Unsteady simulation and experimental study of hydrogen peroxide throttleable catalyst hybrid rocket motor

Zhao, Bo; Yu, Nanjia; Liu, Yuanyuan; Zeng, Peng; Wang, Jue

doi:10.1016/j.ast.2018.02.008

Cited by 26 publications

(7 citation statements)

References 18 publications

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“…where U m is the supply voltage of the motor, R m is the resistance of the circuit, i m is the current, L m is the inductance, t is the time, and e m is the back electromotive force, which can be calculated by e m = C e ω (2) where C e is the back electromotive coefficient of the motor and ω is the rotational angular velocity of the motor.…”

Section: Dynamics Modelingmentioning

confidence: 99%

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System analysis and controller design for the electric pump of a deep-throttling rocket engine

Ferrari

Chen

et al. 2021

Aerospace Science and Technology

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This paper proposes a controller design for the electric pump of a deep-throttling rocket engine. The nonlinearity of the system is taken into consideration by analyzing the gap metric. Then, proportionalintegral-derivative controller and gain-scheduling linear quadratic regulator are designed. Analyzing the amplitude-and phase-frequency characteristics as well as the pole-zero distribution of the system, the results show that the designed controllers can stabilize the linearized equations in incremental form at different operating points. This indicates that these two controllers are available for the original system in the whole range of working conditions and this is verified in the simulation. Meanwhile, the comparison between proportional-integral-derivative controller and gain-scheduling linear quadratic regulator is presented. It demonstrates that the proportional-integral-derivative controller is better at tracking both step and ramp signals but with worse control signals. It means that the proportionalintegral-derivative controller seems less suitable for real use due to severe oscillations. Meanwhile, the parameter tuning of a proportional-integral-derivative controller depends on more extensive manual tuning. Therefore, the gain-scheduling linear quadratic regulator is preferred.

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Section: Dynamics Modelingmentioning

confidence: 99%

“…Liquid-propellant rocket engines (LREs) are the main power equipment used for space transportation systems and spacecraft propulsion and maneuver [1,2]. Liquid-propellant rocket engine with thrust that can be varied in a wide range has gained much importance in recent years.…”

Section: Introductionmentioning

confidence: 99%

System analysis and controller design for the electric pump of a deep-throttling rocket engine

Ferrari

Chen

et al. 2021

Aerospace Science and Technology

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“…This was due to the limited control authority of the valve and the significant effect that small changes in valve angle have on oxidizer mass flow rate. Experimental data and simulations from Zhao et al (2018) have shown that a lag time in the motor response of a paraffin-wax motor exists, as the fuel regression rate cannot respond to the oxidizer flow rate change immediately. In the third stage (III), the command profile is given to throttle down to 310 N. In the fourth and final stage (IV), the command is given to throttle the motor back up to 480 N, but, as Fig.…”

Section: Closed Loop Testingmentioning

confidence: 99%

Closed Loop Throttle Control of a Liquefying Fuel Hybrid Rocket Motor

Velthuysen

Brooks

Pitot

2021

J. Aerosp. Technol. Manag.

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The thrust produced by a hybrid rocket motor (HRM) can be controlled by varying the oxidizer flow rate to the combustion chamber. This feature is useful in shaping motor thrust profiles and optimizing a vehicle flight trajectory, but propellant throttling in solid-fuel hybrids is limited to the liquid component only, complicating the control scheme and potentially destabilizing combustion in the motor. While hybrid motor throttling ability remains a subject of considerable interest, there has been little investigation of throttling in motors that use high regression rate, liquefying fuels such as paraffin wax. This article describes the development and implementation of a closed loop thrust control scheme for a laboratory-scale paraffin wax/nitrous oxide HRM using a low-cost ball valve as the controlling hardware element. A model of motor performance is first developed from which proportional-integral-derivative (PID) controller constants are obtained through experimental testing. The control scheme is demonstrated through closed loop hot fire tests of a laboratory-scale motor in which thrust tracks a set-point value with feedback provided through a load cell. Upon reaching the setpoint, the motor remains throttled within ± 2.4% of the maximum thrust of the motor. Constant and ramping thrust profiles are demonstrated.

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“…The vacuum performance of a HTP hybrid rocket motor has been demonstrated experimentally with a combustion efficiency of approximately 98% [49]. Apart from the use of higher HTP grades and concentrations, increased interest in throttleable HTP hybrid rocket motors [2,50,51] and work on solid fuels hypergolic with HTP [41,52] can be seen. Another trend considers additive manufacturing of fuel grains.…”

Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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Unsteady simulation and experimental study of hydrogen peroxide throttleable catalyst hybrid rocket motor

Cited by 26 publications

References 18 publications

System analysis and controller design for the electric pump of a deep-throttling rocket engine

System analysis and controller design for the electric pump of a deep-throttling rocket engine

Closed Loop Throttle Control of a Liquefying Fuel Hybrid Rocket Motor

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

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