for measuring the use efficiency of the passive liquid supply propellant of the electric spraying thruster.
2. The invention can accelerate the propellant supply rate and then measure the propellant use efficiency, thereby greatly shortening the measurement time.
3. The measuring device provided by the invention has a simple structure and is easy to build and maintain.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of a passive supply of electrospray thruster propellant.
Fig. 2 is a schematic diagram of a propellant utilization efficiency measuring apparatus.
The figure shows:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
The invention provides a propellant use efficiency measuring device for simulating capillary transport, which comprises: a weigh scale 207, an electrospray thruster propellant reservoir 206, a propellant absorber 204, a propellant collection plate 203, a bracket 205, as shown in fig. 2. The propellant absorber 204 is spongy. The weighing balance 207 is a high-precision balance with a precision better than 0.1mg. A porous plate having the same porosity as the emitter is selected as the propellant collection plate 203. An electrospray thruster propellant reservoir 206 is placed on a weighing scale 207 and a propellant absorber 204 is placed into the electrospray thruster propellant reservoir 206 and connected to a propellant collection plate 203 on a bracket 205. The propellant collection plate 203 used has the same aperture as the emitter aperture, the aperture being 1-10 um, the propellant collection plate 203 being 50 times the emitter area. The sponge absorber is used for transporting the propellant, and the pore size of the sponge absorber is larger than that of the collecting plate and is 50 times of that of the collecting plate. According to the measuring device provided by the invention, the use efficiency of the propellant is measured by simulating the transportation mode of the propellant of the electrospray thruster and measuring the mass of the storage tanks before and after the propellant is supplied.
The invention provides a method for measuring the use efficiency of a propellant in a simulated capillary transport, which can be used for measuring the use efficiency of the propellant in a storage tank of an electrospray thruster.
During testing, the propellant using efficiency measuring device simulating capillary transport is placed in the vacuum cabin. First, the mass m of the empty electrospray thruster propellant reservoir 206 is measured 1 The mass m of the propellant reservoir 206 of the electrospray thruster with propellant is then measured 2 Obtaining mass m of the injected propellant 2 -m 1 。
The propellant absorber 204 is then placed on a weighing scale 207, the mass of the propellant absorber 204 being measured as m 3 One end of the propellant absorber 204 is placed in the propellant tank 206 of the electric injection thruster provided with propellant, the other end is connected to the propellant collection plate 203, the vacuum chamber is opened, and the vacuum degree is pumped to 10 -2 Of the order of Pa. The propellant is transported to the propellant collection plate 203 by capillary action of the propellant absorber 204, and after the propellant collection plate 203 is saturated, the propellant collection plate 203 is replaced until no propellant is collected on the propellant collection plate 203.
Measuring the mass m of the electrospray thruster propellant reservoir 206 and the propellant absorber 204 after transport is completed at this time 4 The mass m of the residual propellant can be obtained 4 -m 3 -m 1 . The mass utilization efficiency of the propellant can be obtained according to the mass of the propellant measured in the front and back. The whole test process is completed in a vacuum environment.
Wherein the efficiency of use of the propellant is calculated according to the formula:
wherein: m is m 4 -total mass of electrospray thruster propellant reservoir 206 and propellant absorber 204 after propellant transport is completed;
m 3 -the mass of the propellant absorber 204 prior to propellant transportAn amount of;
m 2 -total mass of propellant and electrospray thruster propellant reservoir 206 prior to propellant transport;
m 1 -mass of electrospray thruster propellant reservoir 206 prior to propellant transport;
η—efficiency of use of the propellant.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (6)
1. A propellant use efficiency measuring device simulating capillary transport, comprising: a weighing balance (207), an electrospray thruster propellant storage tank (206), a propellant absorber (204), a propellant collection plate (203) and a bracket (205);
the electric spraying thruster propellant storage box (206) is arranged on a weighing balance (207);
a propellant collection plate (203) is placed on the carrier (205);
one end of the propellant absorber (204) extends into the propellant reservoir (206) of the electrospray thruster, and the other end of the propellant absorber (204) is connected to the propellant collection plate (203);
when the simulated capillary transport propellant usage efficiency measuring device is disposed in the vacuum chamber,opening the vacuum chamber to draw vacuum degree to 10 -2 After Pa-magnitude, capillary action of the propellant absorber (204) transports the propellant from the electrospray thruster propellant reservoir (206) to the propellant collection plate (203).
2. A device for measuring the efficiency of use of a propellant in simulated capillary transport as claimed in claim 1, wherein the aperture of the propellant collection plate (203) used is the same as the aperture of the emitter, the aperture being 1-10 um, the area of the propellant collection plate (203) being 50 times the area of the emitter.
