Propulsion subsystem component development program for the MECB RSS satellite

Hinckel, J. N.; Trava-Airoldi, V.J.; Corat, Evaldo José; Bressan, Claudio

doi:10.2514/6.1991-1836

Cited by 5 publications

(3 citation statements)

References 1 publication

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“…The engine was designed for operation in the feed pressure range of 2.2MPa to 0.55 MPa with nominal thrust of 35N at 2.2MPa feed pressure. The corresponding catalytic bed load is 2.75 to 0.9 g/cm 2…”

Section: The Test Enginementioning

confidence: 99%

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Low Cost Catalysts for Hydrazine Monopropellant Thrusters

Neto¹,

Zacharias²,

Palandi³

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: The Test Enginementioning

confidence: 99%

“…Schmitz 1 describes the qualification test sequence for a long life, iridium catalyst, 2 newton monopropellant thruster for a satellite reaction control system. Hinckel 2,3 describes the development of hydrazine monopropellant thrusters carried out at INPE. Rath 4 and Pitt 5 describe the development of a 400 N monopropellant engine.…”

Section: Introductionmentioning

confidence: 99%

Low Cost Catalysts for Hydrazine Monopropellant Thrusters

Neto¹,

Zacharias²,

Palandi³

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…In the operation of the hydrazine propulsion system, generally pressure fluctuation was observed. In cold start, a large pressure spike might be generated by excess hydrazine injection and accumulation of hydrazine in the induction period of the decomposition reactions 16 . Pressure oscillation might also be initiated by valve actuating disturbance and reaction instability.…”

Section: Introductionmentioning

confidence: 99%

Propellant Grade Hydrazine in Mono/Bi-propellant Thrusters: Preparation and Performance Evaluation

Krishnamachary¹,

Mohan²,

Kulkarni³

et al. 2015

DSJ

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Propellant grade hydrazine was prepared with 64 per cent yield and 95.5 per cent purity. Purity of the propellant grade hydrazine was determined using wet chemical, gas chromatographic (GC) and eudiometric methods. It was observed that the compositions containing blends of hydrazine-methyl alcohol-ammonium nitrate and hydrazine-methyl alcohol-ammonium perchlorate were not found to be frozen even after cooling to -65 °C for 30 minutes. Mono and bi-propellant thrusters were designed and developed to demonstrate the performance of prepared propellant grade hydrazine as a promising rocket fuel. Five static tests with 22 N thruster and one static test with 1 N thruster were performed successfully in mono-propellant mode. The hurdles of chamber pressure oscillations were overcome by compact packing of the catalyst. The desired decomposition and chamber pressure were achieved. One static test was performed successfully with 60 N bi-propellant thruster. The desired chamber pressure and thrust were achieved. The combustion was smooth and C* achieved was higher than that of UH-25, N 2 O 4 combination. The performance of prepared propellant grade hydrazine shows it as a promising rocket fuels.

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