CN105606368A - Solid rocket engine gas flow adjustment cold-flow and hot-flow ground test systems - Google Patents
Solid rocket engine gas flow adjustment cold-flow and hot-flow ground test systems Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention relates to solid rocket engine gas flow adjustment cold-flow and hot-flow ground test systems. The solid rocket engine gas flow adjustment cold-flow ground test system comprises a test stand, a flow adjustment control system and a cold state simulation test system, the solid rocket engine gas flow adjustment hot-flow ground test system comprises a test stand, a flow adjustment control system and a hot test system. The two test systems can realizing monitoring on two types of performance of a solid rocket engine, a cold-flow flow adjustment test and a gas generator hot-flow flow adjustment test on the solid rocket engine can be realized, so the two test systems almost can realize all tests of a research period of the solid rocket engine flow adjustment technology, through the two simulation test systems, the performance of the solid rocket engine flow adjustment technology can be effectively monitored, the research period is shortened, igniting test frequency of the solid rocket engine is reduced, and safety and the success rate are improved.
Description
Technical field
The present invention relates to Ducted rocket gas flow and regulate cold flow and hot-fluid ground system test, belong to Gu ChongThe simulated test field of engine.
Background technology
At present, on rocket in the world, especially medium range air-to-air missile, adopted Ducted rocket as leadingThe power drive device of bullet, Flow-rate adjustment technology is one of mark of advanced Ducted rocket, this technique guaranteeGuided missile in flight border, high maneuver warfare situation, also have good function of the engine. As Fig. 1Shown in, be Ducted rocket model, comprise gas generator and boosting afterburning chamber, the output of gas generatorEnd is communicated with the input of boosting afterburning chamber by flow regulator. Flow regulator comprises Flow-rate adjustmentValve and interlinked mechanism. Can be to regulate motor for regulating the device of this control valve, can be also otherAdjusting device, such as barometric control unit or hydraulic regulating device. Regulate motor to enter control valve when usingWhen row regulates, regulate electromechanics this control valve that is in transmission connection, by control the rotation of this adjusting motor come rightAnswer adjust flux control valve, to change the throat opening area of gas generator.
Ducted rocket has the features such as cost is high, not reproducible, and each piece of guided missile all drops into a large amount ofMan power and material's capital, this just need to be to carrying out property of key technology such as the Ducted rocket Flow-rate adjustment in guided missileEnergy is tested, but in currently available technology, does not have a kind of property of effective Ducted rocket Flow-rate adjustment technologyCan pilot system.
Summary of the invention
The object of this invention is to provide Ducted rocket gas flow and regulate cold flow and hot-fluid ground system test,For Ducted rocket is carried out to simulated test and the performance monitoring of Flow-rate adjustment.
For achieving the above object, the solution of the present invention comprises that a kind of Ducted rocket gas flow regulates cold flow groundInterview check system, comprises testboard bay, flow regulating control system and cold-simulation test system; Described surveyExamination stand is used for setting firmly Ducted rocket model, and described flow regulating control system is used for gathering gas generatorPressure and the opening information of flow control valve flow control valve is carried out to Flow-rate adjustment control; Described cold conditionsSimulation experiment system comprises source of the gas part and air path part, and described source of the gas part is sent out by air path part and combustion gasRaw device is communicated with to realize gas generator is carried out to the given pressure of cold conditions air feed with simulation gas generator.
Described flow regulating control system comprises industrial computer, and described industrial computer adopts Flow-rate adjustment control, described inFlow-rate adjustment control is two closed-loop controls, and this pair of closed-loop control comprises in a pressure outer shroud and an apertureRing, between the pressure of the gas generator inside in described pressure outer shroud and the given pressure of gas generatorDifference is the specified rate for encircling in described aperture after a PID controller, described in the flow control valve that collectsOpening information be the feedback quantity of ring in aperture, the feedback quantity encircling in the specified rate of ring and aperture in described apertureAfter doing difference, input to the 2nd PID controller, the control signal of the 2nd PID controller output is for adjust fluxThe aperture of control valve.
Described cold-simulation test system also comprises observing and controlling part, and described air path part comprises that a gas circuit is logicalRoad, on described gas channels, string is provided with flowmeter, cold conditions control valve and master control magnetic valve, described observing and controlling partSampling connects described flowmeter, cold conditions control valve and master control magnetic valve described in control connection.
