aerodynamics and planetary entry - nasa · lemphasis - the effect of aerodynamic errors,...
TRANSCRIPT
Leslie A. Yates(650) [email protected]
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Aerodynamicsand Planetary Entry
Leslie A. YatesGary T. Chapman
Presented at JPLJune 6, 2002
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Leslie A. Yates(650) [email protected]
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Overview
l Background
l Objectives– General description of planetary entry
– Impact of aerodynamics on trajectory
– Review sources of aerodynamic information
– Review status of aerodynamics
l Concluding remarks, issues, and futuredirections
Leslie A. Yates(650) [email protected]
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Background
l Extensive interest in the 1960’s to 70’s– Research– Probes to Venus, Mars, and Jupiter
l Renewed interest in the 90’s– Probes to Mars, Stardust, Huygen, Genesis
l Project driven environment leads to:– Erosion of expertise and database– Limits innovation
l Greater demand on aerodynamics– Increased program requirements– Aeroassist to reduce costs
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lGeneral Description of PlanetaryEntry
lDemonstrate role of aerodynamicson planetary entry
lReview sources of aerodynamicinformation
lReview status of aerodynamics ofplanetary entry shapes
Objectives
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l Entry
– Max. loads
– Max. heating
l Special events
– Parachute deployment
l Unplanned events
– Vehicle breakup
Schematic of Planetary Entry
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Planar Planetary Entry
l Equations
where
m ˙ V = −qACD + mgsinγ
mV˙ γ = −qACL + mV2
r− g
cosγ
I ˙ ̇ Θ = qAl Cm∑
CL = CL0 + CLα (α − αt )
Cm∑ = Cmα (α − α t ) + Cmq
˙ Θ lV
+
Cm ˙ α ˙ α lV
+ Cmδδ
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Point Mass Behavior
l Equations of motion:
l Important events /issues– Maximum q– Maximum heating– Mach at impact /
parachute deploy– Landing footprint
m ˙ V = −qACD + mgsinγ s
mV˙ γ s = −q A CL0 + CLα (α t + αs )[ ] − m
V2
r− g
cosγ s
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Oscillatory Behavior
l Equations of Motion
l Stability Criteria
– Static:
– Dynamic:
l Important events / issues– Control system design– Amplitude at impact /
parachute deploy
Cmα < 0
I˙ ̇ θ 0 = qAl Cmαα + Cmq
˙ θ 0lV
+ Cm ˙ α ˙ α 0lV
ρACD
mK < ∂q ∂s
q+
∂Cmα ∂s
Cmα
K = 1CD
−CLα + lσ
2Cmq + Cm ˙ α ( )
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Typical Planetary EntryImportant Events / Effects
Impact velocity /parachutedeploy
Maximumdynamicpressure
Maximum heating
Amplitude growth
Minimumamplitude
Impact angle
Mars Pathfinder Data
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lGeneral Description of PlanetaryEntry
lDemonstrate role of aerodynamicson planetary entry
lReview sources of aerodynamicinformation
lReview status of aerodynamics ofplanetary entry shapes
Objectives
Leslie A. Yates(650) [email protected]
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Impact of Aerodynamics onTrajectory
l Impact demonstrated using trajectorysimulations
l Conventions and definitions– Coordinate systems used for aerodynamic
forces / moments
– Nondimensionalization of the aerodynamicforces / moments
– Static and dynamic stability
l Simulations - Description and examples
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l Three coordinate systems used to describe motion:inertial, wind, and body
l Forces - two conventions used– Parallel and normal to flight path
Drag, lift, and side force
– Parallel and normal to body axesAxial, normal, and side force
l Moments– Pitching / yawing referenced to body axes and center of
gravity• Static• Dynamic
– Rolling referenced to body axes and center of gravity
Aerodynamic Forces and Moments
