Conceptual design and contour optimization of altitude compensation nozzles for ssto vehicles

Pradeep, R and Thianesh, UK and Prabhu, R and Kumar, K and Rajaram Perumal, M and Sumanth Eswar, KS and Rajesh, M and Mariappan, A and Sukumaran, A and Sanal Kumar, VR (2020) Conceptual design and contour optimization of altitude compensation nozzles for ssto vehicles. In: AIAA Propulsion and Energy 2020 Forum, 24-28 August 2020, Virtual, Online, pp. 1-8.

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Abstract

An altitude compensating nozzle is a class of rocket engine nozzles that are designed to operate with the highest momentum thrust across a wide range of altitudes. Herein, we are proposing a single nozzle with different adjustable area ratios at different altitude. This could be achieved by shelling thin-wall nozzles one upon another from a low nozzle area ratio to that of the high area ratio. During flight the low area ratio nozzles will be dropped as and when the altitude compensation effect is diminishing. In another attempt the altitude compensation nozzle is designed with inflated walls, which could alter the area ratio during the flight at deflated conditions using surface profile actuators. As a first step, an algorithm has been developed for generating a shock-less altitude compensation convergent-divergent (CD) nozzle with moving wall using the method of characteristics. Simultaneously, numerical simulations have been carried out on an aero spike nozzle with the help of a validated three-dimensional SST k�� turbulence model for the reconfirmation of the code capability for featuring the flow field during altitude compensation. Note that the pressure on the aerospike nozzle surface has the ability to adjust to changes in ambient pressure, leading to the well-known altitude compensation effect for aerospace vehicles. We have conjectured that the judicious optimization of a moving wall nozzle with a validated flow solver using the proposed algorithm for designing a shock-less CD nozzle with an adjustable area ratio could facilitate better altitude compensation throughout the flight with a commendable improvement in payload capability for single-stage-to-orbit reusable launch vehicles. © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type:	Conference Paper
Publication:	AIAA Propulsion and Energy 2020 Forum
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	cited By 0; Conference of AIAA Propulsion and Energy 2020 Forum ; Conference Date: 24 August 2020 Through 28 August 2020; Conference Code:244349
Keywords:	Aerospace vehicles; Conceptual design; Propulsion; Rocket nozzles; Rockets; Turbulence models; Vehicles, Aerospike nozzle; Altitude compensation; Ambient pressures; Contour optimization; Method of characteristics; Payload capabilities; Reusable launch vehicles; Single stage to orbits, Nozzle design
Department/Centre:	Others
Date Deposited:	01 Dec 2020 10:15
Last Modified:	01 Dec 2020 10:15
URI:	http://eprints.iisc.ac.in/id/eprint/66787

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