Described master control magnetic valve is in parallel with a magnetic valve parallel branch, and described magnetic valve parallel branch is by leastArticle one, magnetic valve branch circuit parallel connection forms, and on each magnetic valve branch road, all string is provided with a magnetic valve.
A kind of Ducted rocket gas flow regulates hot-fluid ground system test, comprises testboard bay, flow tuneJoint control system and the heat check system of having a try; Described testboard bay is used for setting firmly Ducted rocket model, described streamQuantity regulation and control system is used for gathering the pressure of gas generator and the opening information of flow control valve is carried out convection currentAdjustable valve carries out Flow-rate adjustment control; The described heat check system of having a try comprises source of the gas part, admission line and useIn the heating part that the gas of source of the gas part output is heated, described source of the gas part by admission line withGas generator is communicated with, and described heat is had a try check system for exporting the engine charge of different pressures and temperature.
Described flow control system comprises industrial computer, and described industrial computer adopts Flow-rate adjustment control, described flowRegulate and control as two closed-loop controls, this pair of closed-loop control comprises ring in a pressure outer shroud and an aperture, instituteState the difference between the pressure of the gas generator inside in pressure outer shroud and the given pressure of gas generatorSpecified rate for encircling in described aperture after a PID controller, described in the opening of the flow control valve that collectsDegree information is the feedback quantity of ring in aperture, and it is poor that the feedback quantity of the interior ring of the specified rate encircling in described aperture and aperture doesAfter input to the 2nd PID controller, the control signal of the 2nd PID controller output regulates for adjust fluxThe aperture of valve.
Described heating part is incoming flow heating analogue means, and the described heat check system of having a try also comprises control measurement portionPoint, described incoming flow heating analogue means string is located on described admission line, and described control measurement part is for controlMake described incoming flow heating analogue means, and monitor incoming flow parameter; Described incoming flow heating analogue means is for generatingThe engine charge of different pressures, different temperatures.
Ducted rocket gas flow adjusting cold flow provided by the invention and hot-fluid ground system test can be rightDucted rocket carries out respectively the monitoring of two kinds of performances, to Ducted rocket carry out cold flow Flow-rate adjustment test andThe test of gas generator hot-fluid Flow-rate adjustment, has almost contained the Ducted rocket Flow-rate adjustment technology lead timeTotal Test; Can carry out the performance of Ducted rocket Flow-rate adjustment technology by these two simulated testsEffectively monitoring, shortens the R&D cycle, reduces engine ignition test number (TN), improves security and success rate.
It is low, dangerous little that these two systems have cost, the repeatable feature of exploring; The design of this systemLevel and applicable cases, all reached advanced international level; And these two systems become for Ducted rocketThis height, not reproducible, beforehand research have the features such as dangerous, interim according to emulation, cold flow, hot runin exhibitionTest, guarantees safe and orderly.
These two systems have very the scientific research stage investigative test of the various flow control valve in engineStrong directive significance and very high security, can farthest reduce functional study and comply with test-firedRely, reduced risk, improved success of the test rate, the flow control valve of different structure, different Types of Medicine is groundStudy carefully and there is versatility.
In the emulation of many wheels, cold-flow test and several times on test-fired basis of short time, analyze data, optimizationImprove, finally can complete smoothly long-time punching press Flow-rate adjustment test examination in up to a hundred seconds. These two systems canEnsure scientific research and testing safety, orderly carrying out, reduce costs and risk, there is higher economic serviceability.
Brief description of the drawings
Fig. 1 is the part-structure schematic diagram of Ducted rocket;
Fig. 2 is that Ducted rocket gas flow regulates the control between cold flow ground system test and Ducted rocketSchematic diagram processed;
Fig. 3 is the control chart of flow regulating control system;
Fig. 4 is the structural representation of the air path part of cold-simulation test system;
Fig. 5 is that Ducted rocket gas flow regulates the control between hot-fluid ground system test and Ducted rocketSchematic diagram processed.
Detailed description of the invention
The invention provides two kinds of Ducted rocket gas flows and regulate ground system test, is respectively that Gu Chong sends outMotivation gas flow regulates cold flow ground system test and Ducted rocket gas flow to regulate the interview of hot-fluid groundCheck system, these two pilot systems can be simulated the flow relevant parameter of Ducted rocket, by controlling flowControl valve changes by the flow of combustion gas spout, and then changes the performance of Ducted rocket.
