Design, development and evolution of the Ariane 5 Attitude Control System (CSA)

Pitt, Richard; Rogall, Hartmut

doi:10.2514/6.1995-2808

Cited by 3 publications

(3 citation statements)

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“…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%

“…The catalysts tested were; an heterogenous aluminum oxide supported ruthenium catalyst and a homogeneous catalyst, tungsten carbide. Applications of the ruthenium in monopropellant control thruster ared described in the literature, Pitt 5 . Applications of aluminum oxide supported tungsten carbide and homogeneous tungsten carbide catalysts in monopropellant thrusters are reported by Chen 6 and Rodrigues 7 , respectively.…”

Section: Introductionmentioning

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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“…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%

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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“…Schmitz describes the qualification test sequence for a long life monopropellant thruster for a satellite reaction control system 20 . The development of hydrazine monopropellant thrusters carried out at INPE and 400 N monopropellant engine were reported [21][22][23] . However, all these static tests were done with 98.5 per cent pure propellant grade hydrazine.…”

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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