Document 448596

Programme for Research-Development-Innovation on
Space Technology and Advanced Research - STAR
Prof. dr.ing. Sterian DANAILA
STAR Programme Annual Conference - 26-27 June 2013, Bucharest, Romania
Coordinating organization
UNIVERSITY POLITEHNICA OF BUCHAREST- Research Center for Aeronautics and Space
Project manager
Sterian DĂNĂILĂ
Address: Bucharest, Str. Gheorghe Polizu , , No 1, CP 011061
Partner organization
INCAS – NATIONAL INSTITUTE FOR AEROSPACE RESEARCH “ELIE CARAFOLI”
Address: Iuliu Maniu, No 220, CP 061126
Partner team leader
Mihai Victor PRICOP
Address: Str. Iuliu Maniu, No 220, CP 061126
Practical relevance of the project
The main goal of the proposal is providing several
validated and verified numerical tools for the thermal
inverse problem arising in supersonic/hypersonic flows.
This objective is of paramount importance in the
aerodynamic prediction of the reentry behavior of space
vehicles.
A vehicle entering the atmosphere from space
experiences an extreme thermal environment due to the
very large velocities involved. The extremely high kinetic
energy of the on-coming air (up to about 100MW/m2) is
suddenly converted into thermal energy as the air passes
through the bow shock. This energy conversion raises
the temperature of the air to as high as 20,000K,
resulting in dissociation and possibly ionization of the air
molecules. When this super-heated air flows over the
vehicle, it results in very high heat transfer to the
surface, requiring a thermal protection system to ensure
the survival of the vehicle.
To predict flow and thermal field quantities, models of
hypersonic flow, aerothermochemistry, thermal radiation
and turbulence are needed.
A space capsule reentering the
atmosphere, with relevant physical
phenomena
The purpose of this proposal is two-fold:
-first, recovering the field distribution of
major quantities characterizing the flow
between the bow shock wave and a bluntnosed body travelling at supersonic /
hypersonic speeds from the air data systems;
- second, uncertainty quantification.
Scientific relevance of the project
DIRECT problems
We associate direct mathematical physics
problems with classical boundary value
problems
often
encountered
in
mathematical physics.
In a direct problem, it is required to find a
solution that satisfies some given partial
differential equation and some initial and
boundary conditions.
Boundary and initial conditions are
formulated to identify, among the whole
set of possible solutions of a partial
differential equation, a desired solution.
With this circumstance, the notion of wellposed statement of a problem is related
(the notion of well-posedness of a problem
according to J. Hadamard).
INVERSE problems
Inverse modeling is to find the causal characteristics from the finite effectual information
like the distributions of pressure, temperature, concentrations, etc.
According to different causal characteristics, the inverse modeling can be categorized
into boundary, retrospective, coefficient and geometric problems.
Boundary problems are to find the boundary conditions that form a certain parameter
field; retrospective problems (time reversed problems) are to find the initial conditions;
coefficient problems are to find some coefficients in the governing equation, for example,
the diffusion coefficient of contaminant transport; and geometric problems are to
reconstruct the geometric characteristics of a domain.
Project goal
The main goal of the proposal is providing several validated and verified numerical tools for the thermal
inverse problem arising in supersonic/hypersonic flows.
Objectives
1) Formulation and solution of the inverse thermal problem in the interior of the reentry body. Starting
from the knowledge of temperature distribution in several points at body surface and/or interior of the
body we will determine the heat flux at the fluid-solid interface;
2) Formulation and solution of the thermal inverse problem in the adjacent fluid flow. Starting from the
knowledge of the heat flux at body surface and/or the pressure at points on the surface, the far-field
parameters of the fluid will be determined such that to obtain the previously mentioned conditions;
3) Theoretical model and computing code for the POD
analysis in the inverse problem in the supersonic/hypersonic
flow. The last result is considered useful for the ESA research
programs because it could be applied for the calibration of
various ESA numerical codes already in use against the
experimental data. This result is independent of the CFD
code;
4) Obtaining experimental data in order to validate POD
analysis.
Estimated results
The engineering verified software package for inverse
thermal and flow fields calculations in supersonic/hypersonic
laminar and turbulent flows
Start date of the project
19.11.2012
End date of the project
19.11.2014
Human resources involved
Work plan of the project
Implementation status of the project_1
Activitate II.1 Probleme cuplate de aerotermodinamica si conductie interioara
M=8 , p0=22 Pa, T0=245 K,
2265547 elemente,
alfa= 2 W/m2.K
(T interior sfera 300 K).
M=9 , p0=20 Pa, T0=233 K,
3675239 elemente,
alfa= 2 W/m2.K
(T interior sfera 300 K).
