Information is given in viewgraph form on the Aeroassist Flight Experiment (AFE), an experiment with the objective of investigating critical vehicle design and environmental technologies applicable to the design of aeroassisted space transfer vehicles. Information is given on design, simulation, flight regime, mission requirements and objectives, instrumentation, and the project schedule

Siemers, Paul M., III

English

NASA Technical Reports Server

AEROASSIST FLIGHT
(AFE)
EXPERIMENT
GO
L.O
c.E)
AIAA / OAST
ON CSTI AND
CONFERENCE
PATHFINDER
TECHNOLOGY FOR FUTURE
NASA MISSIONS
SEPTEMBER 12-13, 1988
P. M. Siemers / NASA LaRC
(30
I
i..a
https://ntrs.nasa.gov/search.jsp?R=19890002408 2020-03-20T05:57:26+00:00Z
0
CD
09_
AEROASSIST FLIGHT EXPERIMENT
OBJECTIVE:
TO INVESTIGATE CRITICAL VEHICLE DESIGN AND
ENVIRONMENTAL TECHNOLOGIES APPLICABLE TO
THE DESIGN OF AEROASSISTED SPACE TRANSFER
VEHICLES
0
t_
, r\
AOTV DESIGN / AFE SIMULATION CHALLENGES
O
GO
CO
_'rl ;;O
OZ
_r_
Thickened
shock
Ionized
shock layer
Nonequilibrium !i_!
chemistry
Radiation
Noncatalytic
surface
Slip boundary
conditions
Aerobrake
Solution must
/ _ include wake flow
-
Payload
Convective and
radiative heating
0350
300
250
< 200
t50
VELOCITY, kff / sec
I
36
ASTV REQUIREMENTS SUMMARY
• INABILITY TO ESTABLISH DATA BASE REQUIRED IN GROUND FACILITIES
ESTABLISHES NEED FOR COMPUTATIONAL CAPABILITIES WHICH MUST
BE VERIFIED USING FLIGHT DATA
O
(.2-1
• EXISTING FLIGHT DATA NOT APPROPRIATE FOR ASTV
• AEROASSISTED TECHNOLOGY FLIGHT EXPERIMENT REQUIRED
AFE MISSION OBJECTIVES
OBTAIN DATA TO:
• RESOLVE RADIATIVE HEATING ISSUE
O
• DETERMINE WALL CATALYSIS EFFECTS
• DEVELOP/DEMONSTRATE TPS MATERIALS
• DEFINE WAKE FLOW, BASE HEATING
• ASSESS AERODYNAMICS AND CONTROL
• PROVIDE CFD CODE VERIFICATION DATA
AFE DESIGN / MISSION REQUIREMENTS
CONFIGURATION:
• SHOCK LAYER THICKNESS > 7 INCHES
• BLUNT, RIGID FOREBODY
• DIAMETER > 12FEET
• L/D 0.2 m 0.3
• ROLL CONTROLLED
• NON-ABLATIVE HEATSHIELD
• RECOVERABLE
TRAJECTORY:
• ENTRY INTERFACE (400,000 FT) > 33,800 FPS
• RELATIVE VELOCITY > 31,660 FPS AT 279,000 FEET ALTITUDE
• PERIGEE = 250,000 + 13,000 FEET
• QUIESCENT PERIOD PRIOR TO PERIGEE (30 SEC)
AFE INSTRUMENTATION
ASTV TECHNOLOGY ISSUE AFE EXPERIMENT
CO
SHOCK LAYER RADIATION
SURFACE CATALYSIS
TPS MATERIALS
WAKE FLOWS / HEATING
AERODYNAMICS / CONTROL
COMPUTATIONAL FLUID
DYNAMICS
• RADIATIVE HEATING (RHE)
• WALL CATALYSIS (WCE)
• HEAT SHIELD PERFORMANCE (HSP)
• ALTERNATE THERMAL PROTECTION MATERIALS (ATPM)
• BASE FLOW AND HEATING (BFHE)
• AFTERBODY RADIOMETRY (ARE)
• AFT FLOW IONIZATION (AFIE)
• AERODYNAMIC PERFORMANCE (APEX)
• RAREFIED-FLOW AERODYNAMIC MEASUREMENT
• AIR DATA SYSTEM (PD/ADS)
• RAREFIED-FLOW AERODYNAMIC MEASUREMENT
(RAME)
• PRESSURE DISTRIBUTION P@/ADS)
• FOREBODY AEROTHERMAL CHARACTERIZATION (FACE)
• MICROWAVE REFLECTOMETER IONIZATION SENSOR (MRIS)
(RAME)
FOREBODY INSTRUMENTATION
x
(_ TELEMETRY ANTENNA
[] WALL CATALYSIS
<_ ATPM
TOTAL RADIOMETER
BROAD BAND SPECTROMETER
_1_ HIGH RESOLUTION SPECTROMETER
x
[]
A
x
X Xx
A
O0
HEATSHIELD PERFORMANCE
MRIS
x PRESSURE DISTRIBUTION
I_] AIR DATA SYSTEM
• THERMOCOUPLE
BASE REGION INSTRUMENTATION
XO
O
_) - TELEMETRY ANTENNA
X - PRESSURE TAP
O - THERMOCOUPLE
- LANGMUIR PROBE
C - CAMERA VIEWPOINT
- TOTAL RADIOMETER
_1_ - BROAD BAND SPECTROMETER
_1_ - RESOLUTION SPECTROMETERHIGH
AEROASSIST FLIGHT EXPERIMENT
PROJECT SCHEDULE
(AFE)
KEY MILESTONES
SPACECRAFT DEVELOPMENT
• SYSTEM DESIGN
• CARRIER VEHICLE
FY88 FY 89 FY 90 FY 91 FY 92 FY 93 FY 94
• AEROBRAKE
• INSTRUMENTS
1988
PRR
V'
PRR
1989
PDR
V'
1990 1991
DELTACDR
RP' RP'CDR
P:_E
T "ST
REV
'V'
PDR
DELTA
CDR
1992 1993
DCR
RV' RF' _r CDR RP'_P'
DESIGN I FAB/TEST
I
_RI
I I
DEFINITION PROCURE FAB/TEST
PDR
V'
DESIGN
PDR
Iv,
DESIGN
CDR IV V_ chEL
CDRI v I I
,<-.FA.,TEST IDEL/
• SPACECRAFT ASSY & TEST
MISSION INTEGRATION
KSC INTEGRATION / TEST
MISSION PLANNING/
!
;"t I
OPS PLANNING \
1994
FRR
FLT
'V' V'
FLT



Aeroassist Flight Experiment (AFE)

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