the neutral atmosphere and its influence on basic orbital dynamics at the edge of space
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The Neutral Atmosphere and Its Influence on Basic Orbital Dynamics at the Edge of Space. Delores Knipp Department of Physics US Air Force Academy Colorado USA [email protected]. Developed by members of the Department of Physics, USAFA - PowerPoint PPT PresentationTRANSCRIPT
The Neutral Atmosphere and Its Influence on Basic Orbital Dynamics at the Edge of Space
Delores KnippDepartment of PhysicsUS Air Force Academy
Colorado [email protected]
Developed by members of the Department of Physics, USAFA
Special credit to Dr Evelyn Patterson USAFA and
Dr Esther Zirbel, Yale University
Lt Omar Nava, Naval Post Graduate School
Introduction: Neutral Atmosphere & Orbital Dynamics
• Motivation
• Concepts
– Solar Cycle-Atmosphere Interaction
– Atmospheric Density and Temperature
– Mechanics/Dynamics of Drag
– Computational Concepts
• “What Ifs”
• Tomorrow
– Simulation
Objectives:
Understand sources of upper atmospheric heating
Appreciate the space weather regime- change from magnetized and non-collisional to gravitationally dominated and collisional interactions.
Determine the effects of neutral atmospheric drag on the motion of satellites that are in low enough orbits to be affected by the Earth’s atmosphere
Explore effects of time varying atmospheric temperature and density
Space Weather EffectsSpace Weather Effects
The effects of solar and magnetic storms—what scientists call space weather—extend from beyond Earth-orbit (BEO) to geostationary orbit (GEO) to the ground (Courtesy: L Lanzerotti)
MOTIVATION
•Track and identify active payloads and debris (DOD)•Collision avoidance and re-entry prediction (NASA) •Study the atmosphere’s density and temperature profile (Science)
Skylab, 1978
April 9, 1979
Impacts of the Variable Sun
As the Sun’s activity increases during the solar cycle the Earth’s upper atmosphere heats up and heaves up
Are Sunspots Related to Satellite Drag?
Sunspots Up Close
Courtesy La Palma Telescope
How can a Sun with more Spots be Hotter/Brighter?
Courtesy of Robert Cahalan, NASA
Where Does Energy Enter the Upper Atmosphere?
Dayside:
Solar EUV
and
Auroral particles
Nightside:
Joule Dissipation
and
Auroral Particles
After Killeen et al., 1988
The Solar Spectrum
(Courtesy S Solomon)
Courtesy of Judith Lean
Geomagnetic Activity Plays a Role in Upper Atmospheric Heating
Courtesy of US Air Force
Altitude-Time Profile for a Spherical Satellite
Observed and Simulated STARSHINE-1 Altitude Vs Time
120
160
200
240
280
320
360
400
0 20 40 60 80 100 120 140 160 180 200 220 240 260 280
Time (Days)
Alt
itu
de
(km
)
Thin curve Simulated STARSHINE orbits Thick curve actual STARSHINE data
Vertical Forces on a Static Parcel of Air
• Weight = mgn(Vol)– m = average mass of air in amu– g = local gravitational acceleration– n = number density of gas molecules (#/Vol)– Vol = volume = dz * A
• dP – Change in pressure (decreases upwards)
• A– Area of horizontal surface
• P = nkT– T = temperature in °K– k = Boltzmann constant (=1.38x10-23 J/°K)
z
z+dz
Fup=PA
Fdown=(P+dP)A
Weight
Fnet = Fup-Fdown-Weight=0
PA-(P+dP)A = Weight
-dP A = Weight
A=area
z
More realistic Pressure-Height Variation
-dP A = Weight
-dP A = mgn dz A
dP =d(nkT)= -mgn dz
kT (dn) = - mgn dz
dn/n=-mgdz/kT
nz/n0=exp(-mgdz/kT)
mnz/mn0=exp(-mgdz/kT)
z/ 0=exp(-mgdz/kT)
Atmospheric Concepts• Need to know about the atmosphere in which satellites are orbiting. • The simple law of atmospheres states that, close to the earth's surface, the
atmospheric density decreases exponentially with elevation.
