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Romanian R&D Potential and Industrial Capabilities in Aeronautics

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Romanian R&D Potential and Industrial Capabilities in Aeronautics RomanianRomanian R&D R&D Potential Potential and and Industrial Industrial Capabilities Capabilities in in Aeronautics Aeronautics Dr. Marius-Ioan PISO, ROSA - Romanian Space Agency [email protected] Dr. Catalin NAE, INCAS – National Institute for Aerospace Research [email protected] Aeronautics Days 2006, 19-21 June 2006, Vienna RomanianRomanian Capabilities Capabilities in in Aeronautics Aeronautics ContentsContents • R&D capabilities • Industrial capabilities • Romanian National AEROSPATIAL RTD Program • Some conclusions Aeronautics Days 2006, 19-21 June 2006, Vienna 1 RomanianRomanian Capabilities Capabilities in in Aeronautics Aeronautics GeneralGeneral Overview Overview • Research establishments – State-own national research establishments (INCAS) – Private research companies (INAv, STRAERO) – Agencies and NGO’s (IAROM, ROSA, OPIAR) • Aeronautical industry – Primes - Major a/c and helicopter companies (AEROSTAR, ROMAERO, Avioane Craiova, IAR Brasov/EUROCOPTER); – Airframers – Small/Medium private companies • Universities/Academia – University Politehnica Bucharest (Aerospace Engineering Dep.) – Romanian Academy – Institute for Applied Math. Aeronautics Days 2006, 19-21 June 2006, Vienna RomanianRomanian Capabilities Capabilities in in Aeronautics Aeronautics R&DR&D Policy Policy Romanian National R&D Program Universities ROSA AEROSPATIAL Program Research & Development Manufacturing Units Units INCAS COMOTI AEROFINA IAR Bucharest Bucharest Bucharest Brasov STRAERO SIMULTEC AEROSTAR METAV Bucharest Bucharest Bacau Bucharest INAV CPCA AEROTEH ROMAERO Bucharest Craiova Bucharest Bucharest ELAROM AVIOANE TURBOMECANICA Bucharest Craiova Bucharest Aeronautics Days 2006, 19-21 June 2006, Vienna 2 A.A. Romanian Romanian Research Research and and Development Development CapabilitiesCapabilities Cost Analysis Safety Requirements Competitivity Time to Market Regulations Aeronautics Days 2006, 19-21 June 2006, Vienna INCAS – National Institute for Aerospace Research “Elie Carafoli” B-dul Iuliu Maniu 220, sector 6, Bucharest, ROMANIA www.incas.ro Tel. +40(21) 434.00.83, Fax +40(21) 434.0082 Aeronautics Days 2006, 19-21 June 2006, Vienna 3 INCASINCAS – – National National Institute Institute for for Aerospace Aerospace Research Research SubsonicSubsonic Wind Wind Tunnel Tunnel (2.5(2.5 x x2.0 2.0 m, m, 110 110 m/s) m/s) Aeronautics Days 2006, 19-21 June 2006, Vienna INCASINCAS – – National National Institute Institute for for Aerospace Aerospace Research Research SupersonicSupersonic Wind Wind Tunnel Tunnel (1.2(1.2 x x1.2 1.2 m, m, Mach Mach 0.2…3.5) 0.2…3.5) Aeronautics Days 2006, 19-21 June 2006, Vienna 4 INCASINCAS – – National National Institute Institute for for Aerospace Aerospace Research Research CFDCFD & & Grid Grid Computing Computing Aeronautics Days 2006, 19-21 June 2006, Vienna INCASINCAS – – National National Institute Institute for for Aerospace Aerospace Research Research AircraftAircraft Design Design Aeronautics Days 2006, 19-21 