SHEFEX II
2nd Flight within
DLR„s Re-Entry Technology and Flight Test Program
Andoya, Norway
DLR`s Re-Entry Program, Why?
- Re-entry or return technology respectively, is a
strategic key competence which becomes obvious
after retirement of the Space Shuttle fleet.
- Currently, the German industry and DLR is well
experienced and prepared within all related disciplines
due to a lot of recent development programs.
- Within DLR CMC based thermal protection systems
are available up to a technology readiness level of 6
to 7
- Within the SHEFEX/REX Development program all
related scientific disciplines like materials and
structures, TPS, flight control, GNC and aerodynamics
are linked together to develop and test in flight new
technologies for innovative space crafts with
SHEFEX-Concept, Why?
- Reduction of manufacturing and maintenance
costs of the thermal protection system up to 50%
due to facetted shape and flat TPS elements
- Sharp edges allow optimized hypersonic
aerodynamic performance with lower drag and
enlarged cross range or re-entry flexibility
respectively
- Scale able aerodynamic performance at
hypersonic velocity.
- Low angle of attack and defined shock geometry
reduces “communication black-out”
- A mission optimized return vehicle shall be
possible
“classic”, high angle of attack
Returnable Spacecraft Technology – Flight Tests
Vortrag > Autor > Dokumentname > Datum
Running activities
CMC Nose Cap System on EXPERT (ESA)
TPS Experiments on FOTON Missions
CMC Fin Experiment on HIFIRE 5 and ablative
stabilizer leading edge on HIFIRE 3 & 5
CMC Stabilizer Fins within SCRAMSPACE
(UQ/DSTO Australia)
n
Köln
-
Porz
n
Stuttgart
n
Oberpfaffenhofen
Braunschweig
n
n
Göttingen
Bremen
n
Location of DLR Competences for SHEFEX
Bremen:
Mission analysis, Navigation technology,
Avionics
Braunschweig:
Aerodynamic vehicle layout, Interstage
Structures, aerodynamic control system,
Göttingen:
Hypersonic Wind Tunnel Tests
Köln:
Instrumentation and Hypersonic Wind Tunnel
Tests, oxide based TPS
Stuttgart:
Program coordination, Vehicle design, TPS and
Hot Structures, Fairing and fin structures
Oberpfaffenhofen:
Rocket Design, Subsystems, RCS-Control,
Launch Operation
Institute of Structures and Design
Institute of Aerodynamics and Flow Technology
Institute of Flight Systems
Institute of Space Systems
Institute of Materials Research
Examination of sharp leading edge structures
3 different materials
250.0°C 1500.0°C 500 1000 1500SHEFEX-Programm
Pathfinder-Mission
Suborbital
Rocket system VSB 30 /Imp.
Orion
Mass approx. 250 kg
Velocity Ma 6, duration 20 s
Successful flight in 2005
Unique free flight test data
Large amount of lessons learnt
2 External passengers
SHEFEX-Program
SHEFEX I
SHEFEX II
Suborbital
Rocket system VS 40 (brasilian)
Controlled hypersonic flight
Mass approx. 500 kg
Velocity Ma 10
Re-entry duration 50 s
Successful Flight 2012
4 External passengers
Re-entry velocity rises from 1.4 km/s to 2.8 km/s
Experiment duration rises from 15 s to 50 s
Acitive flight control during entry phase (100-20 km)
Facettet, symmetric payload tip
Measurement also during ascent phase
Extension of instrumentation and experiments
SH I
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Trj 900
Flight Time [s ec.]
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SHEFEX 2 Basic Mission Scenario
-1st Stage Burn Phase -Precessio n Manoeuvre -Recover y -Experimen t Phase -Desepin, -Fairing Release, Star Track and ACS Manoeuvre -2nd Stage Burn Phase
- 1st stage burn phase
t=62sec
- Precession manoeuvre
tmax≈120sec
- 2nd stage burn phase
t≈70sec
- Despin, Fairing Release,
Star Update and ACS
manoeuvre for reentry
attitude
- Experiment phase from
100km to 20km t≈53sec
- Recovery sequence starting
w/ P/L split in approx. 14km
altitude
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Reentry Angle
Ground Range over Earth curvature [km]
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SHEFEX 2 Preliminary Altitude vs. Ground Range
Apogee Trj800 (Baseline) h≈194km
Ground range GR≈800km
Reentry angle δ≈35
°
Ground range Experiment Phase GR
exp
≈120km
-Experiment Phase
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Mach No. 800 [-]
Alt 800 [10km]
Mach No. 900 [-]
Alt 900 [10km]
Dyn. P res s. 800 [10^4 P a]
Dyn. P res s. 900 [10^4 P a]
Flight time [sec]
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SHEFEX 2 Predicted Reentry Parameter
- Mach No. regime
M≈ 10.3 to 8.7
- Experiment time from
100 to 20km t
exp
≈ 53sec
- Max. dynamic pressure up to
900 kPa at P/L split
- P/L split at h≈ 15km (M≈9)
- Begin of both recovery
sequences at h≈ 4.6km
-Mach Regime
-P/L Split and Recovery
Complete Vehicle Layout - Overview
Vehicle consists of S40/S44 motor combination w/ modified tail can and fins
Interstage adapter with active stage separation system
Motor adapter equipped w/ destruct and separation system
Experiment fins covered by CFK split fairing (l= 1.6m)
Total length l= 12.741m
Total mass m≈ 6800kg
Precession Vehicle Layout – Mass & Dimensions
- Complete experimental P/L
w/ S44 motor and fairing
- Length 6925 mm (excl.
Nozzle extension)
- Mass 1574 kg
- Ipol 154 kgm²
- Ilat 4558 kgm²
Folie 19 > SHEFEX2 DLR, Weihs 21.08.08
Experiment Vehicle Layout - Modules
- Facetted symmetric
forebody w/ five sections a
300mm
- Canard control in Actuator
Module
- Gas Module #1 w/
precession thrusters
- Service Module w/
Antennae
- Main Recovery Module
- P/L Split/Separation
System
- YoYo and Fairing Release
Ring
- Gas Module #2 w/ 4 gas
tanks
- Conical Adapter w/ Aft
Recovery System & ACS
thruster
- Motor Adapter w/ roll
control thrusters
-Split
Experiments on SHEFEX II
9 TPS Systems (ASTRIUM,
MT-A, AFRL, DLR)
1 actively cooled segment
4 „Hot“ Antennas
Hybrid navigation system
Instrumentation, TC,
Heatflux, pressure,
Pyrometer, Compare (IRS)
New ablative fin structure
Aerodynamic control
Hybrid CMC/Metallic
Canards
SHEFEX II: Determination of Aerodynamic Data Base
(numerical and wind tunnel testing)
-Pressure sensors
-Pyrometer
-COMPARE Spectrometer
-Heat flux sensors
-Electronic boxes for
-sensor data processing
-Pressure sensors
-FADS
-Pressure sensors
-Heat flux sensors
-CMC-Tip
-CMC-TPS
-CMC-TPS
-Metallic-TPS
-Alu substructure
Instrumentation
SHEFEX Program Team Weihs 23
SHEFEX Program Team Weihs 24