(z) = 0exp(-mgz/kT)
• This expression assumes that the acceleration due to gravity g, the temperature T, and the mean gas molecule mass, m, remain constant.
Altitude vs. Atmospheric Mass Density, Simple Law of Atmospheres
0
200
400
600
800
1000
1200
1.000E-17 1.000E-14 1.000E-11 1.000E-08 1.000E-05 1.000E-02 1.000E+01
Atmospheric Mass Density (kg/m3)
Alt
itu
de
(km
)
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MaAdPPWPA
r
mnAdyGM
r
mnVGM
r
mNGM
r
GMWeight
MaF
E
E
mCorrecting for variations in “g”
Concept: What if “g” Varies?
MSIS Atmosphere
Altitude vs. Atmospheric Mass Density, Comparing Different Models
0
200
400
600
800
1000
1200
1E-17 1E-14 1E-11 0.00000001 0.00001 0.01 10
Atmospheric Mass Density (kg/m3)
Alt
itu
de
(km
)
Law of Atm, Corrected "g"
Law of Atm
Concept: What if the Temperature Varies?
Altitude vs. Temperature in the Atmosphere
0
200
400
600
800
1000
1200
0.0 100.0 200.0 300.0 400.0 500.0 600.0 700.0 800.0 900.0 1000.0 1100.0 1200.0
Atmospheric Temperature (K)
Alt
itu
de
(km
)
MSIS Atmosphere
Concept Check
The figure on the right shows the altitude versus atmospheric mass density curves for three different temperatures. Which of the following is the correct ranking, from lowest temperature to highest temperature, for the three curves shown?
a) A, B, C b) C, B, A c) B, C, A d) A, C, B
Altitude vs. Atmospheric Mass Density, Comparing Different Models
0
200
400
600
800
1000
1200
1.0E-14 1.0E-11 1.0E-08 1.0E-05 1.0E-02 1.0E+01 1.0E+04
Atmospheric Mass Density (kg/m3)
Alt
itu
de
(km
)
Law of Atmospheres
MSIS Model Hot
Temperature K
Troposphere
Stratosphere
Thermosphere
MSIS Model Cool
a b
TIEGCM Density Profile
MSIS Hot
MSIS Cool
Mechanics Concepts Kinetic Energy
• Satellites in orbit experience a centripetal acceleration
• Solve for speed
• Associated kinetic energy
rr
GMmr
r
mvamF ˆˆ
2
2
r
GMv
r
mGMmv
22
1 2
Mechanics Concepts Potential and Total Energy
• Potential Energy
Significance of “-” sign?
• Total Mechanical Energy
• Solve for Altitude
• Total Mechanical Energy is constant unless non-conservative forces act
r
GMmrdFU
B
A
AB
r
GMm
r
mGMmvE
22
1 2
hRE
GMmr E
2
Mechanics Concepts Drag Force and Work
• Drag Force
• Work Done by Drag
2
2
1|| vACF DD
lvACrdFW D
B
A
2
2
1
Assumptions
• Circular orbit
• No change in orbital parameters during the satellite period
• Satellite does not tumble (A and Cd constant)
• Atmosphere
– Law of Atmospheres
– MSIS Atmosphere—temperature and density
• No seasonal, day/night or spatial variations in the atmospheric density
Iterative Techniques and Formulation and Graphics Concepts
Work Done by
Drag Force
Boundary Conditions and Initial Physics
Reduced Mechanical
Energy
New Conditions And
Same Physics
More Work Done by Drag Force
Satellite De-Orbits
Iterate
Newton’s Second Law
Energy Conservation
Newton’s Second Law
Energy Conservation…Etc
Orbital Drag Laboratory Worksheet Flowchart of Orbit Decay Model:
Initial values
Energy at this
altitude
Altitude
Speed
Atmospheric density at this
altitude
Drag Force Work done
by drag force in this orbit
Next values
Energy at the next
orbit
Altitude
