Prince William Composite Squadron Col M. T. McNeely
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Prince William Composite Squadron
Col M. T. McNeely
Presentation for AGI Users Conference
CIVIL AIR PATROL PRESENTS
The CAP-STK Aerospace Education Program
INTRO TO SPACE COURSE
…using AGI’s Satellite Tool Kit
Why is this important?
• Intro to Space will enhance CAP Aerospace Education Program
• Broaden cadet’s knowledge of Space and Satellite operations
• Cadet will gain an understanding of a variety of Space fundamentals
• Orbital Mechanics• Types of Orbits • Placing a Satellite in Orbit• Conducting Satellite Operations
• Stimulate interest in the ‘Final Frontier’: THE FUTURE!!
ORBITAL MECHANICSLesson Plan 1 - Part 1
Origins Physical Laws Requirements for Injection Classifications of Orbits Coordinate Reference Systems Orbital Elements
PHYSICAL LAWSKepler’s 2nd Law: Law of Equal Areas
PHYSICAL LAWSKepler’s 2nd Law: Law of Equal Areas
The line joining the planet to the center of the sun sweeps out equal areas in equal times
T6
T5T4 T3
T2T1A2A3A4A5
A6
A1
PHYSICAL LAWSNewton’s 2nd Law: Law of Momentum
Change in momentum is proportional to and in the direction of the force applied
Momentum equals mass x velocity Change in momentum gives: F = ma
F
F
INJECTION REQUIREMENTSSpeed
100 miles
17,500 mi/hr
ORBITAL ELEMENTSKeplerian Elements
Semi-Major Axis (Size) Eccentricity (Shape) Inclination Right Ascension Argument of Perigee Epoch Time (Location within orbit)
– True Anomaly
(Orientation)
ORBIT CLASSIFICATIONShape (Conic Sections)
CircleEllipse
ORBIT CLASSIFICATIONSEccentricity
Eccentricity = c/a
e = 0.75
e = .45
e = 0
ORBITAL ELEMENTSKeplerian Elements: Inclination
Orbital Plane
Equatorial Plane
Inclination ( i )
ORBITAL ELEMENTSKeplerian Elements: Right Ascension
iLine of N
odes
Right Ascension of the Ascending Node ()
First Point of Aries ()
ORBITAL ELEMENTSKeplerian Elements: Argument of Perigee
iLine of N
odes
Argument of Perigee ()
ORBITAL MECHANICSLesson Plan 1 - Part 2
Ground Tracks Perturbations Launch Considerations Orbital Maneuvers De-orbit/Decay
Ground TracksWestward Regression
- Earth rotates east under a satellite => satellite appears to walk west
- Earth rotates 360 degrees in 24 hours (15 degrees per hour)
Ground TracksWestward Regression
0 30-30-60-90-120
ABC
A - time zeroB - after one orbitC - after two orbits
60
Ground tracks Inclination
60
30
0
30
60
45N
45S
Inclination = 45 degrees Eccentricity ~ 0
Ground TracksEccentricity
Ground Track for Molnyia orbit eccentricity = .7252
PERTURBATIONS
Definition– A disturbance in the regular motion of a
satellite Types
– Gravitational– Atmospheric Drag– Third Body Effects– Solar Wind/Radiation Effects– Electro-magnetic
PERTURBATIONSGravitational: Libration
Ellipticity of the Earth causes gravity wells and hills
Stable points: 75E and 105W-- Himalayas and Rocky Mountains
Unstable points: 165E and 5W-- Marshall Islands and Portugal
Drives the requirement for stationkeeping
PERTURBATIONSElectro-Magnetic
Interaction between the Earth’s magnetic field and the satellite’s electro-magnetic field results in magnetic drag
LAUNCH CONSIDERATIONSLaunch Windows
The period of time during which a satellite can be launched directly into a specific orbital plane from a specific launch site
Window duration driven by safety, fuel requirements, desired injection points, etc.
Window is centered around optimal launch time
DE-ORBIT/DECAY
De-Orbit is the controlled re-entry of a satellite to a specific location– Used for the recovery of payload
Manned missions
Decay is uncontrolled re-entry – Potential impact anywhere along ground
track– Re-entry Assessment (by Cheyenne Mountain)
TYPES OF ORBITSLesson Plan 2
Types of Satellites and Missions
Satellites vs Orbits
Use STK to Evaluate Orbit Type vs Mission Requirement
TYPES OF ORBITS -Uses of Satellites
Daily Uses of Satellites Big Picture Affects of Altitude
TYPES OF ORBITS -Uses of Satellites
GPS Receiver Used in Search and Rescue Missions
TYPES OF ORBITS
LEO MEO HEO GEO
PLACING A SATELLITE IN ORBITLesson Plan 3
How Satellites are Launched
Location Advantages of Two Primary Launch Sites
Purpose of a Hohmann Transfer
Use STK to Demonstrate Concepts
PLACING SATELLITES IN ORBIT
Booster Types
DELTA II
PLACING SATELLITES IN ORBIT
Booster Types
ATLAS 2AS
PLACING SATELLITES IN ORBIT
Booster Types
TITAN IV
PLACING SATELLITES IN ORBIT
Booster Types
TAURUS
PLACING SATELLITES IN ORBIT Booster Types
TheSHUTTLEBOOSTER
PLACING SATELLITES IN ORBIT
Booster Types
PEGASUS
PLACING SATELLITES IN ORBIT Launch Constraints
CONDUCTING SATELLITE OPERATIONSLesson Plan 4
Basic Elements of a Space System
Space System Functions
Access
STK Demonstrations
SATELLITE OPERATIONSFUNCTIONS
GPS Example
EXERCISESLesson Plan 5
Apply Knowledge Concepts to Problems and Formulate Solutions
Demonstrate with STK
INTRO TO SPACESUMMARY
Classroom Presentations
using Powerpoint
Demonstrate with STK
Let’s Demo !!
The world of Space Operations awaits you!!
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