Rocket nozzles: 75 years of research and development

Khare, Shivang; Saha, Ujjwal K.

doi:10.1007/s12046-021-01584-6

Cited by 16 publications

(5 citation statements)

References 97 publications

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“…This model describes the iterations between the oxidiser and the fuel to develop the theoretical model of the fuel combustion process. The assumptions include complete and instantaneous combustion processes, incompressible single-phase fluid flow, and thermal equilibrium between the liquid and gas phases in saturated form [32][33][34]. The thermodynamic properties required for the model are extracted from the National Institute for Standards and Technology (NIST) [15].…”

Section: Propulsion Modellingmentioning

confidence: 99%

On the Multidisciplinary Design of a Hybrid Rocket Launcher with a Composite Overwrapped Pressure Vessel

Souza,

Gonçalves,

Afonso

et al. 2024

J. Compos. Sci.

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A multidisciplinary design optimisation (MDO) study of a hybrid rocket launcher is presented, with a focus on quantifying the impact of using composite overwrapped pressure vessels (COPVs) as the oxidiser tank. The rocket hybrid propulsion system (RHPS) consists of a combination of solid fuel (paraffin) and liquid oxidiser (NOx). The oxidiser is conventionally stored in metallic vessels. Alternative design concepts involving composite-based pressure vessels are explored that could lead to significant improvements in the overall performance of the rocket. This design choice may potentially affect parameters such as total weight, thrust curve, and maximum altitude achieved. With this eventual impact in mind, structural considerations such as wall thickness for the COPV are integrated into an in-house MDO framework to conceptually optimise a hybrid rocket launcher.

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Section: Propulsion Modellingmentioning

confidence: 99%

On the Multidisciplinary Design of a Hybrid Rocket Launcher with a Composite Overwrapped Pressure Vessel

Souza,

Gonçalves,

Afonso

et al. 2024

J. Compos. Sci.

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“…In addition, the overexpanded state also causes unstable flow separation on the nozzle inner wall, generating lateral loads and reducing nozzle stability. In order to improve the thrust performance of rocket engine nozzles and compensate for thrust losses caused by back pressure changes during operation, various altitude compensation nozzle concepts have been proposed and gained widespread attention from the scientific and engineering community [4]. Typical altitude compensation nozzles include dual-bell nozzles [5], expansion-deflection nozzle [6], extending nozzles [7], aerospike nozzles [8], vented nozzles [9], and slotted nozzles [10].…”

Section: Introductionmentioning

confidence: 99%

Numerical study on altitude-compensating mechanism of a permeable nozzle

Xue,

Bu,

Wang

et al. 2024

J. Phys.: Conf. Ser.

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A conceptual adaptive altitude compensation nozzle with a permeable wall (permeable nozzle for short) is proposed in the present study. The typical operating states of the nozzle are demonstrated using numerical methods and the underlying mechanism of its altitude compensation is interpreted. The numerical results show that, at low nozzle pressure ratios, the external atmosphere enters the nozzle through its permeable wall section, which inhibits the backflow at the nozzle wall, weakens the strength of the separated oblique shock, thus improves the low-altitude thrust performance of the nozzle. However, at high nozzle pressure ratios, the exhaust gas leaves the nozzle through its permeable wall, which weakens the expansion of the exhaust gas and reduces the thrust performance. The permeable nozzle is considered to possess altitude compensation ability when the enhancement in its low-altitude thrust performance surpasses the deterioration in high-altitude thrust performance. The thrust composition analysis of the permeable nozzle reveals that its altitude compensation ability derives from the internal pressure rise due to the atmospheric air penetration into the nozzle at low nozzle pressure ratios.

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“…The dual-bell nozzle, as mentioned in the name, consists of two distinct contours between the throat and the exit [10]. Considered an altitude-adaptive nozzle concept, it combines a small nozzle area ratio at low altitude with a large one at high altitude.…”

Section: Introductionmentioning

confidence: 99%

A shape design optimization methodology based on the method of characteristics for rocket nozzles

2023

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Even though shape optimization is a powerful tool for designing aerospace vehicles, it can be time-consuming when high-fidelity models are employed. Thus, lower-fidelity simulations covering a wider design space can be a solution for shape optimization in the early design phases. With this in mind, the present work aims to develop a low-fidelity and fast method to conduct nozzle shape optimization. This method consists in using the free-form deformation (FFD) parameterization technique to control the nozzle shape by means of an optimization algorithm to maximize the coefficient of thrust determined by a two-dimensional method of characteristics (MoC). To verify the reliability of the proposed method, a similar optimization process is carried out, recurring to high-fidelity simulations, namely using an Euler solver, in the open-source framework $$\text {SU}^2$$ SU 2 . This latter optimization process is established as a surrogate-based optimization (SBO) not only to mitigate the $$\text {SU}^2$$ SU 2 framework limitations in performing shape optimization on nozzles, but also as a way to reduce the computational power. A good agreement between the results from both methods is achieved, displaying solely a small offset concerning the optimal contour width and the coefficient of thrust. Hence, this proves the usefulness of the developed shape optimization strategy based on the MoC for the preliminary design of nozzles.

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Rocket nozzles: 75 years of research and development

Cited by 16 publications

References 97 publications

On the Multidisciplinary Design of a Hybrid Rocket Launcher with a Composite Overwrapped Pressure Vessel

On the Multidisciplinary Design of a Hybrid Rocket Launcher with a Composite Overwrapped Pressure Vessel

Numerical study on altitude-compensating mechanism of a permeable nozzle

A shape design optimization methodology based on the method of characteristics for rocket nozzles

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