Hybrid Propulsion In-Situ Resource Utilization Test Facility Results

Karp, Ashley C.; Nakazono, Barry; Vaughan, David; Warner, William N.

doi:10.2514/6.2015-4200

Cited by 2 publications

(4 citation statements)

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“…The test numbering starts at #10 for consistency with the previous campaign. 4 BP refers to Black Paraffin procured from the Candlewic company and SP1X to SPG's paraffin based formulation. The maximum burn time was determined to reach the longest steady state duration without fully consuming the fuel to collect regression rate measurements.…”

Section: Hotfire Results and Discussionmentioning

confidence: 99%

“…Cold flow measurements were compared to mass loss in the cylinder (ref. 4 ). Using a velocity coefficient C v of 1, the measured and calculated values were within 5-10% of each other.…”

Section: B Oxidizer Mass Fluxmentioning

confidence: 99%

“…Candlewic paraffin material properties such as volatiles release, phase transition and coefficient of thermal expansion were obtained and described in ref. 4 The fuel grains were centrifugally cast in a Flame-Retardant Garolite (G10/FR4) thermal insulator using a dedicated casting system at JPL. It is possible to test alternative fuel types since the only constraints are length and outer diameter.…”

Section: Introductionmentioning

confidence: 99%

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Hybrid Propulsion In-Situ Resource Utilization Test Facility Results for Performance Characterization

Mechentel

Karp

Nakazono

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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Hybrid propulsion presents a promising alternative to conventional systems for in-space propulsion applications using In-Situ Propellant Production (ISPP). A hybrid propulsion test facility has been built at the NASA Jet Propulsion Laboratory (JPL) with the capability to evaluate ISPP oxidizers (gaseous mixtures of O2 and CO2) and modify fuel type and chamber geometry. This work is the result of a continuing effort at JPL to characterize the burn characteristics and performance of different propellant combinations and motor configurations in order to refine and support preliminary designs. Twelve tests using gaseous oxygen and two paraffin based fuels (Black Paraffin and SP1X) from the 2015 campaign are presented. Different reduction techniques are compared in an effort to determine the uncertainty associated with deriving a regression rate law and evaluating c* efficiency with the collected data.

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Section: Hotfire Results and Discussionmentioning

confidence: 99%

“…Cold flow measurements were compared to mass loss in the cylinder (ref. 4 ). Using a velocity coefficient C v of 1, the measured and calculated values were within 5-10% of each other.…”

Section: B Oxidizer Mass Fluxmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Hybrid Propulsion In-Situ Resource Utilization Test Facility Results for Performance Characterization

Mechentel

Karp

Nakazono

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…In recent years there has been increasing interest in using hybrid rocket motors for interplanetary missions [1,2]. Preliminary design studies have shown hybrid motors to be viable alternatives to conventional propulsion systems for some exploration missions [3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%