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

S. Krishnamachary; S. Krishna Mohan; S. G. Kulkarni; D. Jayaraman; M. Raghavendra Rao; L. Dev Singh; Sai Krishna Prasad

doi:10.14429/dsj.65.7986

S. Krishnamachary Defence Research and Development Laboratory, Hyderabad
S. Krishna Mohan Defence Research and Development Laboratory, Hyderabad
S. G. Kulkarni Defence Institute of Advanced Technology, Pune
D. Jayaraman Defence Research and Development Laboratory, Hyderabad
M. Raghavendra Rao Defence Research and Development Laboratory, Hyderabad
L. Dev Singh Defence Research and Development Laboratory, Hyderabad
Sai Krishna Prasad Defence Research and Development Laboratory, Hyderabad

DOI: https://doi.org/10.14429/dsj.65.7986

Keywords: Propellant grade hydrazine, static test, mono-propellant, bi-propellant

Abstract

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, N2O4 combination. The performance of prepared propellant grade hydrazine shows it as a promising rocket fuels.

Defence Science Journal, Vol. 65, No. 1, January 2015, pp.31-38, DOI:http://dx.doi.org/10.14429/dsj.65.7986

Author Biographies

S. Krishnamachary, Defence Research and Development Laboratory, Hyderabad

Mr S. Krishnamachary has completed his MSc Chemistry from Sri Krishna Devaraya University, Anantapur, Andhra Pradesh. Currently pursuing his PhD from DIAT, Pune. Presently he is working as a scientist at Propellant and Polymer Division of Directorate of Propulsion, Defence Research and Development, Hyderabad. His area of expertise is development of liquid propellants for rockets, liquid fuels for ramjets, and thermal protection systems for rocket applications. His contributions includes development of liquid high density hydrocarbon fuels, Mixed oxides of nitrogen (MON-10) for low-freezing applications and silicone-based low density ablative material for external thermal protection.

S. Krishna Mohan, Defence Research and Development Laboratory, Hyderabad

Dr S. Krishna Mohan is presently working as a scientist at Propellant and Polymer Division of Directorate of Propulsion, Defence Research and Development, Hyderabad. He obtained his PhD in Organic Chemistry from Indian institute of Chemical Technology, Hyderabad. He has received prestigious fellowships from Japan Science and Technology, Japan Society of Promotion of Science and Swiss Postdoctoral Research. He has filed 02 world patents, 06 Indian patents, published over 40 peer reviewed international journal papers and 01 book. His current research interests include development of polymer matrix composites for air frames, ablative materials for thermal protection systems and liquid propellants for rocket and ramjet applications.

S. G. Kulkarni, Defence Institute of Advanced Technology, Pune

Dr S.G Kulkarni is working as Visiting Professor at Defence Institute of Advanced Technology, Pune (India). He has vast experience of teaching at post-graduate level and guided several MTech and PhD theses. He has published a number of research papers in national and international journals of repute and attended seminars / symposia / conferences and presented papers. His areas of interest include high energy materials, detonics, NBC warfares, energetic polymers and nanocomposites. He has delivered a number of invited lectures at various universities, research establishments and ordnance factories in the country.

D. Jayaraman, Defence Research and Development Laboratory, Hyderabad

Dr D. Jayaraman Completed his MSc from School of Chemical Sciences, Pondicherry University. He obtained his PhD from Indian Institute of Technology, Bombay, Mumbai. He joined DRDL (DRDO), Hyderabad at Propellants and Polymer Division under Directorate of Propulsion in 2005. Presently he is working as Scientist-‘D’. His areas of research include synthesis, characterisation and performance evaluation of high density hydrocarbon fuels for SCRAMJET and LFRJ application and materials for thermal protection of rocket motor.

M. Raghavendra Rao, Defence Research and Development Laboratory, Hyderabad

Mr M. Raghavendra Rao is currently working as scientist ‘F’ and is the Head of Liquid Propulsion Division at Defence Research and Development Laboratory, Hyderabad. He has received his BE in Mechanical Engineering from National Institute of Technology, Bhopal, and ME (Aerospace Engineering) from Anna University, Chennai. He is the designer and system manager for ‘Reaction Control Systems’ (RCS) of all the AGNI missile variants. He has more than 20 years of experience in design and developments of various sub-systems for RCS and Velocity Trimming Package (VTP).

L. Dev Singh, Defence Research and Development Laboratory, Hyderabad

Mr L. Dev Singh is presently working as scientist ‘D’ in Liquid Propulsion Division of Defence Research and Development Laboratory, Hyderabad. He has received his BE in Mechanical Engineering and ME in Production Engineering from Osmania University, Hyderabad. He has 10 years of experience in production management in BDL and is presently the In-charge of the liquid rocket engines’ static testing facility at DRDL.

Sai Krishna Prasad, Defence Research and Development Laboratory, Hyderabad

Mr G. Sai Krishna Prasad is currently working as scientist ‘C’ in Liquid Propulsion Division of Defence Research and Development Laboratory, Hyderabad. He has received his BTECH and MTECH degrees in Aerospace Engineering from Indian Institute of Technology Madras. His research areas are design of liquid propulsion systems & development of pulse detonation engine technology.