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Nondimensionalizationl Reduces number of simulation variables, resulting
terms valid over wider range of conditions
l Forces:
l Moments:
l Rates:
l Caution: Various quantities used to nondimen-sionalize variables (l or d, V or 2V)
CD = D0.5ρV2 A
Cm = M0.5ρV2 Ad
˙ α = ˙ α d2V
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Coefficient Math Modelsl Aerodynamic coefficients functions of Mach
Number, Reynolds Number, angles, angular rates,control deflections, …
l Look up tables, polynomials, and complicatedfunctions used to model coefficients
Mars Pathfinder Mars 03, Ballistic Range
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l Static stability
– If displaced from equilibrium vehicle tends toreturn to or pass through equilibrium point
l Dynamic stability
– Amplitude of oscillatory motion decreases withtime
l Limit cycle
– Motion approaches constant amplitude
Definitions
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Stability – Limit Cycle
-0.40
-0.30
-0.20
-0.10
0.00
0.10
0.20
0.30
0.40
0.00 0.05 0.10 0.15 0.20 0.25 0.30
Calculated, 1 Calculated, 2Measured, 1 Measured, 2
-0.80
-0.60
-0.40
-0.20
0.00
0.20
0.40
0.60
0.80
0.00 0.05 0.10 0.15 0.20
Calculated, 1 Calculated, 2Measured, 1 Measured, 2
-0.6
-0.4
-0.2
0.0
0.2
0.4
0.6
0.8
1.0
0 5 10 15 20 25
Angle(deg)
Mach = 1.25Mach = 1.50Mach = 1.75Mach = 2.00Mach = 2.50Mach = 3.00Mach = 3.50
When damping coefficientis nonlinear function ofangle, Mach, complicatedbehaviors occur.
Mars 03 Unstable
Stable, Limit Cycle
Cmq + Cm ˙ α
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Trajectory Simulations
l Brief description of simulations
l Examples
– Linear aerodynamics
– Nonlinear aerodynamics
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Linear Aerodynamics Simulations
l Six-degree-of-freedom, nonlinear mathmodels
l Density profiles, gravitational forces, androtational rates consistent with Mars
l Vehicle specifications and aerodynamicsconsistent with axisymmetric probeconfigurations
l Shallow entry for longer flight paths andbetter demonstration of effects
l Not modeled - winds, controls
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Linear Aerodynamics Simulations(concluded)
l Emphasis - the effect of aerodynamic errors,uncertainties on the entry
l Varied parameters:– Drag, lift coefficient slope, trim lift, trim angle,
moment coefficient slope, damping, roll
l Comparative effects– Forces, moments proportional to dynamic pressure
• 5% variation in density produces similar effect as 5%variation in aerodynamic coefficient
• 5% variation in velocity produces similar effect as 10%variation in aerodynamic coefficient
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Drag CoefficientDynamic Pressure, MachLongitude
1° of longitude translates to ≈60 km
Total Angle
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Lift Coefficient SlopeAmplitude Dynamic Pressure
Longitude
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Trim Lift Coefficient
Altitude Total Angle
Longitude Dynamic Pressure, Mach
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Trim Angle VariationLongitude Dynamic Pressure, Mach
Total Angle
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Pitching Moment CoefficientAmplitude Dynamic Pressure
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Damping Parameter
Longitude
Amplitude Dynamic Pressure
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Roll RateAmplitude Dynamic Pressure
Longitude
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Summary of Linear AerodynamicsSimulations
l Landing footprint– Drag, Trim Lift, Trim angle have large effect– Moment, Damping, and Roll have little or no effect
l Amplitude– Drag, Trim Lift, Trim angle have little effect– Moment has little effect– Lift slope has small effect– Roll and damping coefficient have large effect