June 2006, Vienna 5 INCASINCAS – – National National Institute Institute for for Aerospace Aerospace Research Research FlightFlight Dynamics Dynamics Autonomous navigation from the mechanical perspective: (a) Physical quantities determined without the external referential. (b) The principals curvatures determined with a ccomputing procedure on board of aircraft. Intrinsic coordinates of an arbitrary curve Steady-state relative to the trajectory , enlarged category of steady evolutions Serret-Frenet coordinates, denoted x, are expressed as follows: 1 Structural stable control regarding the restrictions evelopments s s s D x(s) = exp( ω×(τ)dτ)⋅ x + [ exp( ω×(λ)dλ)⋅ dτ]⋅ 0 ∫ 0 ∫ ∫ s s τ Primary control decoupling (regarding aero-dynamics and inertia) 0 0 0 − 0 kn (s) 0 The mechanical movement broke up into : with: ω× = k (s) 0 − k (s) Applications n t (a) The movement along the flight path (b) The movement around the flight path 0 kt (s) 0 and the exponential function defined in reference [8] Stabilised statement of principal curvatures (R t ) k W 1 K 2 − W 2 K 1 k& = FO 1 ⋅ ' k 'k n 1 2 t k t l − t k t l W'kW'l (R FO )1 (R FO ) 2 (R FO ) 2 (R FO )1 Mechanical Modeling The control of Following the Trajectory (R t ) k W 2 K 1 − W 1 K 2 k = FO 2 ⋅ 'k 'k Supplementary effects of rotors stated Control decoupling : t 1 2 t k t l − t k t l k nW'kW'l (R FO )1 (R FO ) 2 (R FO ) 2 (R FO )1 in the non-inertial reference frame of the (a) inertial effects 1 2 − 1 2 F 2' F 3' F 3' F 2' aircraft . (b) aerodynamic effects not = 1 2 − 1 2 µ⋅ − t ⋅ = The dynamics decoupling : considering: 0 F 3' F 1' F 1' F 3' R FO u W (x γ ) (a) algebraic sub-system determining the F 1 F 2 − F 1 F 2 1' 2' 2' 1' control variables t=[ ] u 1 0 0 , R FO is the rotation matrix of Serret-Frenet axes system (b) differential sub-system determining the < > < > r = r ⋅ q ⋅ p ⋅ h − r s l k − r l t k ⋅ + r t k ⋅ 2 state variables related to the flight path and K (S q S p S h ) W W'k l '' s X& X& X& [(3 W'k 'l X& )R FO ]2 (kn ) (W' k R FO )1 (k n ) Control Variables Sub-System Cinematics Variables Sub-System δ = ⋅ − ⋅ ∆ δ⋅⋅ * * ⋅ ⋅ − ⋅ ∆∆ * E (I Qδ ) k C δ E (I Qδ ∆∆) Cδ T l1 3 &t −1111 0 T l1 3 T * = Ω δ ⋅ E ⋅[I − ]⋅ δ l2l3 3 * − k Cδ v c 1 * t * * * &n T δ = −(M δ ) ⋅[ M + J(B⋅ ∆∆∆∆⋅ B )( −F + Cδ ⋅ M )] − χ = Π ⋅ω − c −1 ⋅ − T + ⋅ ∆∆⋅ t − + * ⋅ T ⋅ − ⋅ ∆∆ δ⋅ * & a a (M δ ) [ M δ J(B ∆∆ B )( Cδ Cδ M δ )] El (I3 Qδ ∆∆) T T T 1 σ = Π ⋅ω & f f f − * + * * = t ⋅ * ( F Cδ M ) X& F v δ x v ω v ω = ( ; , a , &, & a ) * C δ T Control law, u, differential modeled : σ = σ σ = σ & F( ,u) (t0 ) 0 with: and 0=W(σ,u) = σ = u& U( ,u) u(t0) u0 σ = σ + ~ σ Φ U( ,u) U( ,u) U( ,u; ) in witch: Analitical, continuous solution, of the equation sin( x) = f (t) the reference dynamics , ~ the dynamics of the deviatio ns from the restrictions = = U U With the conditions: x(t0 ) x0 ; sin( x 0 ) f (t0 ) W& = Φ(W,σ,u) the dynamics of the restrictions = − r f ( t) ⋅ + ⋅ π x (t ) ( )1 a sin[ f (t0 )] rf (t ) in witch: r (t ) is the solution of the equation x = (− )1 r f ( t 0 ) ⋅ a sin[ f (t )] + r ( Natural Stability of the unsteady evolutions: f 0 0 0 f The damping has the same characteristics as the perturbed local movement . dx (t + τ ) + τ = + − k ⋅ + τ ⋅ + τ ⋅ 0 r f (t ) r f (t ) ∑ ( )1 f (t k )] f (t 0 ) sgn[ ] < τ < τ ~ 0 k dt The comparison between the curent perturbation, z(t + τ;...) , and the local + τ = | f ( t k |) 1 + τ τ = ς > perturbation, z(t ;...) tend to the formulation: 0 min ( )0 ∃τ > → ∀τ ∈ τ ∀ ≥ ~ + τ ≤ + τ ~ + τ + τ | f ( t −ς |) =1 ( 0 0) ( (0, 0 ), t t 0 , || z(t ; ...) || || z(t ;t, z(t;...), x(t ), u(t )) ||) The necessary condition for the neutral stability: ∂ ∂ ∂ ∂ t t f t f z ⋅ x[& ⋅ + u& ⋅ ]⋅ z ≥ 0 ∂x ∂x ∂u ∂x Control Sub-System ~ r r r + r k k M M C M I 0 M I 0c k ω = ⋅ + + − ω r=1,2,3 & cr [( ~ r ~ r ) ~ r ] & O J d r Jd r Jd r t <1> ~ t <1> = ⋅ + + ⋅ + mv&γ (RCF ) ( R R C ) (RCF ) ( R I 0 R I0c ) χ = Π ⋅ ω & a aN Generating Flight Path Sub-System σ = Π ⋅ ω & f f f Σ = Π ⋅ ω & O O O λ R O cos E X& = ⋅ ⋅v ⋅sin ψ cos θ E R cos λ N f f Mechanical modeling Trajectory Tracking Control R Y& = O ⋅ v ⋅ cos ψ cos θ E R N f f Interactions uniform structuring Local Control : ⋅ θ Z& E = vN sin f The Dynamics of the Aircraft (multi- (a) the local principal curvatures are s&γ = vγ bodyu dynamics): the new references (a) general effects (b) the control laws are differential Equilibrium on Flight Path Sub-System 2 = t <2> ⋅ ~ + + t <2> ⋅ + (b) specific effects of each body modeled mk nv γ (RCF ) ( R R C ) (RCF ) ( R I 0 R I0c ) (c) coupling effects of bodies The control variables are the new = t <3> ⋅ ~ + + t <3> ⋅ + 0 (RCF ) ( R R C ) (RCF ) ( R I 0 R I0c ) movements. references The cinematic superposition of : (a) the Serret-Frenet axes system The dynamic equilibrium relative to kinematics the trajectory (b) the kinematics relative to the is Serret-Frenet axes system The Necessary and Suficient Autonomous relative positioning : condition for the trajectory tracking (a) the two poles axis representing control of the Aircraft and Referential. (b) the normal plane to these axis Aeronautics Days 2006, 19-21 June 2006, Vienna INCASINCAS – – National National Institute Institute for for Aerospace Aerospace Research Research ProjectsProjects in in EU EU FP5 FP5 and and FP6 FP6 • FP5 CASH Collaborative Working within the Aeronautical Supply Chain, 2000 EXPRO Experimental and Numerical Study of Reacting Flows in Complex Geometries, 2001 IMAGE Interoperable Management of Aeronautical Generic Executive Software,2003 • FP6 EGEE Enabling Grids for e-Science, 2004 SEE-GRID South-Eastern European Grid-enabled e-Infrastructure Development, 2005 UFAST Unsteady Effects in Shock Wave Induced Separation, 2005 CESAR Cost Effective Small Aircraft, 2006 AVERT Aerodynamic Validation of Emission Reducing Technologies, 2006 Aeronautics Days 2006, 19-21 June 2006, Vienna 6 Aeronautics Days 2006, 19-21 June 2006, Vienna Aeronautics Days 2006, 19-21 June 2006, Vienna 7 Aeronautics Days 2006, 19-21 June 2006, Vienna Aeronautics Days 2006, 19-21 June 2006, Vienna 8 Aeronautics Days 2006, 19-21 June 2006, Vienna Aeronautics Days 2006, 19-21 June 2006, Vienna 9 •Validation and certification for a/c structures •Fatigue, endurance and dynamic stability •Ground vibration tests •Theoretical and experimental analysis for a/c structures Aeronautics Days 2006, 19-21 June 2006, Vienna B.B.
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