3. A device for measuring the efficiency of use of a propellant in simulated capillary transport as claimed in claim 1, wherein the propellant absorber (204) is spongy, the propellant absorber (204) having pores larger than the pores of the propellant collection plate (203).
4. A propellant use efficiency measuring method for simulating capillary transport is characterized in that a measuring device is built to simulate capillary transport, and the propellant use efficiency is calculated by using the quality difference measured before and after propellant transport;
a propellant use efficiency measuring device employing simulated capillary transport as claimed in claim 1;
placing the propellant using efficiency measuring device simulating capillary transport in a vacuum cabin;
firstly, measuring the mass m of an empty propellant tank (206) of an electrospray thruster 1 The mass m of the propellant reservoir (206) of the electrospray thruster with propellant is then measured 2 Obtaining mass m of the injected propellant 2 -m 1 ；
The propellant absorber (204) is then placed on a weighing balance (207), the mass of the propellant absorber (204) being measured as m 3 One end of a propellant absorber (204) is placed in a propellant storage tank (206) of an electric spraying thruster filled with propellant, the other end is connected to a propellant collecting plate (203), a vacuum chamber is opened, and the vacuum degree is pumped to 10 -2 Of the Pa magnitude, transporting the propellant to the propellant by capillary action of the propellant absorber (204)A collection plate (203);
measuring the mass m of the propellant tank (206) and the propellant absorber (204) of the electrospray thruster after transport is completed 4 The mass m of the residual propellant can be obtained 4 -m 3 -m 1 ；
The mass utilization efficiency of the propellant can be obtained according to the mass of the propellant measured in the front and back.
5. The method for measuring the efficiency of using a propellant in simulated capillary transport according to claim 4, wherein the propellant collection plate (203) is replaced after the propellant collection plate (203) is saturated until no propellant is collected on the propellant collection plate (203).
6. A method for measuring the efficiency of use of a propellant in simulating capillary transport according to claim 4,
the efficiency of propellant use is calculated according to the formula:
wherein: m is m 4 -total mass of the electrospray thruster propellant reservoir (206) and the propellant absorber (204) after the propellant transport is completed;
m 3 -the mass of the propellant absorber (204) before the transport of the propellant;
m 2 -the total mass of propellant and electrospray thruster propellant reservoir (206) before propellant transport;
m 1 -the mass of the electrospray thruster propellant reservoir (206) prior to the transport of the propellant;
η—efficiency of use of the propellant.
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| CN116754211B (en) * | 2023-08-22 | 2023-12-19 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110082258A (en) * | 2019-05-10 | 2019-08-02 | 西安航天化学动力有限公司 | Composite solidpropellant medicine slurry flow velocity test device and test method |
| CN110884693A (en) * | 2019-12-06 | 2020-03-17 | 中国人民解放军国防科技大学 | Passive feed type electrospray thruster system |
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| JPS61122524A (en) * | 1984-11-20 | 1986-06-10 | Ishikawajima Harima Heavy Ind Co Ltd | Measuring method of remaining amount of propellant of astrogation body |
| US20040226279A1 (en) * | 2003-05-13 | 2004-11-18 | Fenn John B. | Wick injection of colloidal fluids for satellite propulsion |
| CN103017852B (en) * | 2012-12-28 | 2015-01-21 | 中国人民解放军国防科学技术大学 | Method for measuring quantity of liquid propellant in storage tank |
| CN108684127A (en) * | 2018-04-11 | 2018-10-19 | 上海空间推进研究所 | Emitter wetting method and its dedicated unit |
| CN109405918A (en) * | 2018-12-06 | 2019-03-01 | 上海空间推进研究所 | A kind of spacecraft propulsion agent residue measuring method based on propellant physical property |
| CN110779591B (en) * | 2019-10-30 | 2020-10-27 | 中国人民解放军国防科技大学 | Method and device for measuring residual quantity of propellant in complex storage tank |
| CN112729498B (en) * | 2020-12-24 | 2021-10-29 | 上海空间推进研究所 | Method, system and medium for measuring residual propellant mass of propulsion system |
| CN112780514B (en) * | 2021-02-22 | 2022-03-18 | 北京理工大学 | Ionic liquid electric spraying thruster for electric field control liquid supply |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110082258A (en) * | 2019-05-10 | 2019-08-02 | 西安航天化学动力有限公司 | Composite solidpropellant medicine slurry flow velocity test device and test method |
| CN110884693A (en) * | 2019-12-06 | 2020-03-17 | 中国人民解放军国防科技大学 | Passive feed type electrospray thruster system |
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