l If effective damping, K, used, position and angularmotion largely independent of each other
K = 1CD
−CLα + lσ
2Cmq + Cm ˙ α ( )
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Effects of NonlinearAerodynamics on Trajectory
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Nonlinear Aerodynamics Simulations
l Density profiles, gravitational forcesidentical to those used in linearsimulations
l Vehicle specifications identical to thoseused in linear simulations
l Shallow entry for better demonstration ofeffects
l Nonlinearities consistent with observedfor planetary entry vehicles
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Drag Coefficient (CD = 1.5 - 2 sin2σ)Dynamic Pressure, MachLongitude
Total Angle
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Damping Parameter (Cmq + Cmα = 1.5 eAsin2σ - 0.5 )Amplitude Dynamic Pressure
Longitude
Difference in small angle limitmay be due to modeltumbling and resulting errors
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Summary of NonlinearAerodynamics Simulations
l Landing footprint– Nonlinear drag has effect
– Nonlinear moment, lift effect trim angle and trim lift;therefore they will have an effect
l Amplitude– Nonlinear damping coefficients have significant
impact on amplitude
– Impact of other terms small compared to nonlineardamping coefficient
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Impact of Accurate AerodynamicInformation
l Reduce risks– Parachute deployment
– TPS
l Improve landing precision– Minimize foot print
l Expand landing alternatives
l Reduce control propellant mass margin
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lGeneral Description of PlanetaryEntry
lDemonstrate role of aerodynamicson planetary entry
lReview sources of aerodynamicinformation
lReview status of aerodynamics ofplanetary entry shapes
Objectives
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Aerodynamic Information
l Effects of uncertainties and nonlinearitiesin aerodynamic coefficients demonstrated
l Sources
– Types
– Availability
– Accuracy
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Sources of AerodynamicInformation
l Theories
l Computational Fluid Dynamics – CFD
l Ground based experiments
– Wind tunnels
– Ballistic ranges
l Flight tests
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Theories
l Inexpensive
l Limited to high Mach number
l Poorly known and not understood
l Useful in some cases for quick estimatesand trends
l Not validated in all cases
l Examples– Free molecular– Newtonian
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CFD
l For simple configurations provides goodresults for static aerodynamics
l Not thoroughly validated
l Not readily used by non-expert
l Dynamic parameters untried and could beexpensive
l Examples:– Euler - Inviscid– Navier Stokes - Viscid– Navier Stokes - Real Gas
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Ground Based Experiments
lWind tunnels
– Standard approach
lBallistic ranges
– More versatile
– Under appreciated
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Wind Tunnels
l Many readily available
l No real gas effects
l Wall effects at transonicMach numbers
l Sting effects in lowsupersonic / transonicMach range
l Dynamic testingdifficult / expensive
StingM
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Ballistic Ranges
l Overview given since community is less familiar withthese types of facility
l Experimental approach– Free flying model
– Trajectory measurements obtained from series of orthogonalshadowgraphs taken at known times
l Facility– Range & Launcher
• Small model in sabot• Wide range of Mach, Reynolds numbers• Various gases, real gas effects
– 6 DOF, nonlinear data analysis
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NASA Ames HFFAFModel Assortment
