Present:. Sea Launch/ Zenit Thrust: 8,180,000 N Fueled Weight: 450,000 kg Payload to LEO: 13,740 kg Cost per launch: $100,000,000 Cost per kg: $7,300 Launches: 31/28. Gateway To Space ASEN 1400 / ASTR 2500 Class #20. T 30. Colorado Space Grant Consortium. Today:. Announcements
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Sea Launch/Zenit
Thrust: 8,180,000 N
Fueled Weight: 450,000 kg
Payload to LEO: 13,740 kg
Cost per launch: $100,000,000
Cost per kg: $7,300
Launches: 31/28
pCDR peer reviews…
 3rd place is Team #5
 2nd place is Team #7
 1st place is Team #4
DD Rev A/B Grades
HW #8 Due 4:00 PM November 9th
Office Hours and Questions in Class
Mid Semester Team Evaluations…
Please pass them forward now
New grades posted next Tuesday
Community Service project will be included
Geostationary VS. Geosynchronous
 What types of orbits do they do around other planets?
 Is there a polar orbit that is also geosynchronous?
 Could spacecraft ever be launched from Colorado?
 How do you get on elliptical orbit?
 What is the advantage of elliptical orbit vs. a circular orbit around the Earth?
 Does the angle at which you launch a satellite affect its eccentricity?
 How many different orbits are there?
 Do you have launch a satellite at an angle to get it into orbit or can you shoot it straight up?
 Who owns the geosync orbit space?
UN through the International Telecommunications Union
 When is our Movie Night?
 What is the amount of time between turning on the Sat at launch?
 Do you have to write a journal about every chapter?
 How will the inclass simulation work?
 Do we need to have all the satellite building and testing done before the inclass simulation?
 What chances do students have to go to those big conferences?

 Where does Tom Kelly work now?
 What is an acoustic test?
 Are vibration tests done with mass models or the actual products?
 Did they use Velcro on floor to keep them in place?
 Has an emergency ever occurred on an EVA?
 Is Grumman still making space vehicles?
 Arduino is beginning to look like a next of wires?
 Why is water blue?
 Why is this class so awesome?
 What is the craziest thing I ever did…
A Brief Historical Look
Earth, the Moon, Mars, and the Stars Beyond
A Brief Discussion on Mission Design
Universal Gravitation, Applied:
Kepler’s Laws...Orbits described by conic sections
Velocity of an orbit described by following equation
For a circle (a=r):
For a ellipse (a>0):
For a parabola (a=):
Earth, the Moon, Mars, and the Stars Beyond
A Brief Discussion on Mission Design
Velocity & Position
 Given position and velocity of a satellite at
time t, you can calculate the position and
velocity at any other time
Keplerian Elements
 Right Ascension of Ascending Node (RAAN, Ω)
 Rotation about the Earth’s Spin Axis
Keplerian Elements
 Argument of Perigee (ω)
 Rotation of the conic section in the plane
Keplerian Elements
 True Anomaly (θ)
 Defines the position of a body in orbit
 Angle between the Position Vector and
the vector to Perigee
 Elliptical only
Orbital Period
Changing orbits usually involves an elliptical orbit or Transfer Orbit
Perigee = close
Apogee = far
1) Velocity of initial orbit
2) Velocity of final orbit
3) Velocity at perigee 4) Velocity at apogee
1) Velocity of initial orbit
2) Velocity of final orbit
3) Velocity at perigee 4) Velocity at apogee
DV2is to circularize orbit
What if we did the whole thing in reverse?
Go from 500 to 250 km?
What happens to the answer?
1) Velocity of initial orbit
2) Velocity of final orbit
3) Velocity at perigee 4) Velocity at apogee
DV2is to circularize orbit
Time to do transfer is the same
Also something called
“Fast Transfer”
• It is more direct and quicker
• However it takes more fuel
• DV1 and DV2 are much bigger