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Transcript of Colorado Space Grant Consortium
![Page 1: Colorado Space Grant Consortium](https://reader036.fdocuments.net/reader036/viewer/2022081603/5681383b550346895d9fe5bc/html5/thumbnails/1.jpg)
Colorado Space Grant ConsortiumColorado Space Grant Consortium
Gateway To SpaceASEN / ASTR 2500
Class #19
Gateway To SpaceASEN / ASTR 2500
Class #19
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Announcements…
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Announcements…
- 25 days to launch
- Website updated
- Launch Vehicle In-class exercise
- Launch vehicle lecture
- Orbits and Mission Design Plan10/23/08 Part A (15 minutes)10/30/08 Part B (15 minutes)11/18/08 Part C (45 minutes)
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Announcements…
- This Thursday…
- Each team will have 5 minutes to demonstrate something related to there science mission in front of the class
- You may use projector or other A/V resources but slides are discouraged
- We will spend roughly one hour doing this
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Announcements…
- Next Tuesday we will have a guest lecture on Spacecraft Attitude Determination and Control (ADCS)
- Bruce Schulz from Lockheed Martin
- I will not be here but Kristina, Bruce Davis, and Brian Sanders will be present
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Announcements…
- Who is still waiting for hardware?
- Who is completely lost?
- Who needs something?
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One minute:
- How will the presentations at the Design Expo work?- Do we need to catch all this information as if it will
be potentially on the final?- What do you do about jerk team members?- I don’t have nice clothes here- What are the LRR cards?- Is there community service available by Space
Grant?- Tim May and scheduled meetings and how are we to
learn programming?- What string are we supposed to use for our whip
test?
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One minute:
- Why do we have to be worried?- Can you go over the camera code in more detail?- Does this only work for Canon cameras? Only this
model?- What if it stops working?- What can you change?- Whip test with mass sim?- Drop out of a plane?- Is it normal for team dynamics to fall apart now?- Craziest picture recorded by balloonsat?- Due date for the team video?
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One minute:
- Do the videos get watched by everyone at the end of class?
- How much drag does the balloonsat undergo?- What colorful language was used during zipline?- How many pictures will we get from the flight?- Why don’t you ever answer my questions in class?- What has been your most embarrassing moment?
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Team Video:
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Mid Semester Team Evaluations:
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Announcements:Announcements:
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Announcements:Announcements:
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Announcements:Announcements:
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Announcements:Announcements:
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In Class ExerciseIn Class Exercise
Before we get Before we get started…started…
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Building a Rocket on Paper:
- Please wait, everyone will be opening your envelopes in a minute
- Not every rocket design will work...
- YOU ARE A ROCKET ENGINEER:You make $70,000.00 a year and you have a masters degree and drive a company Viper
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Building a Rocket on Paper:
1.) Build a rocket with the right people.You will need…
Payload Specialist Thruster Specialist Fuel Expert Structural Engineer
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Building a Rocket on Paper:
2.) Calculate total mass of your rocket, must include everything.
Total mass = mass of fuel+payload+
structure+thrusters
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Building a Rocket on Paper:
3.) Calculate the thrust needed to lift your rocket off the launch pad
Needed thrust = total mass * gravity
F = m * a [Newtons, N])
1 N =1 kg*m/s21 pound-force = 4.45 Na=gravity=10 m/s2
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Building a Rocket on Paper:
4.) Calculate the total lift (thrust) capability of your rockets thrusters
5.) Does your structure support the total weight of the rocket?
6.) Do you lift off the ground or did you crash and burn?
