CN106134479B - The method of a kind of Accurate Assessment space rail control engine vacuum specific impulse performance - Google Patents
The method of a kind of Accurate Assessment space rail control engine vacuum specific impulse performanceInfo
- Publication number
- CN106134479B CN106134479B CN201110011733.1A CN201110011733A CN106134479B CN 106134479 B CN106134479 B CN 106134479B CN 201110011733 A CN201110011733 A CN 201110011733A CN 106134479 B CN106134479 B CN 106134479B
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- propellant
- specific impulse
- vacuum
- thrust
- engine
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Abstract
The present invention proposes the method for a kind of Accurate Assessment space rail control engine vacuum specific impulse performance, the method is by actual measurement engine vacuum thrust and propellant flow rate, propellant temperature, relation between matching vacuum specific impulse and propellant temperature obtains relation curve and relation formula: I simultaneouslysv＝aT2+ bT+c. Realize accurate control and the evaluation of engine vacuum specific impulse by the application of relation formula. Adopt the present invention, effectively, determine accurately the performance state of space rail control engine, and then the consumption of propellant when accurately calculating spacecraft and becoming rail, for accurate evaluation, the estimating of spacecraft life-span of spacecraft propulsion agent surplus provide reliable basis.
Description
Technical field
The present invention relates to low thrust double elements rail control engine in spacecraft propulsion system use, be specifically related toVacuum specific impulse Reliable Evaluating Methods of Their Performance.
Background technology
Space rail control engine vacuum specific impulse is the thrust that specific discharge propellant produces, as spacecraftThe liquid rail control rocket engine of entering the orbit used, vacuum specific impulse is very important performance parameter, conventionallyThe propellant quantity that in situation, spacecraft carries is certain, and wherein major part is disappeared by rail control engine change railConsumption, remainder is by attitude control engine consumption in operation. Rail control engine vacuum specific impulse performance mainly contains followingThe impact of several aspects: the first, the vacuum specific impulse performance of raising rail control engine, can reduce effectivelyThe consumption of propellant while becoming rail, thus extend the service life of spacecraft or increase effective that spacecraft carriesLoad quantity; In general, within the specific limits along with propellant temperature raises, propellant viscosity and tableSurface tension reduces, and can promote to a certain extent the shock atomization of propellant, but is advancing temperature rising sameTime, combustion reaction aggravation, two kinds of propellant atomization regions will produce a large amount of high-temperature products and NTOThermal decomposition product, these products, by hindering the further shock blending of fuel and oxidant, even can occurThe effect of blowing off of propellant, seriously hinders the atomization of propellant, reduces efficiency of combustion, and then makes engineVacuum specific impulse reduce.
The second, in spacecraft operation on orbit process, engine is mainly as the change in current propulsion subsystemRail engine, its vacuum performance is one of very important performance parameter, every engine is being paid flightBefore using, all need to carry out the examination of altitude simulation heat run heat mark to obtain the practical vacuum specific impulse of enginePerformance. But due to the restriction of experimental condition, the test period of engine is conventionally within the different time periodsCarry out, this has just caused under the condition of different time, different temperatures, and engine vacuum specific impulse performance is depositedIn very large difference, if provide satellite control using above-mentioned data as the final result of engine vacuum specific impulseSystem processed, will cause and advance the deviation of controlling.
Centering low thrust space rail control engine is accurately determined vacuum specific impulse performance in application process at present,Can calculate the propellant consumption of rail control engine while becoming rail, thereby carry out estimating of Residual PropellantWith estimating of spacecraft operation on orbit life-span.
Summary of the invention:
Technical problem to be solved by this invention is to apply for middle low thrust space rail control engineThe problem of vacuum specific impulse performance Accurate Assessment in journey, the invention provides a kind of space rail control engine vacuum ratioRush the method for Accurate Assessment.
The technical scheme that the present invention takes for its technical problem of solution is by determining vacuum specific impulse and pushing awayEnter the relation between agent temperature, formulate propellant temperature and vacuum specific impulse relation curve, utilize propulsion systemThe temperature sensor monitors propellant temperature of arranging on propellant tank and pipeline, changes with propellant temperatureData are revised the vacuum specific impulse of engine, realize the vacuum of engine under different propellant temperature conditionsThan the Accurate Assessment of punching performance.