Implementation status of the project_2
Activitate II.1 Probleme cuplate de aerotermodinamica si conductie interioara
Geometria IXV a fost modificata in prima faza prin eliminarea spatiului dintre corp si flaps
M= 3.5 cu o incidenta de = 288.15K = 6 bar.
Grila initiala 9,4 mil
elemente
Grila adaptata 20
mil. elemente
Implementation status of the project_3
Activitate II.2 Dezvoltare programe de calcul si verificari pentru problema inversa de transfer de caldura
MODEL MATEMATIC
Evolutionary inverse problems 1D
NON-LOCALLY DISTURBED INITIAL CONDITION
Evolutionary inverse problems 2 D
ADDITIVE REGULARIZED SCHEME
Implementation status of the project_4
Evolutionary inverse problems 2D
ITERATIVE REFINEMENT OF THE INITIAL CONDITION
Unsteady inverse problem 1D
RIGHT-HAND SIDE IDENTIFICATION
Steady inverse problem 2D
RIGHT-HAND SIDE IDENTIFICATION
POISSON EQUATION IN A RECTANGLE
Parabolic Unsteady Inverse Problems
Implementation status of the project _5
Activitate II.4 Definirea instrumentarii si geometriei modelului experimental
Mature designs – second iteration
IXV like reentry body
Forces/Moments model
-dorsal repositioning of the sting, as
result of CFD analysis, to minimize
-aluminum alloy 7075
pithing moment
-using existing WT model balance/sting
Temperature instrumentated model
Implementation status of the project_6
Activitate II.4 Definirea instrumentarii si geometriei modelului experimental
Material and instrumentation acquisition
-Aluminum alloy 7075 T651, 850 x 400 x 120mm (115Kg) for manufacturing of 2 sphere and 2 IXV
models
-32 channel National Instruments acquisition system & associated thermocouples: NI 9213, NI
9232, NI 9237, K-Type Thermocouples
Flow assessment technologies
-Specific oil/pigment powder
-Dorsal video camera
Shock wave and separation
Recalibration of trisonic WT using
ONERA M4R model
Risk analysis and contingency plan (lessons learned)
Risk identification
No
Material risk
Solution plan
1
Computer network availability for
computations
Identification of similar facilities in consortium
partners (INCAS facility)
Human risk
Solution plan
Impossibility to achieve a task due to
personnel lack
Identification of PhD or master students to be involved
in project
1
Project’s contribution to the goal of the STAR Programme
The proposed work may contribute to the ESA’s PRIDE Programme with a better
understanding of: a) the basic flow physics during the reentry, b) the sources of
uncertainties in CFD predictions, c) the way to follow to improve CFD calculation
quality. The uncertainty qualification, as actual research subject is included in
ESA_IPC_2011_19,rev5_TRP 2011-13 implementation status.
The proposed work aims at providing future interdisciplinary collaboration
opportunities for the Romanian institutions within long term ESA’s Programmes.
The software produced in the work can be developed for the thermal inverse
problem predictions, the issue related to the in-flight data measurements (as
ESA's PRIDE Programme provides).
Proposal
Software for thermal and flow fields
supersonic/hypersonic boundary layers. Verifications
qualification was approved by ESA, contract in negotiation.
analysis in the
and uncertainty
Dissemination activities
Papers:
1. Aspects regarding hybrid combustion instability control,
author: Sterian DANAILA, accepted for 64th International Astronautical
Congress, Beijing, China, 23-27 September 2013,
http://www.iafastro.net/iac/browse.lite/IAC-13/C4/2/
2. Assessment of the effects of volcanic ash/dust clouds on aircraft safety
authors: Dragos Isvoranu , Sterian Danaila, AWERProcedia Advances in Applied
Sciences, 2013.
3. Experimental results and numerical simulations for transonic flow over the
ONERA M4R model,
authors: Andreea BOBONEA, Mihai Leonida NICULESCU, Mihai Victor PRICOP,
Adrian Chelaru, Florin MUNTEANU, Marius Gabriel COJOCARU, INCAS Bulletin,
Volume 5, Issue 2, April-June 2013.
Conclusions
So far we have performed numerical simulations of heat transfer phenomena in
hypersonic regime for:
canonical configuration of the project (sphere) with the introduction of a molecular
dissociation of air.
modified IXV re-entry vehicle in wind tunnel conditions.
We developed a total of 16 computer programs in FORTRAN language that
implements various methods of solving inverse thermal steady and unsteady
problems.
Using these methods is therefore possible to: a) re-determine the predicted
aerodynamic heating in a numerical experiment and/or b) determine the
aerodynamic heating in an experiment or in real conditions, using measured
temperatures.
The project is carried out according to the schedule specified in the contract.
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