7.) Could you lift off the surface of the moon?g(moon) = 1/6 g(earth)
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Ion Engine:
Max Thrust = 200 NEngine/Fuel Mass = 9,000 kg (90,000 N)Max Thrust (minus Engine/Mass) = - 82,000 NRemaining Mass = - 8,200 kg
Ashes
(2 kg)
Professor
(180 kg)
Stamps
(2K kg)
Water
(20K kg)
Tires
(200K kg)
Comments
Wood = 5K kg
(200 kg)
NO NO NO NO NO
Composite = 9K kg
(20 kg)
NO NO NO NO NO
Iron = 500K kg
(20,000 kg)
NO NO NO NO NO
Aluminum = 3M kg
(2,000 kg)
NO NO NO NO NO
Titanium = 5M kg
(2,000 kg)
NO NO NO NO NO
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Cold Gas Engine:
Max Thrust = 22,000 NEngine/Fuel Mass = 1,700 kg (17,000 N)Max Thrust (minus Engine/Mass) = 5,000 NRemaining Mass = 500 kg
Ashes
(2 kg)
Professor
(180 kg)
Stamps
(2K kg)
Water
(20K kg)
Tires
(200K kg)
Comments
Wood = 5K kg
(200 kg)
YES YES NO NO NO
Composite = 9K kg
(20 kg)
YES YES NO NO NO
Iron = 500K kg
(20,000 kg)
NO NO NO NO NO
Aluminum = 3M kg
(2,000 kg)
NO NO NO NO NO
Titanium = 5M kg
(2,000 kg)
NO NO NO NO NO
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Propane Engine:
Max Thrust = 100,000 NEngine/Fuel Mass = 8,000 kg (80,000 N)Max Thrust (minus Engine/Mass) = 20,000 NRemaining Mass = 2,000 kg
Ashes
(2 kg)
Professor
(180 kg)
Stamps
(2K kg)
Water
(20K kg)
Tires
(200K kg)
Comments
Wood = 5K kg
(200 kg)
NO NO NO NO NO Structural Failure
Composite = 9K kg
(20 kg)
YES YES NO NO NO Structural Failure
Iron = 500K kg
(20,000 kg)
NO NO NO NO NO
Aluminum = 3M kg
(2,000 kg)
NO NO NO NO NO
Titanium = 5M kg
(2,000 kg)
NO NO NO NO NO
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Liquid Engine:
Max Thrust = 1,500,000 NEngine/Fuel Mass = 103,000 kg (1,030,000 N)Max Thrust (minus Engine/Mass) = 470,000 NRemaining Mass = 47,000 kg
Ashes
(2 kg)
Professor
(180 kg)
Stamps
(2K kg)
Water
(20K kg)
Tires
(200K kg)
Comments
Wood = 5K kg
(200 kg)
NO NO NO NO NO Structural Failure
Composite = 9K kg
(20 kg)
NO NO NO NO NO Structural Failure
Iron = 500K kg
(20,000 kg)
YES YES YES YES NO
Aluminum = 3M kg
(2,000 kg)
YES YES YES YES NO
Titanium = 5M kg
(2,000 kg)
YES YES YES YES NO
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Solid Engine:
Max Thrust = 3,000,000 NEngine/Fuel Mass = 52,000 kg (520,000 N)Max Thrust (minus Engine/Mass) = 2,480,000 NRemaining Mass = 248,000 kg
Ashes
(2 kg)
Professor
(180 kg)
Stamps
(2K kg)
Water
(20K kg)
Tires
(200K kg)
Comments
Wood = 5K kg
(200 kg)
NO NO NO NO NO Structural Failure
Composite = 9K kg
(20 kg)
NO NO NO NO NO Structural Failure
Iron = 500K kg
(20,000 kg)
YES YES YES YES NO
Aluminum = 3M kg
(2,000 kg)
YES YES YES YES YES
Titanium = 5M kg
(2,000 kg)
YES YES YES YES YES
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Launch VehiclesLaunch Vehicles
Past, Present, Future & Sci-Fi FuturePast, Present, Future & Sci-Fi Future
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Outline:Outline:
- Fine Print
- Background & Rocket TypesBackground & Rocket Types
- Past
- Present
- Future
- Sci-Fi Future
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Rocket Types:Rocket Types:
- I don’t know everything about Launch VehiclesI don’t know everything about Launch Vehicles
- I may not be able to answer your questionsI may not be able to answer your questions
- This lecture is to expose you to all the different types This lecture is to expose you to all the different types of launch vehiclesof launch vehicles
- I can quit at any time I can quit at any time
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Background:Background:
- Thrust = the force that movesThrust = the force that moves
- Impulse = force over period of timeImpulse = force over period of time
- Specific Impulse = Isp = ratio of impulse to fuel usedSpecific Impulse = Isp = ratio of impulse to fuel used
- Higher Isp usually indicates low thrust but very little Higher Isp usually indicates low thrust but very little fuel usedfuel used
- Will learn more in Propulsion LectureWill learn more in Propulsion Lecture
