Hybrid rockets with mixed <mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" altimg="si1.svg"><mml:mrow><mml:msub><mml:mi mathvariant="bold-italic">N</mml:mi><mml:mn>2</mml:mn></mml:msub><mml:mi mathvariant="bold-italic">O</mml:mi><mml:mo linebreak="goodbreak" linebreakstyle="after">/</mml:mo><mml:mi mathvariant="bold-italic">C</mml:mi><mml:msub><mml:mi mathvariant="bold-italic">O</mml:mi><mml:mn>2</mml:mn></mml:msub></mml:mrow></mml:math> oxidizers for Mars Ascent Vehicles

Kara, Ozan; Karakaş, Hakkı Muammer; Karabeyoğlu, M. Arif

doi:10.1016/j.actaastro.2020.05.060

Cited by 20 publications

(12 citation statements)

References 7 publications

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“…Igniter compounds moslty consist of potassium nitrate based solid fuels. However, larger rocket motors requires additional igniter motors as presented in [2]. Hybrid rocket motors mostly use circular port grain design.…”

Section: Hybrid Rocket Propulsion Fundamentalsmentioning

confidence: 99%

“…Nitrous oxide is another agent has been used mostly in small rocket systems. Nitrous has self-pressurizing capability at saturated liquid state [2]. Selfpressurization eliminates the need of pressurizing system to feed the oxidizer.…”

Section: Propellant Evaluation In Hybrid Rocketsmentioning

confidence: 99%

“…This reaction produces a substantial energy release. Various metals and metal hydrides have been studied in order to understand the combustion characteristics of carbon dioxide as explained in [2,[10][11][12]. In addition, additional information is presented related to the Metal=CO 2 combustion in Chapter 3.…”

Section: Co 2 As a Novel Oxidizermentioning

confidence: 99%

“…In addition, additional information is presented related to the Metal=CO 2 combustion in Chapter 3. However, fundamental findings from [2,[10][11][12] are explained in this section.…”

Section: Co 2 As a Novel Oxidizermentioning

confidence: 99%

“…Moreover, the condensed phase combustion products make the turbojet engine impractical. All these circumstances make rocket propulsion systems more practical for Martian operations [2].…”

Section: Introductionmentioning

confidence: 99%

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Hybrid Propulsion System: Novel Propellant Design for Mars Ascent Vehicles

Kara¹,

Karabeyoğlu²

2021

Propulsion - New Perspectives and Applications

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This chapter briefly introduces hybrid rocket propulsion for general audience. Advantageous of hybrid rockets over solids and liquids are presented. This chapter also explains how to design a test setup for hybrid motor firings. Hybrid propulsion provides sustainable, safe and low cost systems for space missions. Therefore, this chapter proposes hybrid propulsion system for Mars Ascent Vehicles. Paraffin wax is the fuel of the rocket. Propulsion system uses CO2/N2O mixture as the oxidizer. The goal is to understand the ignition capability of the CO2 as an in-situ oxidizer on Mars. CO2 is known as major combustion product in the nature. However, it can only burn with metallic powders. Thus, metallic additives are added in the fuel grain. Results show that CO2 increase slows down the chemical kinetics thus reduces the adiabatic flame temperature. Maximum flammability limit is achieved at 75% CO2 by mass in the oxidizer mixture. Flame temperature is 1700 K at 75% CO2. Ignition quenches below the 1700 K.

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Section: Hybrid Rocket Propulsion Fundamentalsmentioning

confidence: 99%

Section: Propellant Evaluation In Hybrid Rocketsmentioning

confidence: 99%

Section: Co 2 As a Novel Oxidizermentioning

confidence: 99%

“…In addition, additional information is presented related to the Metal=CO 2 combustion in Chapter 3. However, fundamental findings from [2,[10][11][12] are explained in this section.…”

Section: Co 2 As a Novel Oxidizermentioning

confidence: 99%

“…Moreover, the condensed phase combustion products make the turbojet engine impractical. All these circumstances make rocket propulsion systems more practical for Martian operations [2].…”

Section: Introductionmentioning

confidence: 99%

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