Why these two systems are ground system test, are because both are all without trying in MISSILE LAUNCHING flightIn testing, carry out, but just can carry out simulated test on ground. According to interim scientific research and development requirement, Jiang GuchongThe ground performance study on monitoring of engine Flow-rate adjustment technology can be divided into three phases test, HWIL simulation examinationTest, cold conditions flow simulation test and the test of gas generator hot-fluid, these three test corresponding corresponding examinations respectivelyTest subsystem, instruct thus experimental study complete by the stage and optimize. Wherein, Hardware-in-loop Simulation Experimentation and coldState flow simulation is tested corresponding flow regulating control system and cold-flow test system, matter emulation test and heat examinationThe corresponding flow regulating control system of fire trial and hot-fluid pilot system.
Below in conjunction with accompanying drawing to the concrete knot in these two Ducted rocket Flow-rate adjustment ground system testsStructure and effect thereof are further described in detail.
Ducted rocket gas flow regulates cold flow ground system test embodiment
As shown in Figure 2, Ducted rocket gas flow regulates cold flow ground system test, comprise testboard bay,Flow regulating control system and cold-simulation test system. Testboard bay for setting firmly Gu Chong in the time testingEngine mockup, and the present embodiment and heat below has a try in check system embodiment, and flow regulator is equalFormed by flow control valve and adjusting motor.
Flow regulating control system is a Semi-physical simulation system, and the test that this test relies on dividesSystem is core and the basis of all ground Flow-rate adjustment controlling test, is driven by industrial computer, capture card, motorMoving box, sensor composition. Wherein industrial computer gathers the pressure of gas generator by capture card and sensor(this current potential information regulates the potentiometer at motor place to enter by being arranged on to the current potential information of strong information and adjusting motorRow detects and feeds back to industrial computer); Industrial computer drives box control and regulation motor by motor, drives box to be used forRegulate power drive and the signal condition of motor. The software program that industrial computer arranges by inside andSimulink platform is controlled and is driven box to complete simulation Technique Study and Flow-rate adjustment is controlled in real time. In addition,Control and research in order to realize smoothly, the signal of collection also has current signal, Timing Signal etc.
For flow is carried out to real-time regulation and control, the control strategy to gas generator in industrial computerCarry out modeling, be specially a Flow-rate adjustment control method. Gas generator and flow control valve are reduced toThe first order inertial loop that band lags behind, as shown in Figure 3, this Flow-rate adjustment control is two closed-loop controls, in employingThe control of outer shroud cascade PID, comprises ring in a pressure outer shroud and a current potential, and outer shroud is measured gas generatorInternal pressure as feedback quantity, by given pressure with feedback pressure error deliver in PID1 controller,The specified rate encircling in again as current potential through the output quantity after treatment of this PID1 controller; In encircling in current potential,Measure potentiometer angle as the feedback quantity encircling in current potential, by what encircle in the specified rate encircling in current potential and current potentialThe difference of feedback quantity is sent in PID2 controller, and after PID2 controller is processed, the control signal of output is passed throughMotor drives box to control to adjust the rotational angle of motor, thereby changes the throat opening area of gas generator,Pressure changes thereupon, thereby realizes the closed-loop control of gas generator operating pressure.
Between gas generator pressure and throat opening area, exist compared with strong nonlinearity, increase with exponential relationship, therefore workControl machine is corresponding employing variable-gain controller segmentation control also, thereby reduce the non-linear impact bringing. Program is excellentWhile also design in change, unite security interpretation, output violent change, integration anti-saturation measure etc., reduce empirical risk.On the basis that system modelling completes, repeatedly carry out inner and outer ring controller parameter matching and debugging, meet overall controlIndex.
This industrial computer can complete the rapid modeling of control object by inner Flow-rate adjustment control strategy, controlThe algorithm debugs, reduction test cost, improve development speed.
Above-mentioned carrying out in Flow-rate adjustment control procedure, need the certain pressure of given gas generator, and lead toSupercooled state simulation experiment system is exported this given pressure. So this Flow-rate adjustment control procedure is mainly by cold conditionsSimulation experiment system has coordinated test with flow regulating control system, as shown in Figure 4, and Flow-rate adjustment controlSystem is responsible for gas generator and flow control valve control and feed back measurement, cold-simulation test systemEngine is carried out to cold conditions air feed simulation gas generator pressure, and analog detection flow control valve is in emulation modeUnder performance test, and the performance test of this engine under different pressure.