Speed
Atmospheric density at this
altitude Drag Force Work done
by drag force in this orbit
(from Atmosphere spreadsheet) = 4.25x10-11
kg/m3
Iterative Technique
Orbital Drag Lab: Modeling Satellite Orbital Decay in a Realistic Atmosphere
m, Mass of Shuttle (kg) = 91974 G, Gravitational Constant (Nm2/kg2) = 6.67E-11
CD, Drag Coefficient = 2 M, Mass of Earth (kg) = 5.97E+24
A, Cross Sectional Area of Shuttle(m2)= 362 Re, Radius of Earth (m) = 6.37E+06
hi, Initial Altitude (km) = 350 350000 = hi in meters
End of
Orbit
Total Time
Mass DensityShuttle's Total
Energy (J)Altitude
(km)Altitude (m) Velocity (m/s) Drag (N)
Work Due To Drag (J)
# (hours) (kg/m3)0.00 4.25E-11 -2.72500E+12 350.0 350000.0 7697.8 0.91 -3.85E+07 Initial
1 1.52 4.32E-11 -2.72504E+12 349.9 349905.2 7697.8 0.93 -3.92E+07 Typical2 3.05 4.32E-11 -2.72507E+12 349.8 349808.6 7697.9 0.93 -3.92E+07
529 797.86 1.18E-07 -2.82766E+12 106.0 106026.2 7841.4 2,618.47 -1.07E+11530 799.30 #N/A -2.93420E+12 -129.1 -129129.3 7987.8 #N/A #N/A
Iterative Technique
Shuttle's Altitude vs. Time
0
50
100
150
200
250
300
350
400
0 100 200 300 400 500 600 700 800 900
Time (hours)
Shuttle's Drag vs. Time
0
1
10
100
1,000
10,000
0 100 200 300 400 500 600 700 800 900
Time (hours)
Concept Check
In a subsequent orbit, after work has been done by the drag force, the satellite would have
a) less kinetic energy and less potential energy
b) more kinetic energy and less potential energy
c) less kinetic energy and more potential energy
Shuttle's Speed vs. Time
7650
7700
7750
7800
7850
7900
7950
8000
8050
0 100 200 300 400 500 600 700 800 900
Time (hours)
Ve
loc
ity
(m
/s)
Shuttle's Total Mechanical Energy vs. Time
-2.95000E+12
-2.90000E+12
-2.85000E+12
-2.80000E+12
-2.75000E+12
-2.70000E+120 100 200 300 400 500 600 700 800 900
Time (hours)
Concept Check
A satellite orbiting in a dense atmosphere will (at next orbit) be
a) at lower altitude and ahead of schedule
b) at higher altitude and ahead of schedule
c) at lower altitude and behind schedule
d) at higher altitude and behind schedule
Radar
Receiver
Atmospheric Drag
EXPECTED POSITION
ACTUAL POSITION
Time-Varying Activity
Heating Activity Level vs. Time
0
1
2
3
4
0 100 200 300 400 500 600 700 800 900 1000 1100
Time (hours)
He
ati
ng
Ac
tiv
ity
Le
ve
l (0
, 1
, 2
, o
r 3
)
Shuttle's Altitude vs. Time
0.0
50.0
100.0
150.0
200.0
250.0
300.0
350.0
400.0
0.00 50.00 100.00 150.00 200.00 250.00
Time (hours)
Alt
itu
de
(km
)
Shuttle's Drag vs. Time
0.10
1.00
10.00
100.00
1,000.00
10,000.00
0.00 50.00 100.00 150.00 200.00 250.00
Time (hours)
Dra
g (
N)
The Atmosphere can have Significant Temporal and Spatial Variability in Temperature and Density
Location of heating associated with low energy particles bombarding the nightside auroral zone
Solar EUV and Particle Power
Daily Average Solar and Particle Power Values for Solar Cycles 21-23
0
500
1000
1500
2000
2500
1975 1977 1979 1981 1983 1985 1987 1989 1991 1993 1995 1997 1999 2001 2003 2005
Year
Po
wer
(G
W)
Solar Power
Cycle 21 Cycle 22 Cycle 23
Particle Power
Joule Power –Two Hemispheres
Daily Average Joule Power Values for Solar Cycles 21-23
