The new generation of rocket engines, operating by ecologically safe propellant “liquid oxygen and liquefied natural gas(methane)”

Klepikov, I.A.; Katorgin, Boris; Chvanov, Vladimir

doi:10.1016/s0094-5765(98)00076-9

Cited by 38 publications

(9 citation statements)

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“…Using paper [6] we obtain the rate between throat area t A and exit area of the nozzle e A propose the relation:…”

Section: Internal Ballistic Modelmentioning

confidence: 99%

Small Launcher Enabled by Hybrid Rocket Motor Technology

Mingireanu¹

2016

The International Conference on Applied Mechanics and Mechanica

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In this paper, we present a small launcher for payloads <10kg and orbits of 350-400 km as well as for suborbital flights with larger payload. Currently there is an increasing demand for small launchers, demand that is increased especially by the nano-satellite expanding missions as well as a strategy shift to smaller and more efficient payloads. Advancements in electronics helped this direction by creating smaller and more powerful computers and communication equipments that can be fitted on smaller satellites with performances at least equal with the ones from the previous generation. We propose a three stage small launcher powered by solid-hybrid-hybrid combination. We investigate the full flight dynamics of the launcher with internal ballistic models for the hybrid rocket motors. The relatively new proposal is to use hybrid rocket motor technology for the second and third stage due to its lower cost of manufacturing as well as simplicity compared to liquid rocket motors. At the same time the performance promise from hybrid rocket motors and their throttable capabilities makes them ideal candidates for upper stage propulsion. Detailed discussion is performed related to the performance of hybrid rocket motors and its influence on launcher lift capability. We also show the preliminary design of such hybrid rocket motors as upper stage propulsion units and propose several fuel/oxidizer pairs based on both technical performances as well as cost parameters. LOX and solid methane are proposed as best oxidizer and fuel candidates in order to obtain a high specific impulse for the upper stages. Next we present a full 6 DOF model for the flight of the launcher as well as simulation results for various flight scenarios ending with different payloads on different orbits. Discussion is performed on guidance and control systems illustrating the main limitations and the option to use as many as possible COTS due to their availability and low design-production cycle. The paper ends with a discussion related to optimization procedures for a small launcher due to its importance on launcher performances and price of operation.

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“…Using paper [6] we obtain the rate between throat area t A and exit area of the nozzle e A propose the relation:…”

Section: Internal Ballistic Modelmentioning

confidence: 99%

Small Launcher Enabled by Hybrid Rocket Motor Technology

Mingireanu¹

2016

The International Conference on Applied Mechanics and Mechanica

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“…Regarding methane based hybrid rocket motors, we can mention that V. P. Glushko and G. E. Langemak first mentioned methane as a possible rocket fuel in a book written 60 years ago [6]. However, at that time the utilization of methane (as well as hydrogen) was not given enough consideration due to low density.…”

Section: Introductionmentioning

confidence: 99%

Solid methane hybrid rocket engine. Regression speed increase by oxidizer doping and embedding wires. Vehicle optimization application through motor parameters.

Mingireanu

2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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This paper presents a novel fuel to be considered for hybrid rocket motors: solid methane. We are showing the potential that this fuel has for hybrid rocket motors from technical perspective as well as from economical perspective. We present an internal ballistic model used to design a hybrid rocket motor with solid methane. We also present a comparison table for solid methane and various cryogenic and non-cryogenic oxidizers. The maximum specific impulse is obtained for the solid methane-LOX pair with a value of ~315 seconds under specific conditions. Although a solid methane-LOX motor shows higher than averages values for the regression speed, these values are still low by performance standards. We present two models that predict the regression speed increase for embedding wires and for oxidizer doping with a factor of ~2-3. An experimental setup that can be used to verify these models is further presented in the paper. Finally, we present a potential application for solid methane hybrid rocket motors in the form of an upper stage propulsion unit for orbital/suborbital vehicles. We find a practical interdependence relation between structural optimization (dry mass) of the launcher and the performance parameters of the motor. We present a study case of such a vehicle intended to place a 50 kg payload on low earth orbit (300 to 500 km altitude). Developing such a launcher is both environmentally safer than current approaches and economically more efficient because methane reserves are a rich resource worldwide.

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“…We mentioned Rishka in Russia [8] and G-IIX in Japan [9]. We have also to mention that LOX/CH4 have been selected for the EADS space tourism flight vehicle [10].…”

Section: Iintroductionmentioning

confidence: 99%

LOX/CH4 and LOX/LH2 Heavy Launch Vehicle Comparison

Vernin¹,

Pempie²

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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LOX/CH4 is often regarded as a new promising propellant. As a light hydrocarbon the advantage of methane compared to RP-1 is its worldwide availability, higher ISP. From a propulsion point of view methane leads to low soot combustion and a good capability to cool the combustion chamber without the risk of cracking and deposit. Compared to liquid Hydrogen fuel despite its lower IPS, methane presents a higher density and a high vapor pressure.The topic of this paper is to present a trade-off design of two kinds of heavy launch vehicle able to bring to GTO a 6t class payload. Each of three stages of the launcher burn either LOX/LH2 or LOX/CH4. The key factors for comparison are the GLOW, the propellant mass and engines thrust for each stage. NomenclatureFs = Delivered thrust at ground level (kN) Fv = Delivered thrust at sea level (kN) ISPs = Specific impulse at ground level (s) ISPv = Specific impulse at sea level (s) Me = Propellant mass (T) Pc = Chamber pressure (bar)

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The new generation of rocket engines, operating by ecologically safe propellant “liquid oxygen and liquefied natural gas(methane)”

Cited by 38 publications

References 0 publications

Small Launcher Enabled by Hybrid Rocket Motor Technology

Small Launcher Enabled by Hybrid Rocket Motor Technology

Solid methane hybrid rocket engine. Regression speed increase by oxidizer doping and embedding wires. Vehicle optimization application through motor parameters.

LOX/CH4 and LOX/LH2 Heavy Launch Vehicle Comparison

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