- Rocket Types include: Solid, liquid, hybridRocket Types include: Solid, liquid, hybrid
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PastPast
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Past/Present:Past/Present:
Scout: Scout: (Solid Controlled Orbital Utility Test)(Solid Controlled Orbital Utility Test)
Thrust:Thrust: 464,700 N (104,500 lb)464,700 N (104,500 lb)Fueled Weight:Fueled Weight: 21,750 kg21,750 kgPayload to Orbit:Payload to Orbit: 270 kg LEO270 kg LEO
# of Flights:# of Flights: 188, 105 successful188, 105 successful
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Past:Past:
Jupiter CJupiter C
Thrust:Thrust: 334,000 N (75,090 lb)334,000 N (75,090 lb)Fueled Weight:Fueled Weight: 29,030 kg29,030 kgPayload to Orbit:Payload to Orbit: 9 kg LEO (14 kg)9 kg LEO (14 kg)
# of Flights:# of Flights: 6, 4 successful6, 4 successful
Explorer IExplorer I
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Past:Past:
Mercury RedstoneMercury Redstone
Thrust:Thrust: 347,000 N (78,000 lb)347,000 N (78,000 lb)Fueled Weight:Fueled Weight: Not Found kgNot Found kgPayload to Orbit:Payload to Orbit: 9 kg LEO9 kg LEO
# of Flights:# of Flights: 5, 5 successful5, 5 successful
Chimp “Ham”, Shepard, and GrissomChimp “Ham”, Shepard, and Grissom
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Past:Past:
Mercury Redstone VideoMercury Redstone Video
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Past:Past:
Go to the Moon VideoGo to the Moon Video
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Past:Past:
Saturn V Saturn V
Thrust:Thrust: 34,500,000 N (7,760,000 lb)34,500,000 N (7,760,000 lb)Fueled Weight:Fueled Weight: 2,910,000 kg2,910,000 kgPayload to Orbit:Payload to Orbit: 127,000 kg LEO127,000 kg LEO
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Past:Past:
The F1 Engine VideoThe F1 Engine Video
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Past:Past:
One Step VideoOne Step Video
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Past:Past:
Lunar Rover VideoLunar Rover Video
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Past:Past:
Apollo Astronaut VideoApollo Astronaut Video
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Saturn V:
Can it be built today?
- The blue prints still exist, however only on microfilm.
- All the subcontractors and suppliers
are no longer around.
- The technology is old. We can build much smaller and lighter rockets today.
Not really…
According to Prof. Jesco von Puttkamer, Program Manager of Future Planning at NASA in 1999…
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PresentPresent
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Present:Present:
United StatesUnited States- ShuttleShuttle- Atlas- Titan- Delta- Pegasus- Athena- Taurus- Falcon- ARES- Dragon (COTS)- Orion
Foreign- France (Ariane)- Japan (H-series)- China (Long March)- Russia (Proton,
Buran)
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Present:Present:
Space ShuttleSpace Shuttle
Thrust:Thrust: 28,200,000 N28,200,000 N(6,340,000 lb)(6,340,000 lb)
Fueled Weight:Fueled Weight: 2,040,000 kg2,040,000 kgPayload to Orbit:Payload to Orbit: 24,400 kg LEO24,400 kg LEOCost per launch:Cost per launch: $245,000,000$245,000,000Cost per kg:Cost per kg: $10,040$10,040
SRB Recovery
External Tank
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Present:Present:
First Shuttle Flight VideoFirst Shuttle Flight Video
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Present:Present:
SRB Separation VideoSRB Separation Video
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Present:Present:
External Tank VideoExternal Tank Video
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Present:Present:
Atlas IIASAtlas IIAS
Thrust:Thrust: 2,980,000 N2,980,000 N(670,000 lb)(670,000 lb)
Fueled Weight:Fueled Weight: 234,000 kg234,000 kgPayload to Orbit:Payload to Orbit: 8,390 kg LEO8,390 kg LEOCost per launch:Cost per launch: $78,000,000$78,000,000Cost per kg:Cost per kg: $9,296$9,296
