THE INTERMEDIATE EXPERIMENTAL VEHICLE IN FLIGHT EXPERIMENTATION. FROM THE DESIGN TO THE FLIGHT.

Transcription

1 8 th Eurpean Cnference n Aerthermdynamics fr Space Vehicles 2 6 March, 2015 Lisbn, Prtugal THE INTERMEDIATE EXPERIMENTAL VEHICLE IN FLIGHT EXPERIMENTATION. FROM THE DESIGN TO THE FLIGHT. G. C. Rufl *, F. Camarri +, R. Rman, D. Vernani, G. Tumin * CIRA/ASI Technical Assistance t ESA Thales Alenia Space Italia, Trin, Italy RUAG Space, Zurich, Switzerland ESA-LAU, Paris, France

2 The IXV System and bjectives The spacecraft is characterized by a lenght f 5.0m, width f 2.2m, height f 1.5m and a mass f abut 1.8 tns. System Demnstratin. First lifting-bdy system flying a fully representative return missin frm LEO wrld-wide. Technlgy in-flight Verificatin Advanced thermal prtectins and ht structures (with ceramics and ablatives) Advanced guidance navigatin and cntrl techniques (with thrusters and aer-flaps) Advanced Aerthermdynamics investigatin techniques (with 300 integrated sensrs)

3 The IXV System Descriptin The Space Segment

4 IXV Experiment Plan OBJECTIVES EXPERIMENTS MEASUREMENT AERODYNAMICS AEROTHERMODYNAMICS Investigatin and quantificatin f aerdynamic and aerthermdynamic phenmena during atmspheric reentry Cntinuum Flw High Altitude Aerdynamics Flush Air Data System Base Flwfield General Heating Wall catalysis Flap ATD+SWBLI Jet Flwfield Interactin Laminar t Turbulent transitin IR CameraTemp Mapping Cavity heating Slip Flw/Skin Frictin SENSORS Type S Thermcuple 105 Type K Thermcuple 89 Abslute Pressure Sensr 37 Differential Pressure Sensr 2 Displacement Sensrs 12 Strain Gauges 48 TPS & HS Validatin f therm-mechanical perfrmance in re-entry cnditins FLIGHT MECHANICS & GNC Mdels Verificatin (Vehicle Dynamics, FPCS, RCS, AED, MCI). Perfrmance and margin verificatin C/SiC Nse Cap C/SiC Shingles TPS Junctin Bdy Flap Hinge Line Seal Ablative TPS Vehicle Mdel Idenificatin Infra Red Camera 1 Inertial Mtin Unit 1 EDAR Experiment Data Acquisitin & Recrding One Data Acquisitin Unit Master Fur Data Acquisitin Units (DAUs) One Ethernet Switch Tw Slid State Recrders One Exp Telemetry Transmitter Tw Exp Telemetry Antennas Fur Redundant Recrders n DAUs IR camera Data Handling Unit 4

5 ATD Experiments Overview LAMINAR TO TURBULENT TRANSITION 34 Type S TCs in lngitudinal and spanwise arrays t detect temperature jump 6 Displacement sensrs t detect steps height in critical TPS znes GENERAL HEATING T investigate the glbal heating f the vehicle surface during all the hypersnic phases f the re-entry All the surface temperature measurement are part f this experiment. WALL CATALYSIS - CATE Tw Mullite Catalytic patches t induce a temperature jump and cnfirm the FRC behaviur f the ceramic material in flight. 30 Type S TCs n the CMC accrss and aside the catalytic patches SWBLI 21 Type S TCs + 4 PS + IRC t detect the effect f Shck Wave Bundary Layer Interactin and Shck/Shck Interactin. The triggering and detectin f these phenmena will depend n the actual flap deflectin experienced during the flight 5

6 ATD Experiments Overview FLUSH AIR DATA SYSTEM Derive AA, AS and atmspheric quantities frm pressure and temperature measurements. 6 Pressure Sensrs in crss shape. 7 Thermcuples in crss shape. TC PS SLIP FLOW AND SKIN FRICTION Pressure rati (difference) between tw pressure tap at different inclinatin is a functin f slip velcity (shear strss) in rearefied (cntinuum) Require crrelatin with CFD and pst flight grund calibratin CONTINUUM FLOW T investigate cntinuum regime aerdynamics. 28 Pressure sensrs n vehicle surface Aerdynamic Cefficients derived frm VMI experiment HIGH ALTITUDE AERODYNAMICS T derive AED cefficient estimatin in rarefied/transitinal regime ( km) via IMU acceleratin measurement. Derived quantities (e.g. L/D) and nrmal cefficient lw variability in transitinal regime used t estimate density. 6

7 ATD Experiments Overview JET FLOW FIELD T investigate interactin between RCS jet n the base with external flw field. Plume spreading and plume impingment 3 PS n base plate after nzzle exit fr each RCS pd + 4 TCs Jet efficiency is derived frm IMU angular rate measurements CAVITY HEATING T investigate lcal aerthermdynamics in flap cavities and pssible sneak flw due t pressure gradient and imperfect sealing. 5 Type S Thermcuples in the hinge bx cavity arund the flap and in the gap between the tw flaps BASE FLOW FIELD T gather data fr CFD validatin in a regin affected by large uncertainity. Separated flw in laminar and turbulent regime. 8 PS (mainly t characterize base pressure in supersnic/transnic regime) 8 Thermcuples IR CAMERA MAPPING Advanced experiment t mnitr Flap temperature evlutin trugh an Infra Red Camera Flap view is btained by means f an external periscpe. 7 TCs n flap t prvide reference t IR measurement 7

