Mars Ascent Vehicle Hybrid Propulsion Effort

Story, George; Karp, Ashley C.; Nakazono, Barry; Zilliac, Greg; Evans, Brian; Whittinghill, George

doi:10.2514/6.2020-3727

Cited by 10 publications

(12 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…But unfortunately, this technology lacked maturity to be considered for the MSR campaign. The launch window envisioned by NASA at the time of the trade-off was as early as 2026 [18]. As stated in [18], NASA strongly recommended a TRL of six for the mission preliminary design, and the studies from the hybrid propulsion team estimated their design to TRL 5+ (depending on the parts considered).…”

Section: Hybrid Propulsionmentioning

confidence: 99%

“…The launch window envisioned by NASA at the time of the trade-off was as early as 2026 [18]. As stated in [18], NASA strongly recommended a TRL of six for the mission preliminary design, and the studies from the hybrid propulsion team estimated their design to TRL 5+ (depending on the parts considered). Despite the promising performances and resilience that a Hybrid MAV would offer, the solid configuration was chosen as it was the most mature technology.…”

Section: Hybrid Propulsionmentioning

confidence: 99%

“…If their technology reaches high TRL levels and if it proves to be successful, it could open the way for a multitude of rocket applications. The observations made in [18] will serve as a guide for tackling difficult aspects of the mission.…”

Section: Hybrid Propulsionmentioning

confidence: 99%

“…The "Initial" configurations both start with a 400 kg GLOM and an unoptimized propellant mass, while the "Final" configurations have a reduced GLOM achieved through lower propellant mass. The results of all four configurations are gathered in Table 4: The efficiency of the TSTO configuration enables us to drastically reduce the GLOM to less than 300 kg, which is the initial goal that was set by NASA at the beginning of the project [18]. As indicated in Table 4, both concepts can attain the desired orbit with initial ∆V values exceeding the required 4765 m/s.…”

Section: Stagingmentioning

confidence: 99%

See 3 more Smart Citations

Design of a Mars Ascent Vehicle Using HyImpulse’s Hybrid Propulsion

Renault,

Lappas

2023

Aerospace

View full text Add to dashboard Cite

The recent growth in maturity of paraffin-based hybrid propulsion systems reassesses the possibility to design an alternative Mars Ascent Vehicle (MAV) propelled by a European hybrid motor. As part of the Mars Sample Return (MSR) campaign, a Hybrid MAV would present potential advantages over the existent solid concept funded by NASA through offering increased performance, higher thermal resilience, and lower Gross Lift-Off Mass (GLOM). This study looks at the preliminary design of a two-stage European MAV equipped with HyImpulse’s hybrid engine called the Hyplox10. This Hybrid MAV utilizes the advantages inherent to this type of propulsion to propose an alternative MAV concept. After a careful analysis of previous MAV architectures from the literature, the vehicle is sized with all its components such as the propellant tanks and nozzle, and the configuration of the rocket is established. A detailed design of the primary structure is addressed. This is followed by a Finite Element Analysis (FEA), evaluating the structural integrity under the challenging conditions of Entry, Descent, and Landing (EDL) on Mars, considering both static and dynamic analyses. The outcome is a Hybrid MAV design that demonstrates feasibility and resilience in the harsh Martian environment, boasting a GLOM of less than 300 kg.

show abstract

Section: Hybrid Propulsionmentioning

confidence: 99%

Section: Hybrid Propulsionmentioning

confidence: 99%

Section: Hybrid Propulsionmentioning

confidence: 99%

Section: Stagingmentioning

confidence: 99%

See 2 more Smart Citations

Design of a Mars Ascent Vehicle Using HyImpulse’s Hybrid Propulsion

Renault,

Lappas

2023

Aerospace

View full text Add to dashboard Cite

show abstract

“…Since the maiden flight of SpaceShipOne, hybrid rockets have become the core technology of at least seven Earth-launch vehicle developers: Rocket Crafters/Vaya Space (since 2010, USA [5,6]), Gilmour Space Technologies (since 2012, Australia [7,8]), TiSPACE (since 2016, Taiwan [9,10]), Nammo (Nucleus project since 2017 [8,11]), HyImpulse (since 2018, Germany [12,13]), Firehawk (since 2018, USA [5,14]), and SpaceForest (SIR project since 2018, Poland [15,16]); at least four new satellite thruster developers: T4i (since 2014, Italy [17]), Utah State University (since 2014, USA [18,19]), NASA (Kick Motor project since 2016, USA [20,21]), and Hokkaido University (Kick Motor project since 2017, Japan [22,23]); and at least one planetary ascent vehicle developer: NASA (MAV project since 2016, USA [24,25]). In recent years, the Hokkaido University kick motor has become the focus for the authors' work.…”

Section: Introduction 1state Of Hybrid Rocket Developmentmentioning

confidence: 99%

Hybrid Rockets as Post-Boost Stages and Kick Motors

2021

View full text Add to dashboard Cite

Hybrid rockets are attractive as post-boost stages and kick motors due to their inherent safety and low cost, but it is not clear from previous research which oxidizer is most suitable for maximizing ΔV within a fixed envelope size, or what impact O/F shift and nozzle erosion will have on ΔV. A standard hybrid rocket design is proposed and used to clarify the impact of component masses on ΔV within three 1 m3 envelopes of varying height-to-base ratios. Theoretical maximum ΔV are evaluated first, assuming constant O/F and no nozzle erosion. Of the four common liquid oxidizers: H2O2 85 wt%, N2O, N2O4, and LOX, H2O2 85 wt% is shown to result in the highest ΔV, and N2O is shown to result in the highest density ΔV, which is the ΔV normalized for motor density. When O/F shift is considered, the ΔV decreases by 9% for the N2O motor and 12% for the H2O2 85 wt% motor. When nozzle erosion is also considered, the ΔV decreases by another 7% for the H2O2 85 wt% motor and 4% for the N2O motor. Even with O/F shift and nozzle erosion, the H2O2 85 wt% motor can accelerate itself (916 kg) upwards of 4000 m/s, and the N2O motor (456 kg) 3550 m/s.

show abstract