A novel technique for hypersonic vehicle control
A novel control technique is investigated for hypersonic aerial vehicles. The technique is based on the use of active shock bumps (SBs) as a form of control device. The SBs deflect to create shockwaves on–demand, at specific locations around the aerial vehicle. As a result, a force is applied on the...
Main Authors: | , , , |
---|---|
Format: | Article |
Language: | English |
Published: |
EDP Sciences
2019-01-01
|
Series: | MATEC Web of Conferences |
Online Access: | https://www.matec-conferences.org/articles/matecconf/pdf/2019/53/matecconf_easn2019_02008.pdf |
id |
doaj-87e39fe14f844571a0d3553c4b026587 |
---|---|
record_format |
Article |
spelling |
doaj-87e39fe14f844571a0d3553c4b0265872021-02-02T06:38:55ZengEDP SciencesMATEC Web of Conferences2261-236X2019-01-013040200810.1051/matecconf/201930402008matecconf_easn2019_02008A novel technique for hypersonic vehicle controlMitridis DimitriosBliamis ChrisPanagiotou PericlesYakinthos KyrosA novel control technique is investigated for hypersonic aerial vehicles. The technique is based on the use of active shock bumps (SBs) as a form of control device. The SBs deflect to create shockwaves on–demand, at specific locations around the aerial vehicle. As a result, a force is applied on the aerial vehicle, which in turn is used to provide the necessary moment for pitch and roll manoeuvres. In this work, a preliminary aerodynamic analysis of the SB device technique is made by means of CFD. For this purpose, and taking the large corresponding Reynolds numbers of the flow into consideration, the two–dimensional Euler equations are solved. A parametric investigation is carried out, by examining the effect of key parameters, namely the Mach number (M) and device deflection angle (δSB) on the produced force acting on the vehicle, serving as a proof of concept. Using a specific interpolation method, the resultant force is presented as a function of the Mach number and the device deflection angle, on three–dimensional charts, where the effect of each parameter is shown (force–Mach–deflection maps). Furthermore, a preliminary feasibility study is performed, including a kinematic analysis and some key material considerations. Additionally, a kinetic analysis is also conducted to secure the dynamic rigidity of the actuating mechanism and provide an initial estimation concerning weight and basic geometrical parameters of the SB mechanism components.https://www.matec-conferences.org/articles/matecconf/pdf/2019/53/matecconf_easn2019_02008.pdf |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Mitridis Dimitrios Bliamis Chris Panagiotou Pericles Yakinthos Kyros |
spellingShingle |
Mitridis Dimitrios Bliamis Chris Panagiotou Pericles Yakinthos Kyros A novel technique for hypersonic vehicle control MATEC Web of Conferences |
author_facet |
Mitridis Dimitrios Bliamis Chris Panagiotou Pericles Yakinthos Kyros |
author_sort |
Mitridis Dimitrios |
title |
A novel technique for hypersonic vehicle control |
title_short |
A novel technique for hypersonic vehicle control |
title_full |
A novel technique for hypersonic vehicle control |
title_fullStr |
A novel technique for hypersonic vehicle control |
title_full_unstemmed |
A novel technique for hypersonic vehicle control |
title_sort |
novel technique for hypersonic vehicle control |
publisher |
EDP Sciences |
series |
MATEC Web of Conferences |
issn |
2261-236X |
publishDate |
2019-01-01 |
description |
A novel control technique is investigated for hypersonic aerial vehicles. The technique is based on the use of active shock bumps (SBs) as a form of control device. The SBs deflect to create shockwaves on–demand, at specific locations around the aerial vehicle. As a result, a force is applied on the aerial vehicle, which in turn is used to provide the necessary moment for pitch and roll manoeuvres. In this work, a preliminary aerodynamic analysis of the SB device technique is made by means of CFD. For this purpose, and taking the large corresponding Reynolds numbers of the flow into consideration, the two–dimensional Euler equations are solved. A parametric investigation is carried out, by examining the effect of key parameters, namely the Mach number (M) and device deflection angle (δSB) on the produced force acting on the vehicle, serving as a proof of concept. Using a specific interpolation method, the resultant force is presented as a function of the Mach number and the device deflection angle, on three–dimensional charts, where the effect of each parameter is shown (force–Mach–deflection maps). Furthermore, a preliminary feasibility study is performed, including a kinematic analysis and some key material considerations. Additionally, a kinetic analysis is also conducted to secure the dynamic rigidity of the actuating mechanism and provide an initial estimation concerning weight and basic geometrical parameters of the SB mechanism components. |
url |
https://www.matec-conferences.org/articles/matecconf/pdf/2019/53/matecconf_easn2019_02008.pdf |
work_keys_str_mv |
AT mitridisdimitrios anoveltechniqueforhypersonicvehiclecontrol AT bliamischris anoveltechniqueforhypersonicvehiclecontrol AT panagiotoupericles anoveltechniqueforhypersonicvehiclecontrol AT yakinthoskyros anoveltechniqueforhypersonicvehiclecontrol AT mitridisdimitrios noveltechniqueforhypersonicvehiclecontrol AT bliamischris noveltechniqueforhypersonicvehiclecontrol AT panagiotoupericles noveltechniqueforhypersonicvehiclecontrol AT yakinthoskyros noveltechniqueforhypersonicvehiclecontrol |
_version_ |
1724300896196624384 |