Test section interiorTest section exterior andshadowgraph film planesLight-gas gun
Images courtesy of NASA Ames Research Center
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Eglin AFB’s ARF
Schematic of the AeroballisticResearch Facility
Interior
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Ballistic Range Data
-0.25
-0.20
-0.15
-0.10
-0.05
0.00
0.05
0.10
0.15
0.20
0.25
0.00 0.05 0.10 0.15 0.20 0.25 0.30
time
Calculated, 1 Calculated, 2Measured, 1 Measured, 2
0
10
20
30
40
50
60
70
80
90
100
0.00 0.05 0.10 0.15 0.20 0.25 0.30time
Calculated, zCalculated, yMeasured, zMeasured, y
SampleShadowgraph Projected angular and swerve motion
Data from Eglin AFBAerodynamic Research Facility
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Modern 6-DOF Analysis ofBallistic Range Data
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Parameter Estimationl Coefficients found by fitting
calculated trajectories toexperimental measurements
l Trajectory defined by 12, firstorder, coupled, nonlineardifferential equations in threecoordinate systems
l Unknown parameters: nonlinearaerodynamic coefficient termsand initial conditions
l Differentiating equations ofmotion with respect to unknownsprovide method for estimatingcorrections
l Trajectory calculated, correctionsto unknowns estimated, trajectoryre-calculated. Process repeateduntil convergence criteria met
l Single / multi fits
l Error estimates available
Drag: ˙ V = − ρAV2
2m CD − gsinθw
˙ x E = V cosθw cos ψw
Rolling Moment: ˙ p = ρAlV2
2IzCp + Izx
Iz˙ r + pq( ) +
Iy − Iz( )Iz
rp˙ φ w= pw + qw sinφw + rw cos φw( ) tanθw
Pitching, yawing ˙ α = q − qw sec β − p cosα +r sin α( ) tanβmoment: ˙ β = rw secβ + p sinα − rcos α
˙ q = ρAlV2
2IyCM + Izx
Iyr2 − p2( ) +
Iz −Ix( )Iy
rp
˙ r = ρAlV2
2IzCN + Izx
Iz˙ p − qr( ) +
Ix − Iy( )Iz
pq
Lift: ˙ y E = V cos θw sin ψw
˙ z E = −V sin θw˙ θ w= qw cos φw − rw sin φw˙ ψ w= qw sinφw + rw cos φw( ) sec θw
where qw = ρAV2m CL − g cosθw cos φw
rw = − ρAV2m CY + gcosθw sin φw
pw = p cosα + r sin α( ) cosβ + q − ˙ α ( ) sinβ
Equations (6-DOF)
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Parameter Identification - Example
-0.40
-0.20
0.00
0.20
0.40
0.00 0.05 0.10 0.15 0.20 0.25 0.30
20
30
40
50
60
0.00 0.05 0.10 0.15 0.20 0.25 0.30
-500
-400
-300
-200
-100
0
100
0.00 0.05 0.10 0.15 0.20 0.25 0.30
Direction sines vs. time
Swerve vs time
Down range distance vs time
CD = CD0 +CD1 + CD3 + CD4 M − 1( )[ ]sin2 α
1 + CD2(M − 1)2
M − 1( )
CL = CL1 +CL2 sin2 α
1 + CL3 sin2 α
sinα
Cm = Cm1 + Cm2 M − 2.5( ) +Cm3 sin2 α
1 + Cm4 sin2 α
sinα
Cmq = Cmq,0 + Cmq,1
exp −Cmq,2 MCmq,3 s in2 α
1 + Cmq,4 M − 1( )[ ]6
Coefficient Expansions
Moment
Damping
Lift
Drag
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Sample Ballistic Range Results (MER)
CD = CD0 +CD1 + CD3 + CD4 M − 1( )[ ]sin2 α
1 + CD2(M − 1)2
M − 1( )
c.g. CD0 CD1 CD2 CD3 CD4 x rms (ft)
0.27D 1.327 0.641 8.31 -1.369 -1.92 0.0234± 0.005 0.028 0.40 0.055 0.06
Resultsc.g. CL1 CL2 CL3 y, z rms (ft)
0.27D -1.650 75.02 142.6 0.008± fixed 3.40 fixed
Results
Drag Lift
CL = CL1 +CL2 sin2 α
1 + CL3 sin2 α
sinα
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Sample Ballistic Range Results (MER)
Moment Damping
Cm = Cm1 + Cm2 M − 2.5( ) +Cm3 sin2 α
1 + Cm4 sin2 α
sinα
c.g. Cm1 Cm2 Cm3 Cm4 α rms (°)
0.27D -0.1049 0.00000 0.95 160.6 1.36± fixed fixed 0.02 fixed
Resultsc.g. Cmq,0 Cmq,1 Cmq,2 Cmq,3 Cmq,4 α rms (°)
0.27D -0.298 1.177 5.73 4.37 0.40 1.32fixed 0.123 2.77 0.56 fixed
Results
Cmq = Cmq,0 + Cmq,1
exp −Cmq,2 MCmq,3 s in2 α
1 + Cmq,4 M − 1( )[ ]6
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Other Applications of Modern6-DOF Analysis Tools
l Vertical Wind Tunnel
l Flight Tests
– Helicopter Drop Tests
– Atmospheric Entry
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Flight Tests
l Expensive
l Can be dangerous for lifting bodies
l Time consuming
l Data acquisition difficult