As a specific embodiment, this cold-simulation test system mainly comprises three parts, source of the gas part,Air path part and observing and controlling part, wherein source of the gas part is that gas generator carries out cold conditions confession by air path partGas. Air path part mainly comprises flowmeter, control valve and magnetic valve, and the sampling of observing and controlling part connects gas circuit portionFlowmeter in point, the flow information detecting for Real-time Collection flowmeter, control connection air path partIn the valve such as control valve and magnetic valve. Observing and controlling part can be existing control chip, such as: singleSheet machines etc., the software program arranging by inside is realized corresponding function.
This air path part comprises the first gas channels, and as shown in Figure 4, on this first gas channels, string is provided with streamAmount meter, control valve and electromagnetic valve pipeline system, wherein electromagnetic valve pipeline system is by several magnetic valve branch roadsFormation in parallel, on each magnetic valve branch road, all string is provided with a magnetic valve. As shown in Figure 4, in figure, GFor filter, Q, Q1-Q5 are ball valve, and D1-D6 is magnetic valve, and TJ is control valve, and KB1-KB3 is holePlate flowmeter, Z is check-valves, JZ1-JZ2 is stop valve, QF gas cylinder, P1-P3 is pressure-measuring-point,T1 is temperature point.
This cold-simulation test system realizes constant flow or fixed by the assembled scheme control of each magnetic valve, ball valvePressure functional test realizes constant flow rate function in 0.3～15MPa pressure limit; Can be 0.3～Within the scope of 10MPa, complete the pressure disturbances function of gas generator. The cold conditions of cold-simulation test system simulationGas has been simulated the pressure condition in gas generator, can examine flow regulator under cold conditions condition of high voltageBearing capacity, mechanism action ability.
Wherein, cold flow constant flow test: select the aperture of control valve pipeline according to flow, utilize orifice plate flowThe flow of meter acquisition system, until flow reaches desired value, then completes Control experiment by flow control system.
Cold flow constant-pressure test: by the pressure of emulation test system Real-Time Monitoring gas generator, reach targetWhen value, keep control valve opening constant, whether the flow of observing now meets the safe adjustable range of cold flow system makes,Then complete Control experiment by flow control system.
Forward/negative pressures interference test: on the basis of constant flow function, control fast a certain way solenoid valveOpen, close, produce pressure pulse, form forward/negative sense and disturb.
Ducted rocket gas flow regulates hot-fluid ground system test embodiment
As shown in Figure 5, Ducted rocket gas flow regulate hot-fluid ground system test comprise testboard bay,Flow regulating control system and the heat check system of having a try; Wherein, the structure of flow regulating control system and functionAct on all identical with the flow regulating control system in above-mentioned cold-flow test system embodiment, no longer concrete hereExplanation.
The heat check system of having a try comprises source of the gas part, incoming flow heating analogue means and control measurement part, source of the gas portionPoint provide engine charge by admission line for gas generator, incoming flow heating analogue means string is located at air inletOn pipeline, it is gas-heated that control measurement part is used for controlling incoming flow heating analogue means, to realize generation notThe gas of same pressure, different temperatures; Control measurement part is also for monitoring the flow parameter of incoming flow gas. ComeStream heating analogue means is used to engine charge to heat to change the temperature of engine charge, and this incoming flow heatsAnalogue means can be an existing heater, realizes the order of heated engine air inlet by fuel combustion. Be the inlet air conditions that incoming flow heating analogue means can be under ground simulation engine true altitude environment, fromAnd complete the ignition of gas generator under hot-fluid air inlet, and carry out the Gas-Generator Flow of real simulation conditionRegulate test. So, can be embodied as engine different pressures and difference are provided by this heat check system of having a tryThe engine charge of temperature. In addition, control measurement part can be industrial computer or single-chip microcomputer, by insideThe software program of setting is realized corresponding function.
The heat of the engine check system of having a try has coordinated gas generator hot-fluid stream with flow regulating control systemAmount regulates test, forms and sees Fig. 5. Flow regulating control system is responsible for control and the feedback of flow control valve,The heat check system of having a try is responsible for igniting, Timing Signal Synchronization Control and the simulated altitude incoming flow situation of engine. ?Under hot examination state, examine the functions such as the pressure-bearing, thermal protection, control of flow regulator. Heat examination certification test bagDraw together the short time, long-time Gas-Generator Flow regulates test, and short time punching press, long-time punching press flowRegulate test, pressure limit contains low pressure to high pressure. Ducted rocket Flow-rate adjustment heat is had a try while testing, utilizesTestboard bay fixes testpieces product---Ducted rocket, and volume control device and heating part are according to heightThe pressure and temperature of empty condition simulated engine air inlet, carries out engine ignition after reaching state, simultaneously flowThe work of regulation and control system control flow regulator, completes collection high-altitude flight condition, flow-control, ignitingHave a try and test in the Flow-rate adjustment heat of one, examination powder charge characteristic, bearing capacity, flow-control, Flow-rate adjustmentThe performance indications such as compare.