0
500
1000
1500
2000
2500
1975 1977 1979 1981 1983 1985 1987 1989 1991 1993 1995 1997 1999 2001 2003 2005
Year
Po
wer
(G
W)
10 Most Powerful Events of Last 30 Years(Knipp et al., 2005)
Daily Average Power Values for Solar Cycles 21-23
0
500
1000
1500
2000
2500
3000
3500
1973 1975 1977 1979 1981 1983 1985 1987 1989 1991 1993 1995 1997 1999 2001 2003 2005
Year
Po
wer
(G
W)
Total Power
Joule Power
Solar Power
SKYLAB Reenters
NORAD Space TrackingDisrupted
JapaneseSatelliteMalfunctionAttributedto Satellite Drag
Particle Power
15 Apr 7 Jul 3 Mar 10 Oct 6 Jun 5 May 15&16 Jul 6 Nov 30 Oct
79 82 89 89 91 92 00 01 03
Altitude Profile
nominal
Level 3 disturbance at hr 100 for 10 hr
Return to nominalLevel 2Disturbance
All Hours
Altitude Speed
Mechanical Energy Drag Force
Orbital Drag Lab: Boundary Values for Space Shuttle Orbit
m, Mass of Shuttle (kg) = 91974CD, Drag Coefficient = 2
A, Cross Sectional Area of Shuttle(m2)= 362hi, Initial Altitude (km) = 350
G, Gravitational Constant (Nm2/kg2) = 6.67E-11
M, Mass of Earth (kg) = 5.97E+24
Re, Radius of Earth (m) = 6.37E+06
Ideal and model atmospheres
Altitude vs. Atmospheric Mass Density, Comparing Different Models
0
200
400
600
800
1000
1200
1.000E-17 1.000E-14 1.000E-11 1.000E-08 1.000E-05 1.000E-02 1.000E+01
Atmospheric Mass Density (kg/m3)
Alt
itu
de
(km
)
MSIS Model (T + 20%)
MSIS Model (T + 10%)
MSIS Model (T + 5%)
MSIS Model (Std. Temp)
Law of Atm, Corrected "g" & T
Law of Atm, Corrected "g"
Law of Atm
Initial values
Energy at this
altitude
Altitude
Speed
Atmospheric density at this
altitude
Drag Force
Next values
Energy at the next
orbit
Altitude
Speed
Atmospheric density at this
altitude Drag Force
NAME ________KEY_______ SECTION___________________
J
r
GMmE
1210x725.2
2
mh 000,350
(from Atmosphere spreadsheet)
= 4.25x10-11 kg/m3
m/s8.7697
hR
GM
r
GMv
E
(from Atmosphere spreadsheet)
= 4.32x10-11 kg/m3
m/s8.7697
hR
GM
r
GMv
E
J
WEE lastlastthis
1210x725.2
N
vACF DD
91.021 2
J
hRF
rFW
ED
DD
710x85.3
])[2(*
)2(*
J
hRF
rFW
ED
DD
710x92.3
])[2(*
)2(*
m
ERE
GMmh
E
GMmhERr
r
GMmE
3499052
2
2
N
vACF DD
93.02
1 2
Iterative Technique
Plot characteristics of satellites (in near circular orbit) under the influence of drag
Shuttle's Altitude vs. Time
0.0
50.0
100.0
150.0
200.0
250.0
300.0
350.0
400.0
0.00 100.00 200.00 300.00 400.00 500.00 600.00 700.00 800.00 900.00
Time (hours)
Alt
itu
de
(km
)
Shuttle's Velocity vs. Time
7650.0
7700.0
7750.0
7800.0
7850.0
7900.0
7950.0
8000.0
8050.0
0.00 100.00 200.00 300.00 400.00 500.00 600.00 700.00 800.00 900.00
Time (hours)
Vel
oci
ty (
m/s
)
Shuttle's Total Mechanical Energy vs. Time
-2.74200E+12
-2.74000E+12
-2.73800E+12
-2.73600E+12
-2.73400E+12
-2.73200E+12
-2.73000E+12
-2.72800E+12
-2.72600E+12
-2.72400E+12
0.00 50.00 100.00 150.00 200.00 250.00 300.00 350.00 400.00 450.00 500.00
Time (hours)
To
tal
Mec
han
ical
En
erg
y (J
)
Shuttle's Drag vs. Time
0.10
1.00
10.00
100.00
1,000.00
10,000.00
0.00 100.00 200.00 300.00 400.00 500.00 600.00 700.00 800.00 900.00
Time (hours)
Dra
g (
N)
Altitude
Mechanical Energy
Velocity
Drag Force
Are Lab Results Realistic?