l Analysis subject to unknowns– Winds
– Atmospheric properties
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Summary of Data Sourcesl Theory
– Limited
l CFD– Good capability– Validation required in some areas– Need to develop capability for damping
l Ground based testing– Wind tunnels - good static aerodynamics but limited in
damping, real gas– Ballistic ranges - good static and dynamic aerodynamics
for wide range of conditions but model size limited andno onboard instrumentation
l Flight testing– Expensive– Unknown or variable atmospheric conditions
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lGeneral Description of PlanetaryEntry
lDemonstrate role of aerodynamicson planetary entry
lReview sources of aerodynamicinformation
lReview status of aerodynamics ofplanetary entry shapes
Objectives
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Aerodynamicsby Flight Regime
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Flight Regimes
l Free molecular
l Transition
l Continuum
– Entry• Hypersonic
– After maximum dynamicpressure
• Supersonic
• Transonic
• Subsonic
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l Knudsen number:
l Theory – Free molecular flow
l Direct Monte Carlo simulation – DMS
l Ground base facilities non-existent
l Accuracy not critical in many cases
Free Molecular Regime
Kn = λ d > o(1)
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Free Molecular Flow
l Molecules hit surface and are reflected ina specular or diffuse manner with nocollisions
l Example-Sharp cones
– Specular reflection
– No reflection
l Type of reflection depends on surface
CD0= 4sin2 θ
CD0= 2s in2 θ
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l Knudsen number:
l Direct Monte Carlo simulations-DMS
l Low Reynolds number CFD
l Empirical bridging functions
l Experimental facilities non-existent
Transition
Kn = λ d ≅ o(1)
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l Knudsen number:
l Mach number:
l Theory– Newtonian
• Normal component of momentum converted to pressure• Mach number independent• Capable of calculating both static and dynamic coefficients
l CFD
l Ground based experiments– Wind tunnel
– Ballistic range
Continuum Entry-Hypersonic
Kn = λ d << o(1)
M = V a > 5
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Examples ofHypersonic
Aerodynamics
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Drag and Lift on Simple Shapes(Mach > 5)
0
0.5
1
1.5
2
2.5
3
0 20 40 60 80
Newtonian, Rn/Rb = 0.0Newtonian, Rn/Rb = 0.6Newtonian, Rn/Rb = 0.95Conical Flow TheoryBlunt Cone DataSharp Cone Data
CD
0
Cone Angle
-1.5
-1
-0.5
0
0.5
1
1.5
2
0 0.5 1 1.5 2
Newtonian TheoryConical Flow TheoryBlunt Cone Data
CLα
CD 0
Lift: CLα = CPmax - 2CDDrag
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Center of Pressure (Mach > 5)
-2
-1
0
1
2
3
4
0 20 40 60 80
Sharp ConeSphere SegmentBlunt Cone
xC
p / r b
Cone Half Angle
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Dynamic Stability
For Sharp Cones
where
Based on reference length l and l /V (not l / 2V )
Cmqx= Cmq0
+ CNq0
xl
− Cmα0
xl
− CNα0
xl
2
Cm ˙ α x≡ 0
(plunging motion)
Cmq0= − 1 + tan2 θ( ), Cmα0
= −4 / 3
CNα0= 2
1 + tan2 θ, CNq0
= +4 / 3
Cmqx< 0 for large cone angles
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Ballistic Range DataMars Smart Lander, Axisymmetric Configuration
(CO2, M ≈ 18, NASA Ames Research Center)
1.0
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
0 5 10 15α
Single FitsMulti Fit
-0.040
-0.035
-0.030
-0.025
-0.020
-0.015
-0.010
-0.005
0.0000 5 10 15
α
Single FitsMulti Fit
-0.50
-0.45
-0.40
-0.35
-0.30
-0.25
-0.20
-0.15
-0.10
-0.05
0.000 5 10 15
RMS Pitch Angle
Single FitsMulti Fit
-0.40
-0.35
-0.30
-0.25
-0.20
-0.15
-0.10
-0.05
0.000 5 10 15
RMS Pitch Angle
Single FitsMulti Fit
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AerospaceComputing, Inc.
