Green Propellant Infusion Mission: Program Construct, Technology Development, and Mission Results

McLean, Christopher H.

doi:10.2514/6.2020-3810

Cited by 11 publications

(6 citation statements)

References 18 publications

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“…The thrust level of the propulsion system has been fixed at the value of 6 N, obtained by mission analysis, therefore it is decided to design the thruster based on the Aerojet Rocketdyne thruster GR-1. A set of these thrusters adopting AF-M315E has already been used for the GPIM mission for NASA [21]: each of these thrusters has the capability of generating a thrust of 1 N nominally, but this value can increase based on the higher the feed pressure is, as can be noted from Table 7.…”

Section: Baseline Thruster Configurationmentioning

confidence: 99%

“…Flame temperature [K] 2,401 [14], 2,373 [35] 2,166 [14] 2,095 [36] 1,903 [19] Freezing temperature [K] <-30 [14], <-37 [35] <-22 [14] 0 [40] -7 [40] Dynamic viscosity @25°C [mPa•s = cP] 11.9 [35] 25 [41], 27 [42] 3.7 [36][38] 3 [39] Vapour pressure [mbar] -14 [10] <21 [38] 136 [39] Acute toxicity LD50 oral, dermal [mg/kg] 300-2,000, >2,000 [14] Moderate [10] 1270, - [40] 750-800, - [40] Heritage RAPIS-1 [14] GPIM [37] -PRISMA [8] * Conditions for specific impulse estimation: a) Pc=0.7 MPa, Ae/At = 50, b) Pc = 2 MPa, Ae/At = 50 common. To preliminary design the catalyst bed pellets in dimensions, a model from Bey and Eigenberger [25], revised in [26], has been adopted.…”

Section: Catalyst Bedmentioning

confidence: 99%

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Enabling Interplanetary Exploration for CubeSats with a Fully Chemical Propulsion System

Giordano¹

2023

JBIS

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Interplanetary CubeSat missions are currently becoming more popular, with a significant number of recently planned missions. The context of this paper is a Mars mission, starting from a parking orbit around Earth: the adoption of a chemical propulsion system for the Earth-Mars transfer phase is investigated, considering the recent technological developments for CubeSats. A trade-off of propulsion system type and propellant results in the choice of a mono-propellant system adopting the HAN-based propellant AF-M315E (ASCENT). The main challenge for the propulsion system is to fit inside a CubeSat standardised volume, which can range up to 24 U, for which the implementation of a suitable COTS micro-pump is considered. Finally, the complete architecture and design of the propulsion system is presented. This work demonstrates the feasibility of adopting full chemical propulsion for an interplanetary CubeSat mission, with consequent advantages in terms of transfer time and required power, at the cost of relatively small mass and volume left for the other subsystems. Even better results can be expected for interplanetary missions requiring slightly lower ΔV budgets, such as Near Earth Objects exploration or asteroid fly-by missions. Keywords: CubeSat, Chemical Propulsion, Green Mono-propellant, Interplanetary Mission, Mars Exploration

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Section: Baseline Thruster Configurationmentioning

confidence: 99%

Section: Catalyst Bedmentioning

confidence: 99%

Enabling Interplanetary Exploration for CubeSats with a Fully Chemical Propulsion System

Giordano¹

2023

JBIS

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“…17−19 In 2010, the hydroxylammonium nitrate (HAN)-based EIL named AF-M315E was successfully synthesized 20 and validated in the flight mission in 2019. 21 After that, other organizations, including Japan Aerospace Exploration Agency and Swedish Defense Research Agency, also began to design similar propellants. 22 Although the HAN-Based EILs have exhibited excellent catalytic ignition capability, the compatibility with electrospray remains uncertain.…”

Section: Introductionmentioning

confidence: 99%

“…To improve the flexibility of satellite missions, the concept of dual-mode propulsion using energetic fuels was proposed. , This new propulsion solution utilizes the shared propellant and combines the advantages of both chemical and electrospray modes. , However, one of the major challenges in practical applications is the identification of dual-mode propellants with a high enthalpy of combustion and ionization capacity. In this regard, the energetic ILs (EILs) might be the most potential candidates. − In 2010, the hydroxylammonium nitrate (HAN)-based EIL named AF-M315E was successfully synthesized and validated in the flight mission in 2019 . After that, other organizations, including Japan Aerospace Exploration Agency and Swedish Defense Research Agency, also began to design similar propellants .…”

Section: Introductionmentioning

confidence: 99%

Multiplexed Electrospray Emission of Green Energetic Ionic Liquids from Wedge-Shaped Porous Emitters

Su,

Yao,

Zhuo

et al. 2023

Energy Fuels

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“…They used the HAN propellant AF-M315E. The technology demonstrator showed high performance and reliability in the earth’s orbit [ 8 ].…”

Section: Introductionmentioning

confidence: 99%

Preparation and Performance Evaluation of Platinum Barium Hexaaluminate Catalyst for Green Propellant Hydroxylamine Nitrate Thrusters

Kang

Kwon

2021

Materials

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Spacecraft have monopropellant thruster systems for attitude control in the vacuum of space. Hydroxylamine nitrate is a green propellant that has high performance and low toxicity. Owing to the high adiabatic decomposition temperature of the hydroxylamine nitrate propellant, it is necessary to develop a catalyst with high thermal stability. We used a platinum barium hexaaluminate catalyst for green propellant hydroxylamine nitrate thrusters. Barium hexaaluminate support was prepared by a wet impregnation method and heat treatment. Platinum, the active material, was coated on catalyst supports. The Brunauer–Emmett–Teller specific surface was also investigated. X-ray diffraction and scanning electron microscope imagery were used to confirm the formation of barium hexaaluminate. A hydroxylamine nitrate propellant blended with methanol was used for performance evaluation via firing tests of the thruster. The catalytic decomposition performance of each test was evaluated by calculating the characteristic velocity efficiency using the pressure of the chamber at the end of the catalyst bed and the mass flow rate of the propellant. As the catalyst bed was preheated to 350 °C, the characteristic velocity efficiency was 71.9%. Test results revealed that the platinum barium hexaaluminate catalyst is feasible for a hydroxylamine nitrate thruster.

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Green Propellant Infusion Mission: Program Construct, Technology Development, and Mission Results

Cited by 11 publications

References 18 publications

Enabling Interplanetary Exploration for CubeSats with a Fully Chemical Propulsion System

Enabling Interplanetary Exploration for CubeSats with a Fully Chemical Propulsion System

Multiplexed Electrospray Emission of Green Energetic Ionic Liquids from Wedge-Shaped Porous Emitters

Preparation and Performance Evaluation of Platinum Barium Hexaaluminate Catalyst for Green Propellant Hydroxylamine Nitrate Thrusters

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