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Research & Reviews : Journal of Space Science & Technology Review Article

Hybrid Rocket Propellant Grains: A Review

  1. Nishad Bhavsar Department of Aerospace Engineering, MIT School of Engineering & Sciences, MIT Art, Design and Technology University, Pune
  2. Paarth Saxena Department of Aerospace Engineering, MIT School of Engineering & Sciences, MIT Art, Design and Technology University, Pune
  3. Prasad Sawant Department of Aerospace Engineering, MIT School of Engineering & Sciences, MIT Art, Design and Technology University, Pune
  4. Maitreyee Birajdar Department of Aerospace Engineering, MIT School of Engineering & Sciences, MIT Art, Design and Technology University, Pune
  5. Pandi Siddharth Department of Aerospace Engineering, MIT School of Engineering & Sciences, MIT Art, Design and Technology University, Pune

Abstract

The go-to-rocket propulsion system is either solid rocket motor or liquid rocket engine, but both have their own drawbacks like solid rocket motors cannot be throttled or stopped and started again or the construction of liquid propulsion systems is quite complex, with difficulty in storage and major safety issues. A hybrid rocket propulsion system uses either fuel or oxidizer in solid form and the other in liquid and has a lot of advantages over the conventional propulsion systems. As hybrid rockets usually provide a few advantages over solid and liquid propulsion rockets, like hybrid rocket system can be turned off and on again, it can also be throttled easily by controlling the flow of the liquid component of the propellant. This paper presents a thorough review of hybrid rocket propellant grains, encompassing their historical development, fundamental principles, design considerations, performance characteristics, and recent advancements.

Keywords

References (12)

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