Supersonic/Transonic
l Mach number:
l No theories for blunt bodies
l CFD– Used extensively
– Not used for dynamics, could be expensive
l Ground based experimental– Wind tunnel
– Ballistic range
5 > M > 0.6
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Examples ofSupersonic/Transonic
Aerodynamics
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Available Data Sets
l Pre 1975– Early research
– PAET /Voyager/Viking
l Post 1985– Huygens Probe
– Stardust
– DS-2
– Genesis
– MER
– Mars Smart Lander
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Stardust Ballistic Range Data (Air, Mach ≈ 2)
Axial Force vs Angle of Attack
1.0
1.1
1.2
1.3
1.4
1.5
1.6
0 5 10 15
Axi
al F
orce
Coe
ff, C
X
Ames (Re_d =1.55e+06)Eglin (CG = 0.35),Re_d = 3.10e+06
Damping Moment vs Angle of Attack
-1.50
-1.00
-0.50
0.00
0.50
0 5 10 15
Angle of Attack, Deg
Dam
ping
Coe
ff, C
mq
Ames (Re_d = 1.55e+06)
Eglin (CG=0.35), Re_d =3.10e+06Eglin Error Bound
Error Bound
Pitching Moment vs Angle of Attack
-0.040-0.035-0.030-0.025-0.020-0.015-0.010-0.0050.000
0 5 10 15
Angle of Attack, Deg
Ames (Re_d =1.55e=06)Eglin (CG=0.35),Re_d = 3.10e+6
Normal Force vs Angle of Attack
00.010.020.030.040.050.060.070.08
0 5 10 15
Nor
mal
For
ce C
oeff,
CN
Ames (Re_d =1.55e+06)Eglin (CG=0.35,Re_d=3.10e+06)
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Stardust Ballistic Range Data (Air, Mach ≈ 2)
Lift vs Angle of Attack
-0.40-0.35-0.30-0.25-0.20-0.15-0.10-0.050.00
0 5 10 15
Angle of Attack, Deg
Lift
Coe
ff, C
L
Nom. Re_d=1.55e+06
Nom. Re=0.27e+06
Pitching Moment vs Angle of Attack
-0.035
-0.030
-0.025
-0.020
-0.015
-0.010
-0.005
0.000
0 5 10 15
Angle of Attack, Deg
Pitc
h M
omen
t Coe
ff, C
m
Nom. Re_d=1.55e+06
Nom. Re_d=0.27e+06
Damping vs Angle of Attack
-1.50
-1.00
-0.50
0.00
0.50
0 5 10 15
Angle of Attack, Deg
Dam
ping
Coe
ff, C
mq
Nom. Re_d=1.55e+06
Nom. Re_d=0.27e+06
Drag vs Angle of Attack
1.0
1.1
1.2
1.3
1.4
1.5
1.6
0 5 10 15
Angle of Attack, Deg
Dra
g C
oeff,
CD
Nom. Re_d=1.55e+06
Nom. Re_d=0.27e+06
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Ballistic Range Pitch Damping Data (Air, Mach ≈ 2)
-1
-0.8
-0.6
-0.4
-0.2
0
-20 -15 -10 -5 0 5 10 15 20Angle of Attack, degrees
-0.5
0
0.5
1
1.5
2
2.5
0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 2
4.88° 0.175.55° 0.236.41° 0.337.66° 0.287.69° 0.247.89° 0.368.64° 0.23
9.00° 0.26 9.62° 0.2211.94° 0.4612.66° 0.3714.31° 0.3516.50° 0.1219.50° 0.28
αm Rex10-6 α
m Rex10-6
M∞
Pre 1975
Blunt Probes Linear Results
Post 1985
Huygen’s Probe Noninear Results
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Impact of Afterbody on Dynamics (Air, Mach ≈ 2)
Stardust-TB: Damping vs. Angle of Attack
-0.40
-0.30
-0.20
-0.10
0.00
0.10
0 5 10 15
Angle of Attack, deg
Dam
ping
Coe
ff, C
mq
Stardust-TB
Stardust-RB
Stardust-S
TB
RB
S
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
1.0
