Aerospike Nozzle
Numerical Analysis of optimized Aerospike nozzle based on combustion chamber temperatures
Sanalkumar V.R.
Swathi Marudhamuthu; Gopinath Jayaraj; Hemasai Nagaraj; Meghana Raj; Anoovendhan Subramanian;
Acknowledged by : Mohanraj Murugesan
Abstract
The research about rocket propulsion has been raised to the level of a higher thrust at high effeciency with a number of methods. Aerospike nozzle is a type of nozzle in which the external surface of the bell nozzle has been inverted inwards to form a spike. Unlike a bell nozzle, aerospike nozzle is an external flow aerodynamic concept as , at the exhaust the flow moves over the external surface of the spike, introducing itself into the atmosphere well before than that of the bell or linear nozzle types. Since it reaches a lower pressure , the mach number increases and thus producing a higher thrust through the exhaust. Moreover its streamlined flow dissimilar to the bell nozzle’s diverged exhaust, would increase the rocket thrust considerably. The spike could also be formed by inverting the upper surface of the airfoil and thus we can bring in the concepts of a better pressure distribution at the exhaust which is the challenge in rocket propulsion. Likewise, when the spike nozzle is made movable horizontally like in a joystick just through one direction, thrust vectoring can be enhanced as well. Thus the intoduction of aerospike nozzles in rocket propulsion and space shuttles could enhance the thrust, pressure distribution, effeciency and also thrust vectoring properties.
O American Institute of Aeronautics and Astronautics 2 moveable spike for thrust vectoring and throttling could provide a more efficient alternative to traditional bell nozzles. Aerospike nozzles with optimal thrust vector control will provide added safety and improved capability to the aerospike rocket test projects, as well as economic benefit through the reuse of nozzles. Thrust vectoring and throttling capabilities
Sanalkumar V.R.
Swathi Marudhamuthu; Gopinath Jayaraj; Hemasai Nagaraj; Meghana Raj; Anoovendhan Subramanian;
Acknowledged by : Mohanraj Murugesan
Abstract
The research about rocket propulsion has been raised to the level of a higher thrust at high effeciency with a number of methods. Aerospike nozzle is a type of nozzle in which the external surface of the bell nozzle has been inverted inwards to form a spike. Unlike a bell nozzle, aerospike nozzle is an external flow aerodynamic concept as , at the exhaust the flow moves over the external surface of the spike, introducing itself into the atmosphere well before than that of the bell or linear nozzle types. Since it reaches a lower pressure , the mach number increases and thus producing a higher thrust through the exhaust. Moreover its streamlined flow dissimilar to the bell nozzle’s diverged exhaust, would increase the rocket thrust considerably. The spike could also be formed by inverting the upper surface of the airfoil and thus we can bring in the concepts of a better pressure distribution at the exhaust which is the challenge in rocket propulsion. Likewise, when the spike nozzle is made movable horizontally like in a joystick just through one direction, thrust vectoring can be enhanced as well. Thus the intoduction of aerospike nozzles in rocket propulsion and space shuttles could enhance the thrust, pressure distribution, effeciency and also thrust vectoring properties.
O American Institute of Aeronautics and Astronautics 2 moveable spike for thrust vectoring and throttling could provide a more efficient alternative to traditional bell nozzles. Aerospike nozzles with optimal thrust vector control will provide added safety and improved capability to the aerospike rocket test projects, as well as economic benefit through the reuse of nozzles. Thrust vectoring and throttling capabilities
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