Side-Force Amplification on an Aerodynamically Thrust-Vectored Aerospike Nozzle

Eilers, Shannon D.; Wilson, Matthew D.; Whitmore, Stephen A.; Peterson, Zachary W.

doi:10.2514/1.b34381

Cited by 36 publications

(3 citation statements)

References 49 publications

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“…He concluded that, for optimal performance of SITVC, a downstream injection position and higher mass flow rates were beneficial. On the other hand, in the MUPHyN project, Eilers et al [12,13] conducted cold-flow experiments with three different secondary injection positions, where they evaluated the performance of side-force generation in terms of the side-specific impulse. Here too, they confirmed the performance advantage for a downstream injection position.…”

Section: Introductionmentioning

confidence: 99%

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Sieder-Katzmann,

Propst,

Stark

et al. 2024

Aerospace

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A cold-gas test campaign has been conducted at the DLR’s P6.2 test bench in Lampoldshausen, with the objective of investigating the linear aerospike nozzle flow in interaction with secondary injection thrust vector control (SITVC). In this campaign, the influence of nozzle truncation, injection position and injection pressure on the nozzle surface and base pressure is analysed using pressure probes and Schlieren flow-visualisation techniques. The effects of injection position and truncation on the nozzle surface pressure development are comparable for all geometric variations, resulting in a locally increased static pressure upstream and a locally decreased static pressure downstream of the injection. The magnitude and dimension of these high- and low-pressure regions are correlated with the injection pressure. However, the influence of injection position and truncation on the base pressure is not entirely predictable by the named parameters, indicating an interdependence between both geometric parameters. Finally, the required pressure ratio of injection to the primary flow to ensure sonic injection has been analysed on TUD’s cold-gas test bench. This allows the respective injection position-dependent threshold to be identified. The analysis reveals that these experiments have been conducted under transsonic injection conditions.

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Section: Introductionmentioning

confidence: 99%

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Sieder-Katzmann,

Propst,

Stark

et al. 2024

Aerospace

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“…Several control strategies have been investigated in the literature including techniques such as Shock Vector Control (SVC), Counter-Flows (CF), Throat Shifting (TS) and supersonic Dual-Throat Nozzle (DTN) [14]. The effectiveness of the mentioned FTV techniques has been investigated numerically and tested experimentally by several research groups [4,7,[15][16][17][18][19][20][21][22][23]. The integration of FTV models in engine and aircraft dynamic models is an on-going research project [24][25][26].…”

Section: Introductionmentioning

confidence: 99%

Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method

Resta

Marsilio

Ferlauto

2021

Fluids

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The application of the Shock Vector Control (SVC) approach to an axysimmetric supersonic nozzle is studied numerically. SVC is a Fluidic Thrust Vectoring (FTV) strategy that is applied to fixed nozzles in order to realize jet-vectoring effects normally obtained by deflecting movable nozzles. In the SVC method, a secondary air flow injection close to the nozzle exit generates an asymmetry in the wall pressure distribution and side-loads on the nozzle, which are also lateral components of the thrust vector. SVC forcing of the axisymmetric nozzle generates fully three-dimensional flows with very complex structures that interact with the external flow. In the present work, the experimental data on a nozzle designed and tested for a supersonic cruise aircraft are used for validating the numerical tool at different flight Mach numbers and nozzle pressure ratios. Then, an optimal position for the slot is sought and the fully 3D flow at flight Mach number M∞=0.9 is investigated numerically for different values of the SVC forcing.

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“…Secondary flow injection has been also used to investigate the thrust-vectoring control on a cold-flow aerospike nozzle [15]. Another approach of jet vectoring is based on the use of synthetic jets instead of continuous blowing [16] and on plasma actuators [17].…”

mentioning

confidence: 99%

Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring

Ferlauto

Marsilio

2017

AIAA Journal

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A computational method tailored for the simulation of fluidic thrust-vectoring systems is employed to investigate the dynamic response of a dual-throat nozzle in open-and closed-loop control. Thrust vectoring in fixed, symmetric nozzles is obtained by secondary flow injections that cause local flow separations, asymmetric pressure distributions, and, as a consequence, the vectoring of primary jet flow. The computational technique is based on a well-assessed mathematical model for the compressible unsteady Reynolds-averaged Navier-Stokes equations. A minimal control system governs the unsteady blowing. Nozzle performances and thrust-vector angles have been computed for a wide range of nozzle pressure ratios and secondary flow injection rates. The numerical results are compared with the experimental data available in the open literature. Several computations of the open-loop dynamics of the nozzle under different forcing have been performed to investigate the system response in terms of thrust-vectoring effectiveness and controllability. These computations have been used to extract autoregressive exogenous models of the nozzle dynamics. The effects of including the actuator dynamics are also discussed. Simple strategies of closed-loop control of the nozzle system by proportional-integrative-derivative regulators are investigated numerically. The closed-loop model predictive control of the system, based on the autoregressive exogenous models, is addressed.

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Side-Force Amplification on an Aerodynamically Thrust-Vectored Aerospike Nozzle

Cited by 36 publications

References 49 publications

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method

Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring

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