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Present:Present:
Atlas II VideoAtlas II Video
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Present:Present:
Titan IVTitan IV
Thrust:Thrust: 4,800,000 N4,800,000 N(1,080,000 lb)(1,080,000 lb)
Fueled Weight:Fueled Weight: 860,000 kg860,000 kgPayload to Orbit:Payload to Orbit: 21,645 kg LEO21,645 kg LEOCost per launch:Cost per launch: $248,000,000$248,000,000Cost per kg:Cost per kg: $11,457$11,457
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Present:Present:
Titan IV VideoTitan IV Video
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Present:Present:
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Present:Present:
Delta IIDelta II
Thrust:Thrust: 2,630,000 N2,630,000 N(591,000 lb)(591,000 lb)
Fueled Weight:Fueled Weight: 230,000 kg230,000 kgPayload to Orbit:Payload to Orbit: 5045 kg LEO5045 kg LEO
17,000 kg17,000 kgCost per launch:Cost per launch: $60,000,000$60,000,000Cost per kg:Cost per kg: $11,892$11,892
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Present:Present:
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Present:Present:
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Present:Present:
Delta IVDelta IV
Height 63 - 77.2 m (206 - 253.2 ft) Height 63 - 77.2 m (206 - 253.2 ft) Diameter 5 m (16.4 ft) Diameter 5 m (16.4 ft) Mass 249,500 - 733,400 kg (550,000 Mass 249,500 - 733,400 kg (550,000
- 1,616,800 lb) - 1,616,800 lb) Stages 2 Stages 2 Capacity Capacity Payload to LEO 8,600 - 25,800 kg Payload to LEO 8,600 - 25,800 kg
(18,900 - 56,800 lb) (18,900 - 56,800 lb) Payload toPayload toGTO GTO
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Present:Present:
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Present:Present:
PegasusPegasus
Thrust:Thrust: 486,000 N486,000 N(109,000 lb)(109,000 lb)
Fueled Weight:Fueled Weight: 24,000 kg24,000 kgPayload to Orbit:Payload to Orbit: 455 kg LEO455 kg LEOCost per launch:Cost per launch: $9,000,000$9,000,000Cost per kg:Cost per kg: $19,800$19,800
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Present:Present:
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Present:Present:
Pegasus VideoPegasus Video
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Present:Present:
Ariane 44L (France)Ariane 44L (France)
Thrust:Thrust: 5,380,000 N5,380,000 N(1,210,000 lb)(1,210,000 lb)
Fueled Weight:Fueled Weight: 470,000 kg470,000 kgPayload to Orbit:Payload to Orbit: 9,600 kg LEO9,600 kg LEOCost per launch:Cost per launch: $110,000,000$110,000,000Cost per kg:Cost per kg: $11,458$11,458
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Present:Present:
Ariane 5 (France)Ariane 5 (France)
Thrust:Thrust: 11,400,000 N11,400,000 N(2,560,000 lb)(2,560,000 lb)
Fueled Weight:Fueled Weight: 737,000 kg737,000 kgPayload to Orbit:Payload to Orbit: 18,000 kg LEO18,000 kg LEOCost per launch:Cost per launch: $120,000,000$120,000,000Cost per kg:Cost per kg: $6,666$6,666
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Present:Present:
Ariane V VideoAriane V Video
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Present:Present:
H-2 (Japan)H-2 (Japan)
Thrust:Thrust: 3,959,200 N3,959,200 N(890,060 lb)(890,060 lb)
Fueled Weight:Fueled Weight: 260,000 kg260,000 kgPayload to Orbit:Payload to Orbit: 10,500 kg LEO10,500 kg LEOCost per launch:Cost per launch: $190,000,000$190,000,000Cost per kg:Cost per kg: $18,095$18,095
VideoVideo
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Present:Present:
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Present:Present:
H2 VideoH2 Video
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Present:Present:
Long March CZ2E (China)Long March CZ2E (China)
Thrust:Thrust: 5,922,000 N5,922,000 N(1,331,000 lb)(1,331,000 lb)
Fueled Weight:Fueled Weight: 464,000 kg464,000 kgPayload to Orbit:Payload to Orbit: 8,800 kg LEO8,800 kg LEOCost per launch:Cost per launch: $50,000,000$50,000,000Cost per kg:Cost per kg: $5,681$5,681
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Yang Liwei