So two Ducted rocket Flow-rate adjustment ground system tests provided by the invention can complete respectivelyBelow test: cold-simulation test system has coordinated the examination of Flow-rate adjustment cold flow with flow regulating control systemTest, the heat of the engine check system of having a try has coordinated gas flow to regulate hot-fluid examination with flow regulating control systemTest.
In above-mentioned two embodiment, the Flow-rate adjustment control strategy in the industrial computer in flow regulating control systemFor encircling in pressure outer shroud and current potential, wherein in current potential, the current potential information in ring is the information that regulates motor, regulatesMotor is for driving control valve to realize the aperture that regulates this control valve, so collection regulates the current potential of motorInformation is equivalent to gather the opening information of control valve, and final result is all to adjust for the aperture to control valveJoint is controlled. When gather be opening information time, this pair of closed-loop control comprises a pressure outer shroud and one soRing in aperture, between the pressure of the gas generator inside in pressure outer shroud and the given pressure of gas generatorDifference specified rate for encircling in aperture after PID1 controller, the actual of the flow control valve collecting opensDegree information is the feedback quantity of ring in aperture, and in the specified rate of the interior ring of aperture and aperture, the feedback quantity of ring does poor rear defeatedEnter the controller to PID2, the control signal of PID2 controller output is for the aperture of adjust flux control valve.
The present invention mainly provides two kinds of Ducted rocket Flow-rate adjustment ground system tests, wherein, and Gu ChongEngine Flow-rate adjustment ground cold-flow test system mainly comprises flow regulating control system and cold conditions simulation examinationCheck system, Ducted rocket Flow-rate adjustment ground hot-fluid pilot system mainly comprise flow regulating control system andThe heat check system of having a try, these subsystems have corresponding function separately, by wherein between system mutuallyIn conjunction with realizing corresponding function, so the overall system architecture that focuses on of the present invention, by threeCombination between subsystem is monitored the performance of Ducted rocket Flow-rate adjustment, so this invention alsoBe not limited to the concrete structure of each subsystem, such as: cold-simulation test system only includes a controllerWith a supply air line, on supply air line, string is provided with a magnetic valve, and controller is by controlling solenoid valve conductionOr turn-off and realize different gas pressure intensities.
Claims (7)
1. Ducted rocket gas flow regulates a cold flow ground system test, it is characterized in that, comprisesTestboard bay, flow regulating control system and cold-simulation test system; Described testboard bay is used for setting firmlyRush engine mockup, described flow regulating control system is for gathering pressure and the Flow-rate adjustment of gas generatorThe opening information of valve is carried out Flow-rate adjustment control to flow control valve; Described cold-simulation test system comprisesSource of the gas part and air path part, it is right that described source of the gas part is communicated with to realize with gas generator by air path partGas generator carries out the given pressure of cold conditions air feed with simulation gas generator.
2. Ducted rocket gas flow according to claim 1 regulates cold flow ground system test,It is characterized in that, described flow regulating control system comprises industrial computer, and described industrial computer adopts Flow-rate adjustment controlSystem, described Flow-rate adjustment control be pair closed-loop controls, this pair of closed-loop control comprises a pressure outer shroud and oneRing in aperture, the pressure of the gas generator inside in described pressure outer shroud and the given pressure of gas generatorBetween difference specified rate for encircling in described aperture after a PID controller, described in the flow that collectsThe opening information of control valve is the feedback quantity of ring in aperture, the interior ring of the specified rate encircling in described aperture and apertureFeedback quantity inputs to the 2nd PID controller after doing difference, and the control signal of the 2nd PID controller output is for adjustingThe aperture of amount of restriction control valve.