The present invention brings following beneficial effect:
Utilize the present invention can realize accurately determining of vacuum specific impulse, rail can calculate spacecraft change rail timeThe propellant consumption of control engine, thus carry out estimating and the spacecraft operation on orbit longevity of Residual PropellantEstimating of life.
Brief description of the drawings
Accompanying drawing 1 is the vacuum specific impulse of one embodiment of the present of invention and the curve of propellant relation;
Detailed description of the invention:
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Fig. 1 has provided the relation curve of certain engine oxidant temperature to vacuum specific impulse performance impact, from figureIn can find out that engine vacuum specific impulse performance and propellant temperature are parabolical relation, therefore can rootDetermine the vacuum specific impulse of engine according to the propellant temperature under different condition.
Its implementation procedure is as follows:
1) vacuum specific impulse of engine is mainly by actual measurement engine vacuum thrust and propellant flow rate,Calculate according to the relation of vacuum specific impulse and vacuum thrust, propellant flow rate. Engine vacuum thrust andPropellant flow rate is mainly measured on altitude simulation heat run testing stand, and wherein vacuum thrust is by comprisingThe device such as thrust pickup, thrust frame, thrust calibration is measured at interior Thrust Measuring System, propellant flowAmount is measured by the Flow Measuring System including the device such as mass flowmenter, turbine flowmeter. Vacuum pushes awayThe measurement data of power and propellant flow rate is by data collecting system collection, processing. Finally according to engineThe relation formula of vacuum specific impulse and vacuum thrust, propellant flow rateCalculate and obtain, wherein IsvBe trueEmpty specific impulse, FvFor vacuum thrust, q are total propellant flow rate.
2), in the time that engine carries out heat run examination work, the temperature of propellant used is mainly by pushing awayEnter the temperature sensor of arranging on agent tank and propellant transfer pipeline measure, by data collecting systemGather, process.
3), by carrying out above-mentioned experimental test, data acquisition, can obtain one group of different propellant temperatureUnder engine vacuum specific impulse and propellant temperature between the data that are mutually related. On this basis, pass throughData fitting method can obtain the matched curve that is related between engine vacuum specific impulse and propellant temperature,Under normal circumstances, the pass between engine vacuum specific impulse and propellant temperature is that quadratic equation with one unknown closesSystem, the general type of relation equation is: Isv＝aT2+ bT+c, wherein IsvFor vacuum specific impulse, T is for advancingAgent temperature, a, b, c are relation equation coefficient. Starting of different thrust magnitudes, different propellant constituent elementsMachine above-mentioned relation equation coefficient a, b, c may be different.
4) when engine application is during in spacecraft operation on orbit, utilize definite engine vacuum ratioRelation formula between punching and propellant temperature, by the monitoring to propulsion system propellant temperature, canVacuum specific impulse performance when real-time acquisition engine real work, thus can calculate accurately enginePropellant waste when work, and then can calculate the surplus of propulsion system propellant, reach essenceReally estimate propulsion system Residual Propellant and the object of estimating the spacecraft operation on orbit life-span. In addition, boatWhen it device operation on orbit, as revised the vacuum specific impulse of engine, can advance by adjustingThe method of agent temperature realizes the variation of engine vacuum specific impulse, realizes engine vacuum specific impulse and accurately controls.
Give an example 1:
Corresponding pass between a kind of double elements 490N liquid-propellant rocket engine vacuum specific impulse and oxidant temperatureIt is curve. Engine adopts dinitrogen tetroxide as oxidant, and MMH is as fuel. Two kinds of propellingsAgent constituent element carries out the distribution of propellant by the nozzle being positioned on spray core body, carries out mist in combustion chamberChange, mix, evaporate and burning, in the practical work process of engine, propellant temperature directly affectsThe density of propellant, viscosity, surface tension, and have influence on the flowing of propellant, atomization, evaporation,Mixing and burning process, and then affect the specific impulse of engine. If employing the present invention, just can be by pushing awayEnter the relation of the performance of agent temperature and vacuum specific impulse the performance of engine is revised, modification method is:According to engine propellant temperature and vacuum specific impulse corresponding relation, regulate engine operation by thermal controls apparatusTime applied propellant temperature, finally obtain need engine vacuum specific impulse, thereby provide determineAccurate vacuum specific impulse performance under condition.