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Present:Present:
Sea Launch / Sea Launch / ZenitZenitWidest Diameter: Widest Diameter: 14 feet 14 feet
Overall length: Overall length: Approximately Approximately 200 feet 200 feet
All stages are All stages are kerosene/liquid kerosene/liquid oxygen fueled oxygen fueled
Capacity to Capacity to geosynchronus geosynchronus transfer orbit: transfer orbit: 6,000 kg 6,000 kg
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Present:Present:
Proton D-1 (Russia)Proton D-1 (Russia)
Thrust:Thrust: 9,000,000 N9,000,000 N(2,000,000 lb)(2,000,000 lb)
Fueled Weight:Fueled Weight: 689,000 kg689,000 kgPayload to Orbit:Payload to Orbit: 20,000 kg LEO20,000 kg LEOCost per launch:Cost per launch: $70,000,000$70,000,000Cost per kg:Cost per kg: $3,500$3,500
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Present:Present:
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Soyuz:Soyuz:
Gross mass: 98,100 lbmGross mass: 98,100 lbmPropellant: 86,400 lbm Propellant: 86,400 lbm Diameter: 8 ft 10 inDiameter: 8 ft 10 inLength: 64 ft 4 inLength: 64 ft 4 inBurn time: 118 s Burn time: 118 s Thrust 813 kN (183 klbf) Thrust 813 kN (183 klbf)
at liftoff at liftoff Specific impulse 245 Specific impulse 245
kgf·s/kg (2.40 kN·s/kg) kgf·s/kg (2.40 kN·s/kg) at liftoff at liftoff
Specific impulse 310 Specific impulse 310 kgf·s/kg (3.04 kN·s/kg) kgf·s/kg (3.04 kN·s/kg) in vacuum in vacuum
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Present:Present:
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Present:Present:
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Present:Present:
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Present:Present:
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Present:Present:
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Present:Present:
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Present/Past:Present/Past:
Energia (Russia)Energia (Russia)
Thrust:Thrust: 34,800,000 N 34,800,000 N (7,820,000 lb)(7,820,000 lb)
Fueled Weight:Fueled Weight: 2,400,000 kg 2,400,000 kg Payload to Orbit:Payload to Orbit: 90,000 kg LEO90,000 kg LEOCost per launch:Cost per launch: $764,000,000?$764,000,000?Cost per kg:Cost per kg: $Not Known$Not Known
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Present/Past:Present/Past:
Buran “Snowstorm” (Russia)Buran “Snowstorm” (Russia)
First and only launchFirst and only launchNovember 15, 1988November 15, 1988
No one on boardNo one on board- Life support not tested- Life support not tested- CRT’s did not have software- CRT’s did not have software
Only 2 orbitsOnly 2 orbits- This was limited because of computer memory- This was limited because of computer memory
Landed by autopilotLanded by autopilot
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Present/Past:Present/Past:
Aero Buran was test unitAero Buran was test unit
Had 24 test flightsHad 24 test flights
3 others were being built3 others were being built- Pitchka (Little Bird)- Pitchka (Little Bird)- Baikal (Typhoon) - Baikal (Typhoon)
All dismantled in 1995All dismantled in 1995
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Present/Past:Present/Past:
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Present/Past:Present/Past:
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Present/Past:Present/Past:
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Present/Past:Present/Past:
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Present/Past:Present/Past:
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Present/Past:Present/Past:
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FutureFuture
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Future/Past:Future/Past:
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Falcon 1:Falcon 1:
- Length: 21.3 m (70 ft) - Width: 1.7 m (5.5 ft) - Mass: 38,555 kg (85
klbs) - Thrust on liftoff: 454
kN (102 klbf)
- Launch video
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Future:Future:
