Development of Reduced Toxicity Hypergolic Propellants

Mahakali, Rohit; Kuipers, Fred M.; Yan, Allen H.; Anderson, William E.; Pourpoint, Timothée L.

doi:10.2514/6.2011-5631

Cited by 29 publications

(9 citation statements)

References 1 publication

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“…7 Initial test series confirmed the ability of the feed system, injector, and combustor configuration to consistently produce violent high pressure pulsed behaviors. Consistent instrumentation challenges continued to promote investigation of various measurement techniques to measuring transient combustor conditions.…”

Section: Introductionmentioning

confidence: 52%

“…The current hypergolic fuel is designed with 8% sodium borohydride (NaBH 4 ) by mass dissolved in the industrial solvent, Triglyme, or triethylene glycol dimethyl ether. 7 The differences between the MAT fuel and the NaBH 4 fuel manifest themselves in physical and chemical properties; the result of which led to sub-optimal performance when using hardware designed for the former. The presented research similarly uses 96% hydrogen peroxide as the oxidizer (ox).…”

Section: Test Apparatus and Facilitymentioning

confidence: 99%

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Chamber Volume Effects on Hypergolic Pulse Detonation Rocket Engine

Kan¹,

Heister²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Experimental results from a valveless pulsed detonation rocket engine concept with hypergolic propellants are detailed. The thruster employed a pintle injector and a simple combustor geometry with an open end. Flow field characterization followed from test measurements from high-speed pressure transducers and ionization gauges placed in the chamber. Propellant manifold feed pressures of 100-200 psi resulted in peak pulsed combustion pressure reaching 10,000 psi. Baseline pulsed combustion frequency ranged from 300-500 Hz. Experiments conducted with a doubled chamber length showed little impact on peak pulsed pressures but indicated a 15% decrease in pulsation frequency. The data suggests that the pulsation frequency is dependent on dynamic orifice response, chamber dimensions (diameter and length), and the chemical ignition delay of the hypergolic propellant combination. Experiments showed repeatable pulsed behavior with the need for robust injection techniques and instrumentation.

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Section: Introductionmentioning

confidence: 52%

Section: Test Apparatus and Facilitymentioning

confidence: 99%

Chamber Volume Effects on Hypergolic Pulse Detonation Rocket Engine

Kan¹,

Heister²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…It is expected that both propellants were full flowing by valve command +300 ms; however, no evidence of combustion occurs. From previous experiments it is known that the hypergolic propellant combination exhibits ignition on the order of 6 ms. 10 At around valve trigger + 675 ms the fluid stream turns from a gray and transparent fluid to a thick milky white fluid, and at valve trigger + 716 ms the fluid stream violently expands as if a reaction within the fluid stream has occurred. Fluid is ejected radially outward from the downward stream, but no visual confirmation of combustion is available.…”

Section: Hot-fire Test 1 Resultsmentioning

confidence: 99%

“…The hypergolic propellants to be used include rocket grade hydrogen peroxide (RGHP) with an experimental fuel, fuel-a, consisting of 11.5% Sodium Borohydride by mass (NaBH 4 ) in a solvent, Triglyme, or triethylene glycol dimethyl ether. 10 Alternative candidate hypergols includes a nontoxic hypergolic miscible fuel (NHMF), Block 0, composed of 78% Methanol and 22% Manganese Acetate Tetrahydrate (Mn 0.2 C 6.4 H 25.4 O 8.7 ) by weight, and RGHP. 11 The current effort differs in that the use of hypergolic fuels for detonation aims to eliminate the need for added hardware to achieve DDT.…”

mentioning

confidence: 99%

Valveless Detonation Concepts for Space Exploration

Kan¹,

Heister²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A pulsed detonation rocket engine concept was explored through the use of hypergolic propellants in a fuel-centered pintle injector combustor. In tandem a 1D lumped parameter transient hydraulic model was developed and tuned based on experimental data. The combustor design yielded a simple open ended chamber with the injection element and pressure instrumentation located at the head end. High-frequency pressure measurements show that large pressure oscillations in excess of 2000 psia at frequencies between 400-600 hz were present during operation. High-speed video confirms high-frequency pulsed behavior and large amounts of after burning. We note that the exact phenomena that occurred within the chamber has not been fully characterized. Damaged hardware and instrumentation failure limited the amount of data gathered, but original test objectives of producing large over-pressures in an open chamber were met. System hydraulic response to chamber phenomena, chamber pressure oscillations, and experimental hardware are discussed. NomenclatureD Diameter, in K t pressure head loss factors L Inertance, lbf −s 2 lbm−in 2 Q Volumetric flow rate, in 3 s R Resistance, lbf −s 2 lbm−in 5 m Mass flow rate, lbm s ρ Density, lbm in 3 f Fanning friction factor g c gravitational conversion factor, lbm−in lbf −s 2 l length, in p Pressure, psi t time, sec

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“…As a candidate for a less toxic hypergolic bipropellant, the combination of highly concentrated hydrogen peroxide and some types of fuel with a catalytic agent or reducing agent dissolved has been studied by many researchers [2][3][4][5][6][7][8][9][10][11]. This type of hypergolic bipropellant was originally developed in the Naval Air Warfare Center Weapons Division (NAWCWD) [2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Quantitative Clarification of Stable Ignition Region for HKP110 Green Hypergolic Bipropellant

Hatai

Nagata

2022

Aerospace

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As a candidate for a green hypergolic bipropellant, the combination of highly concentrated hydrogen peroxide and fuel with dissolved sodium borohydride has been widely studied. In this study, a drop test using such a green hypergolic bipropellant was conducted to investigate the stable ignition region in terms of the mixture ratio. As a result, stagnation phenomena of flame growth were observed in high mixture ratio conditions. In addition, impinging-jet tests using a windowed chamber were conducted with the green hypergolic bipropellant to observe the ignition phenomena inside the combustion chamber. As a result, unstable ignition phenomena were observed in oxidizer-lead injection cases. Besides the unstable ignition, hard starts occurred several times during the test series. Data analysis demonstrated that controlling the transient mixture ratio in the early phase of injection is essential for preventing unstable ignition and hard starts. The quantitative threshold of mixture ratio for stable ignition was clarified based on the test results.

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Development of Reduced Toxicity Hypergolic Propellants

Cited by 29 publications

References 1 publication

Chamber Volume Effects on Hypergolic Pulse Detonation Rocket Engine

Chamber Volume Effects on Hypergolic Pulse Detonation Rocket Engine

Valveless Detonation Concepts for Space Exploration

Quantitative Clarification of Stable Ignition Region for HKP110 Green Hypergolic Bipropellant

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