Technology development and design of a hybrid Mars ascent vehicle concept

Karp, Ashley C.; Redmond, Matt; Nakazono, Barry; Vaughan, David; Shotwell, Robert; Story, George; Dale, Jackson; Young, David L.

doi:10.1109/aero.2016.7500835

Cited by 6 publications

(2 citation statements)

References 16 publications

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“…The samples in the OSC are loaded into the TAV, which is a single-stage rocket that takes the samples to orbit. This vehicle is based on the design proposed by Karp et al [28] which uses a hybrid rocket design. The TAV needs to be capable of 4 km/s of Δ𝑉, based on calculations from [29].…”

Section: Ascent and Returnmentioning

confidence: 99%

ORACLE: A Sample-Return Mission to Titan

et al. 2022

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With a hazy atmosphere, a hydrocarbon cycle, seasons, and a diverse set of surface features, Titan is one of the most unique objects in the Solar System. Further exploration of Titan can elucidate its geologic activity, chemical history, and astrobiological potential. While one-way missions can provide a wealth of information about Titan through remote sensing, in-situ measurements, and communication relays back to Earth, returning samples from Titan allows for unparalleled scientific analysis. Here, we propose a novel mission concept to explore and analyze Titan in situ and return samples from its hydrocarbon lakes. Within ORACLE, a separate lander and orbiter segment will perform all the scientific investigations and collect the hydrocarbon lake samples. After collection of the samples, another segment will return the samples to Earth while the lander and orbiter continue investigating Titan. This mission concept demonstrates novel Titan lake sampling technology and incorporates sample return and in-situ scientific investigation to significantly increase our understanding of Titan, with far broader planetary science implications.

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Section: Ascent and Returnmentioning

confidence: 99%

ORACLE: A Sample-Return Mission to Titan

et al. 2022

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“…Carter [21] discussed technology requirements for propulsion systems such as displacement pumps and bladder lined composite tanks. One of the experimental works for a potential MAV is presented by Karp with paraffin-based fuel and Mixed Oxides of Nitrogen (MON-3) oxidizer [22]. Furthermore, Evans and Karabeyoglu also studied MON based oxidizer for MAV experiment with metallized SP7 fuel by using 30 microns sized aluminum powder [23].…”

Section: Hybrid Propulsion For Mars Ascent Vehiclesmentioning

confidence: 99%

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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