8 TPS&HS Experiment Overview CMC TPS & HS Experiment: Characterizatin f CMC TPS & HS behavir during re-entry. 36 Strain Gauges n metallic stand-ff f Nse and Shingle Synergy with ATD sensrs: Thermcuples and Pressure Sensrs CMC nse with instrumented stand-ff In additin 12 Internal Thermcuples and 5 Pressure Sensrs t characterize the behavir f insulatin and seals. 12 Displacement Sensrs t measure steps in critical pints Hinge TPS and Flap HS 12 TCs t characterize thermal behviur f CMC Hinge TPS and Flap Ht Structure including rd and bearings. Internal Sensrs 8

9 TPS&HS Experiment Overview Ablative TPS Experiment: Investigate and characterize the in-flight behavir and insulating perfrmance f the ablative TPS assemblies. 15 instrumented plugs t measure temperature at different depth (35 TCs in ttal) in rder t characterize temperature evlutin in charred and virgin layer. 16 Pressure Sensrs in synergy with ATD experiment t characterize surface envirnment. 9

10 GNC Experiment Overview VEHICLE MODEL IDENTIFICATION The peratinal envirnment tgether with the vehicle characteristics make the IXV addressing all cmplex issues related t the hypersnic/supersnic phase f a re-entry frm LEO, cntrlled with RCS thrusters and aerdynamic surfaces; The IXV missin will allw: Mdels verificatin (vehicle dynamics, FPCS, RCS, AED); Perfrmance and Margins verificatin. The validatin f the vehicle flight dynamic mdel is pursued thrugh the Vehicle Mdel Identificatin experiment (VMI), including: Sensr calibratin t cmpensate fr IMU systematic errrs; Trajectry recnstructin t be used during the parameter estimatin prcess; Parameter estimatin t update the pre-flight mdels; Mdel validatin t check the estimated parameters. 10

11 PRESSURE SENSING SYSTEM Pressure Sensrs: Sensrs Descriptin and Integratin Custmized KULITE abslute and differential pressure transducers. Best accuracy cmpatible with harsh envirnment. Full sensrs thermal and mechanical qualificatin achieved in phase D Sensrs Mechanical Qualificatin Pressure Manifld (5 bracket in ttal) Pressure Prt in Ceramic: Ceramic nut c-densified with ceramic skin. Design cmplexity induced by high thermal gradient and need t guarantee tight cupling with incnel piping. Pressure Prt in Ablative: Ceramic tube inserted int ablative t maintain shape and tightness. Pressure Prt in Ceramic Cmpnent Pressure Prt fr ablative 11

12 TEMPERATURE SENSING SYSTEM Thermcuples in CMC: Sensrs Descriptin and Integratin Platinum Rhdium Type S Thermcuple Cated with Titanium Nitride t prevent reactins with C-SiC Cmb System fr TCs n mvable flaps Thermcuples in ablative: P50 Ablative plug with Type K TCs at 3 different depth (3, 10, 18 mm frm surface. Type K Thermcuples n CS Frnt Bulkhead TC bracket Flap Cmb System Shingle TCs Flap Tcs Ablative TCs Plug assembly 12

13 STRAIN GAUGES ½ Bridge Encapsulated Strain Gauges with Thermal Cmpensatin and bridge adapter. Spt welded. Calibratin perfrmed at stand-ff level Sensrs Descriptin and Integratin DISPLACEMENT SENSORS Assembly with LVDT in Incnel Husing. Aluminium Titanate rd in cntact with Ht CMC parts. Nse Metallic Stand-Off with strain gauges and TCs SGs Callibratin Displacement Sensrs sticking ut frm TPS insulatin Displacement Sensrs Nse with bundles f sensrs ruted (TCs, 13 Testing Pressure, Strain Gauges)

14 Sensrs Descriptin and Integratin INFRA RED CAMERA ASSEMBLY XEVA XS Infrared Camera Frnt Optic Assembly with Sapphire Mirrr and Incnel Husing. degc) Rtating Multiclur Filter Wheel fr emissivity derivatin Waterprf Data Handling Unit Dedicated SW fr data acquisitin and Image Cmpressin RAW data recrded n DHU and cmpressed images sent trugh telemetry. Whle assembly fully qualified Accurate Elevn deflectin angle cmputatin Infrared Camera Data Handling Unit IRC Periscpe (Left) Infra Red Camera with Filter Wheel (Right) IXV Flap Image taken with IRC 14

15 Cnclusin All the experimental data have been succesfully transmitted n grund trugh telemetry. Memry card have been extracted frm n bard data recrder and are travelling t eurpe Pst Flight analysis level-0 is currently n ging. At a glance, measurement frm thermcuples, pressure sensrs, displacement sensrs seems cherent. First snapsht f temperature measurement shws value sensibly lwer than sizing ne as evident als frm the ablative TPS status after recvery.

16 8 th Eurpean Cnference n Aerthermdynamics fr Space Vehicles 2 6 March, 2015 Lisbn, Prtugal