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
0 5 10 15 20 25 30
P = 110 mmP = 40 mmExperiment
-0.04
-0.03
-0.02
-0.01
0.00
0.01
0.02
0.03
0.04
0.05
0.06
0 5 10 15 20 25 30
P = 110 mmP = 40 mmExperiment
-0.70
-0.60
-0.50
-0.40
-0.30
-0.20
-0.10
0.00
0 5 10 15 20 25 30
RMS Pitch Angle
P = 110 mmP = 40 mmExperiment
-0.5
-0.4
-0.3
-0.2
-0.1
0.0
0 5 10 15 20 25 30
RMS Pitch Angle
P = 110 mmP = 40 mmExperiment
Pre-testCFD
Ballistic Range DataMars Smart Lander, Tabbed Configuration
CO2, Mach = 2.6, NASA Ames Ballistic Range
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Ballistic Range DataMars Smart Lander, Tabbed ConfigurationMach = 2.6, NASA Ames Ballistic Range
PITCH DAMPING
-2.0
-1.5
-1.0
-0.5
0.0
0.5
1.0
1.5
2.0
10 15 20 25
RMS Pitch Angle
M3C, C02
M3C, AIR
M3C, Mix
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Summary of Super/TransonicAerodynamics
l Static aerodynamics– Well understood
l Dynamic aerodynamics– Strong base effects that are not understood
– Potential gas dependence
l Tools– CFD, wind tunnels, and ballistic ranges needed
for high quality data base
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Subsonic Aerodynamics
l Mach number:
l No theories
l CFD– Not used for dynamics, would be expensive
l Ground based experimental– Wind tunnel
• Difficult for dynamics• Sting effects
– Ballistic range• Difficult at low speeds
M < 0.6
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Summary of Aerodynamicsl Free molecular
– Reasonably well understood– Accuracy not critical
l Transition– DMS and low Reynolds number CFD plus bridging
functions give reasonable estimates
l Continuum hypersonic– Statics: well understood– Dynamics: validated theory and CFD required
l Supersonic - Transonic– Statics: reasonably well understood– Dynamics: strong base effect; possible gas effect
l Subsonic– Shortage of data– Required only for missions without drogues / parachutes
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Concluding Remarks
l Aerodynamics plays major role in shapingtrajectory
l Accurate aerodynamics database reduces foot-print size and reduces control fuel mass margins
l Aerodynamic understanding can provide missiondesign flexibility
l CFD, wind tunnels, and ballistic ranges all have arole in database generation
l Today’s project driven environment limitsinnovation and is eroding expertise base
Leslie A. Yates(650) [email protected]
Copyright © 2002 byAerospaceComputing, Inc.
AerospaceComputing, Inc.
Issues and Future Directions
l Loss of expertise– Develop user friendly training tools– Train new personnel
l Database erosion– Develop user friendly tool kits containing database,
theory and simple CFD, and access tools for morecomplicated CFD
l Gaps in aerodynamic database– Pitch damping
• Understand base effects• Determine effect of gas composition• Validate Newtonian Theory• Develop CFD approach / program