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Transcript of Sea Launch/Zenit Thrust: 8,180,000 N Fueled Weight: 450,000 kg Payload to LEO: 13,740 kg Cost per...
![Page 1: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/1.jpg)
Sea Launch/Zenit
Thrust:8,180,000 N
Fueled Weight:450,000 kg
Payload to LEO:13,740 kg
Cost per launch:
$100,000,000Cost per kg:
$7,300Launches:
31/28
Present:
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Colorado Space Grant Consortium
Gateway To SpaceASEN 1400 / ASTR 2500
Class #20
T-30
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- Announcements
- One minute Report Questions
- Mid Semester Team Evaluations
- Orbits and Mission Design – Part II
- Launch is in 30 days
Today:
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4
Announcements…
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
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5
Mid Semester Team Evaluations…
Please pass them forward now
New grades posted next Tuesday
Community Service project will be included
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Colorado Space Grant Consortium
Next Tuesday…Guest Lecture on ADCS
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One Minute Reports:
Geostationary VS. Geosynchronous
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One Minute Reports:
- 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?
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Types of Rockets:
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One Minute Reports:
- 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 in-class simulation work?- Do we need to have all the satellite building and
testing done before the in-class simulation?- What chances do students have to go to those big
conferences?
-
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One Minute Reports:
- Where does Tom Kelly work now?
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One Minute Reports:
-- 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…
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Colorado Space Grant Consortium
Orbits and Mission Design – Part 2ASEN 1400 / ASTR 2500
Class #19
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Orbits:A Brief Historical Look
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Earth, the Moon, Mars, and the Stars Beyond
A Brief Discussion on Mission Design
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Universal Gravitation, Applied:
• What is an orbit?
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Newton’s Laws:
Newton Continued... • 1687, Principia Published• Law of Universal Gravitation (Attraction)
221
r
GmmF
r
VmF
22ma
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Orbit History:
Kepler’s 3 Laws of Planetary Motion:
1. All planets move in elliptical orbits, sun at one focus
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Orbit History:
Kepler’s 3 Laws of Planetary Motion:2. A line joining any planet to the sun, sweeps
out equal areas in equal times
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Orbit History:
Kepler’s 3 Laws of Planetary Motion:3. The square of the period of any planet about the sun is
proportional to the cube of the of the planet’s mean distance from the sun.
If you can observe the period of rotation, you can determine the distance
Planet P (yr) a (AU) T2 R3
Mercury 0.24 0.39 0.06 0.06
Venus 0.62 0.72 0.39 0.37
Earth 1.00 1.00 1.00 1.00
Mars 1.88 1.52 3.53 3.51
Jupiter 11.9 5.20 142 141
Saturn 29.5 9.54 870 868
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Types of Orbits:
Orbits are conic sections:• Circle• Ellipse• Parabola• Hyperbola
From Kepler’s Law, the central body is at a focus of the conic section
a
MG
r
MGV
2
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Kepler:
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=):
v2 r
a
GM
v r
v2 r
a
v2 r
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Earth, the Moon, Mars, and the Stars Beyond
A Brief Discussion on Mission Design
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Orbit Introduction:
What is an orbit?- The path of a satellite around the Earth (or any central body)
What shape is it?- Orbits are conic sections- Circles, Ellipses, Parabolas, Hyperbolas
How are orbits described?- Position and Velocity at any one time- Keplerian Elements (from Kepler’s Laws)
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Orbit Definition:
Velocity & Position
- Given position and velocity of a satellite at time t, you can calculate the position and velocity at any other time
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Orbit Definition:
Keplerian Elements
- Semi major axis (a)- Size
- Eccentricity (e)- Shape
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Orbit Definition:
Keplerian Elements
- Inclination (i)- Angle to the Equator
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Orbit Definition:
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Orbit Definition:
Keplerian Elements
- Right Ascension of Ascending Node (RAAN, Ω)- Rotation about the Earth’s Spin Axis
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Orbit Definition:
Keplerian Elements
- Argument of Perigee (ω)- Rotation of the conic section in the plane
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Orbit Definition:
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
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Types of Orbits (cont.)
• Geosynchronous/Geostationary (equator)
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Types of Orbits (cont.)
• Critical Inclination
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Types of Orbits (cont.)
• Repeating Ground Trace
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• Polar/ Sun Synchronous
Types of Orbits (cont.)
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Types of Orbits (cont.)
• Molniya
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Circular Orbit:
For a 250 km circular Earth Orbit
Orbital Velocity
v r
v398600.4
(250 6378.14)
v7.75 km
sec 17,347 mph
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Circular Orbit:
Orbital Period
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Circular Orbit:
For a 500 km circular Earth Orbit
Orbital Velocity
v r
v398600.4
(500 6378.14)
v7.61 km
sec 17,028 mph
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Circular Orbit:
For a 500 km circular Earth Orbit
Orbital Period
Conclusions???
P 2 r3
P 2(500 6378.14)3
398600.4P 5,676 sec 94.6 min
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Changing Orbits:
How about 250 km to 500 km
How would you do it?
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Changing Orbits:
Changing orbits usually involves an elliptical orbit or Transfer Orbit
Perigee = closeApogee = far
apof
iper
vvv
vvv
2
1
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Changing Orbits:
1) Velocity of initial orbit
2) Velocity of final orbit
3) Velocity at perigee 4) Velocity at apogee
v f 7.61 km
sec
apof
iper
vvv
vvv
2
1
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Changing Orbits:
Since orbit is elliptical at Vper and Vapo a > 0, so
where
v2 r
a
a r1 r2
2
a (250 6378.14) (500 6378.14)
2a 6753 km
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Changing Orbits:
So back to our DV’s3) Velocity at perigee
vper 2 r
a
vper 2* 398600.4
(250 6378.14)
398600.4
6753
vper 7.83 km
sec
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Changing Orbits:
So back to our DV’s4) Velocity at apogee
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Changing Orbits:
1) Velocity of initial orbit
2) Velocity of final orbit
3) Velocity at perigee 4) Velocity at apogee
v f 7.61 km
sec
apof
iper
vvv
vvv
2
1
vapo 7.54 km
sec
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Changing Orbits:
Therefore:DV1 is to start transfer
v2v1
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Changing Orbits:
DV2 is to circularize orbit
v2v1
![Page 51: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/51.jpg)
Changing Orbits:
What if we did the whole thing in reverse?
Go from 500 to 250 km?
What happens to the answer?
![Page 52: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/52.jpg)
Changing Orbits:
1) Velocity of initial orbit
2) Velocity of final orbit
3) Velocity at perigee 4) Velocity at apogee
vapo 7.54 km
sec
![Page 53: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/53.jpg)
Changing Orbits:
Therefore:DV1 is to start transfer
![Page 54: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/54.jpg)
Changing Orbits:
DV2 is to circularize orbit
![Page 55: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/55.jpg)
Changing Orbits:
Time to do transfer is the same
v2v1
![Page 56: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/56.jpg)
How well do you understand Hohmann Transfers?
123
• 1 to 2?
• 2 to 3?
• 3 to 1?
• 1 to 3?
![Page 57: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/57.jpg)
Circular Orbit:
![Page 58: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/58.jpg)
Changing Orbits:
Also something called “Fast Transfer”
• It is more direct and quicker
• However it takes more fuel
• DV1 and DV2 are
much bigger
![Page 59: 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.](https://reader036.fdocuments.us/reader036/viewer/2022062518/5697bf9c1a28abf838c933c5/html5/thumbnails/59.jpg)