Observed and Simulated STARSHINE-1 Altitude Vs Time
120
160
200
240
280
320
360
400
0 20 40 60 80 100 120 140 160 180 200 220 240 260 280
Time (Days)
Alt
itu
de
(km
)
Thin curve Simulated STARSHINE orbits with MSIS temperature-6%Thick curve actual STARSHINE data
Concept: Temporal Variations in Heating
Shuttle's Altitude vs. Time
0.0
50.0
100.0
150.0
200.0
250.0
300.0
350.0
400.0
0.00 100.00 200.00 300.00 400.00 500.00 600.00 700.00 800.00 900.00
Time (hours)
Alt
itu
de
(km
)
Level 0 Activity Orbital Decay
Level 1 Activity Orbital Decay
Level 2 Activity Orbital Decay
Level 3 Activity Orbital Decay
Shuttle's Altitude vs. Time
0.0
50.0
100.0
150.0
200.0
250.0
300.0
350.0
400.0
0.00 50.00 100.00 150.00 200.00 250.00
Time (hours)
Alt
itu
de
(km
)
Solar Activity Level vs. Time
0
1
2
3
4
0 100 200 300 400 500 600 700 800 900 1000 1100
Time (hours)
So
lar
Act
ivit
y L
evel
(0,
1,
2, o
r 3)
Altitude vs Time Profiles for 0,5,10 and 20%
Temperature Increases
Impulsive heating event
Sources of Temporal Variations
• Solar Cycle variations (Proxy F10.7 cm index)
• Day to Day solar variations (Solar Flare) (Proxy F10.7 cm index)
– Minimal effects except in most extreme cases
– Short-lived• Daily Geomagnetic Heating
Variations (Magnetic Storm) (Ap Index)
– Maybe long lived if under certain solar wind conditions
• Shock followed by Mass Ejection followed by High Speed Stream
Daily Average Power Values for Solar Cycles 21-23
0
500
1000
1500
2000
2500
3000
3500
1974 1976 1978 1980 1982 1984 1986 1988 1990 1992 1994 1996 1998 2000 2002 2004
Year
Po
wer
(G
W)
Jul 14 Mar 13 Oct 21 Jun 6 Jul 13 May 10 Jul 14 Mar 31 Nov 6 & 24 1982 1989 1989 1991 1991 1992 2000 2001 2001
Solar Power
Total Power
Joule Power
Particle Power
Concept: What if the Temperature Varies?
Shuttle's Altitude vs. Time
0
50
100
150
200
250
300
350
400
0 100 200 300 400 500 600 700 800 900
Time (hours)
Alt
itu
de
(km
)
7650
7700
7750
7800
7850
7900
7950
8000
8050
Altitude Profile Using Hot ModelAtmosphere
Altitude Profile Using Hot ModelAtmosphere +5%
Velocity Profile Using Hot ModelAtmosphere
Velocity Profile Using Hot ModelAtmosphere +5%
Solar Spectrum