3. Ducted rocket gas flow according to claim 1 regulates cold flow ground system test,It is characterized in that, described cold-simulation test system also comprises observing and controlling part, and described air path part comprises oneGas channels, on described gas channels, string is provided with flowmeter, cold conditions control valve and master control magnetic valve, described surveyControl part sampling connects described flowmeter, cold conditions control valve and master control magnetic valve described in control connection.
4. Ducted rocket gas flow according to claim 3 regulates cold flow ground system test,It is characterized in that, described master control magnetic valve is in parallel with a magnetic valve parallel branch, in parallel of described magnetic valveRoute at least one magnetic valve branch circuit parallel connection forms, and on each magnetic valve branch road, all string is provided with an electromagnetismValve.
5. Ducted rocket gas flow regulates a hot-fluid ground system test, it is characterized in that, comprisesTestboard bay, flow regulating control system and the heat check system of having a try; Described testboard bay is used for setting firmly Gu Chong and sends outMotivation Model, described flow regulating control system is for gathering the pressure of gas generator and flow control valveOpening information is carried out Flow-rate adjustment control to flow control valve; The described heat check system of having a try comprises source of the gas portionPoint, admission line and the heating part for the gas of source of the gas part output is heated, described source of the gas portionDivide and be communicated with gas generator by admission line, described heat is had a try check system for exporting different pressures and temperatureThe engine charge of degree.
6. Ducted rocket gas flow according to claim 5 regulates hot-fluid ground system test,It is characterized in that, described flow control system comprises industrial computer, and described industrial computer adopts Flow-rate adjustment control,Described Flow-rate adjustment control is two closed-loop controls, and this pair of closed-loop control comprises a pressure outer shroud and an apertureInterior ring, between the pressure of the gas generator inside in described pressure outer shroud and the given pressure of gas generatorDifference specified rate for encircling in described aperture after a PID controller, described in the Flow-rate adjustment that collectsThe opening information of valve is the feedback quantity of ring in aperture, the feedback of ring in the specified rate of ring and aperture in described apertureAmount inputs to the 2nd PID controller after doing difference, and the control signal of the 2nd PID controller output is used for regulating streamThe aperture of adjustable valve.
7. Ducted rocket gas flow according to claim 5 regulates hot-fluid ground system test,It is characterized in that, described heating part is incoming flow heating analogue means, and the described heat check system of having a try also comprises prisonControl measure portion, described incoming flow heating analogue means string is located on described admission line, described control measurement portionDivide for controlling described incoming flow heating analogue means, and monitor incoming flow parameter; Described incoming flow heating analogue meansFor generating the engine charge of different pressures, different temperatures.
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| CN106053083B (en) * | 2016-06-06 | 2018-11-13 | 南京理工大学 | A kind of solid engines cold air impact experiment apparatus |
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| CN106797847A (en) * | 2016-10-24 | 2017-06-06 | 中国路桥工程有限责任公司 | A kind of rainer |
| CN108628183A (en) * | 2018-04-20 | 2018-10-09 | 南京理工大学 | Variable-flow gas generator pressure controls semi-matter simulating system |
| CN109139300A (en) * | 2018-08-29 | 2019-01-04 | 南京理工大学 | Flow adjustable gas generator simulation system based on DSP and ARM |
| CN110608891A (en) * | 2019-09-04 | 2019-12-24 | 陕西蓝箭航天技术有限公司 | Cold flow test system of liquid rocket engine and parallel storage tank propellant conveying balance performance test method |
| CN110608891B (en) * | 2019-09-04 | 2024-03-26 | 陕西蓝箭航天技术有限公司 | Cold flow test system of liquid rocket engine and parallel storage tank propellant conveying balance performance test method |
| CN112682221A (en) * | 2020-12-14 | 2021-04-20 | 西安航天动力试验技术研究所 | Attitude control engine high-mode ignition test thermal environment real-time adjusting and accurate loading method |
| CN112682221B (en) * | 2020-12-14 | 2022-03-11 | 西安航天动力试验技术研究所 | Attitude control engine high-mode ignition test thermal environment real-time adjusting and accurate loading method |
| CN114251190A (en) * | 2021-11-09 | 2022-03-29 | 北京动力机械研究所 | Low-cost solid-impact engine control method |
| CN115324772A (en) * | 2022-07-28 | 2022-11-11 | 北京控制工程研究所 | Method for predicting mixing ratio of propellant of double-component thruster |
| CN115324772B (en) * | 2022-07-28 | 2024-05-31 | 北京控制工程研究所 | Method for predicting mixing ratio of propellants of two-component thruster |
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