In addition, 490N engine is carrying out Satellite Orbit Maneuver when work, by the present invention, and can be according to pushing awayThe propellant temperature that entering system monitoring provides is revised the vacuum specific impulse of engine, thus the propulsion system of realizationAccurate control. Meanwhile complete and become after rail aerial mission at 490N engine, true during due to workThe accuracy of empty specific impulse performance data, the true consumption of propellant can calculate accurately the flight of change rail time.Computational methods are:
Isc＝aT2+bT+c (1)
C＝q.t (3)
Isc--vacuum specific impulse (N.s/kg);
A, b, c-propellant temperature and vacuum specific impulse property relationship coefficient;
T-propellant temperature (DEG C);
Fv-engine vacuum thrust (N);
Propellant flow rate (kg/s) in unit interval when q-engine operation;
T-engine net cycle time (s);
Propellant total burn-off in C-engine working process.
Claims (5)
1. a method for Accurate Assessment space rail control engine vacuum specific impulse performance, is characterized in that: logicalCross following process implementation:
1) obtain engine vacuum thrust and propellant flow rate, according to vacuum specific impulse and vacuum thrust, push awayThat enters agent flux is related to calculation engine vacuum specific impulse; Its computing formula is as follows:Wherein: IsvForVacuum specific impulse, FvFor vacuum thrust, q are total propellant flow rate;
2) when obtaining 1) when described vacuum thrust and propellant flow rate, by propellant tank with push awayEnter the Temperature numerical that the temperature sensor of arranging on agent transfer pipeline obtains propellant;
3) by data fitting above-mentioned 1), 2) in the data obtained, obtain engine vacuum specific impulse and push awayEnter the matched curve that is related between agent temperature, the general type of relation equation is: Isv＝aT2+bT+c，Wherein IsvFor vacuum specific impulse, T is propellant temperature, and a, b, c are relation equation coefficient.
2. a kind of Accurate Assessment according to claim 1 space rail control engine vacuum specific impulse performanceMethod, it is characterized in that: determine different engine vacuum ratios according to the difference of motor power magnitudeRelation equation between punching and propellant temperature.
3. a kind of Accurate Assessment according to claim 1 space rail control engine vacuum specific impulse performanceMethod, it is characterized in that: the different propellant constituent element using according to engine is determined different sending outRelation equation between motivation vacuum specific impulse and propellant temperature.
4. a kind of Accurate Assessment according to claim 1 space rail control engine vacuum specific impulse performanceMethod, it is characterized in that: adopt routine data process approximating method, establish X to for propellant temperature,Y-direction is engine vacuum specific impulse, obtains relation curve according to one group of data point of actual measurement.
5. a kind of Accurate Assessment according to claim 1 space rail control engine vacuum specific impulse performanceMethod, it is characterized in that: described vacuum thrust is by comprising thrust pickup, thrust frame, thrust markThrust Measuring System in fixing on is measured and is obtained;
Described propellant flow rate is surveyed by the flow including mass flowmenter, turbine flowmeter, pipelineAmount system obtains;
Described vacuum thrust and the measurement data of propellant flow rate are by data collecting system collection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110011733.1A CN106134479B (en) | 2011-06-28 | 2011-06-28 | The method of a kind of Accurate Assessment space rail control engine vacuum specific impulse performance |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110011733.1A CN106134479B (en) | 2011-06-28 | 2011-06-28 | The method of a kind of Accurate Assessment space rail control engine vacuum specific impulse performance |
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| CN106134479B true CN106134479B (en) | 2014-04-23 |
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| CN201110011733.1A Expired - Fee Related CN106134479B (en) | 2011-06-28 | 2011-06-28 | The method of a kind of Accurate Assessment space rail control engine vacuum specific impulse performance |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106198033A (en) * | 2016-06-23 | 2016-12-07 | 中国空间技术研究院 | A kind of satellite engine/motor specific impulse computational methods in-orbit |
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2011
- 2011-06-28 CN CN201110011733.1A patent/CN106134479B/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106198033A (en) * | 2016-06-23 | 2016-12-07 | 中国空间技术研究院 | A kind of satellite engine/motor specific impulse computational methods in-orbit |
| CN106198033B (en) * | 2016-06-23 | 2018-08-31 | 中国空间技术研究院 | A kind of in-orbit computational methods of satellite engine/motor specific impulse |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| GRSP | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140423 Termination date: 20200628 |