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Falcon 9:Falcon 9:
- Length: 54.3 m (178 ft) - Width: 3.6 m (12 ft) - Mass (LEO, 5m fairing): 325,000 kg
(716 klb) - Mass (GTO, 4m fairing): 323,000 kg
(713 klb) - Thrust (vacuum): 4.4 MN (1 M lb)
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Dragon:Dragon:
- Fully autonomous rendezvous and docking with manual override capability in crewed configuration
- Pressurized Cargo/Crew capacity of >2500 kg and 14 cubic meters
- Down-cargo capability (equal to up-cargo)
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Dragon:Dragon:
- Supports up to 7 passengers in Crew configuration - Reaction control system - 1200 kg of propellant from sub-orbital insertion to
ISS rendezvous to reentry - Designed for water landing under parachute for
ocean recovery
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Dragon:Dragon:
- Lifting re-entry for landing precision & low-g’s - Ablative, high-performance heat shield
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Future/Past:Future/Past:
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NASA’s Exploration Roadmap
05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25
Lunar Lander Development
Ares V Development
Earth Departure Stage Development
Surface Systems Development
Orion CEV Development
Ares I Development
Space Shuttle Ops
Lunar Outpost BuildupInitial Orion Capability
Ares/Orion Production and Operations
Lunar Robotic Missions
Science Robotic Missions
1st Human Orion Flight
7th Human Lunar Landing
Early Design Activity
Demonstrate Commercial Crew/Cargo for ISSDemonstrate Commercial Crew/Cargo for ISS
Mars Expedition DesignMars Expedition Design
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Ares ICrew Launch
Vehicle
Earth Departure Stage
OrionCrew Exploration
Vehicle
LunarLander
ELO Ambassador Briefing – 105
Ares VCargo Launch
Vehicle
Our Exploration Fleet
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Crew
Lander
S-IVB(1 J-2 engine)240k lb LOx/LH2
S-II(5 J-2 engines)1M lb LOx/LH2
S-IC(5 F-1 engines)3.9M lb LOx/RP
LunarLander
Earth DepartureStage (EDS) (1 J-2X)499k lb LOx/LH2
Core Stage(5 RS-68 Engines)3.1M lb LOx/LH2
Upper Stage(1 J-2X)
280k lb LOx/LH2
5-Segment Reusable Solid Rocket Booster (RSRB)
Space Shuttle Ares I Ares V Saturn VHeight: 184.2 ft
Gross Liftoff Mass: 4.5M lb
55k lbm to LEO
Height: 321 ftGross Liftoff Mass: 2.0M lb
48k lbm to LEO
Height: 358 ftGross Liftoff Mass: 7.3M lb
117k lbm to TLI144k lbm to TLI in Dual-Launch Mode with Ares I
290k lbm to LEO
Height: 364 ftGross Liftoff Mass: 6.5M
lb
99k lbm to TLI262k lbm to LEO
Two 5-SegmentRSRBs
Orion CEV
Building on a Foundation of Proven Technologies– Launch Vehicle Comparisons –
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Ares I Elements
Stack Integration
• ~25 mT payload capacity• 2 Mlb gross liftoff weight• 315 ft in length• NASA-led
Stack Integration
• ~25 mT payload capacity• 2 Mlb gross liftoff weight• 315 ft in length• NASA-led
Upper Stage
• 280 klb LOx/LH2 stage
• 216.5 in. (5.5 m) diameter • Aluminum-Lithium (Al-Li) structures• Instrument unit and interstage• Reaction Control System (RCS) / roll
control for 1st stage flight• Primary Ares I avionics system• NASA Design / Contractor Production
First Stage
• Derived from currentShuttle RSRM/B
• Five segments/Polybutadiene Acrylonitrile (PBAN) propellant
• Recoverable• New forward adapter• Avionics upgrades• ATK Launch Systems
Upper Stage Engine
• Saturn J-2 derived engine (J-2X)• Expendable • Pratt and Whitney Rocketdyne
Orion• 198 in. (5 m) diameter
Orion• 198 in. (5 m) diameter
InterstageCylinder
InterstageCylinder
LAS LAS
Spacecraft Adapter
Spacecraft Adapter
Instrument Unit
Instrument Unit
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Ares V Elements
Stack Integration
• 65 mT payload capacity• 7.3 Mlb gross liftoff weight• 358 ft in length• NASA-led
Stack Integration
• 65 mT payload capacity• 7.3 Mlb gross liftoff weight• 358 ft in length• NASA-led
Earth Departure Stage
• TBD klb LOx/LH2 stage
• 216.5 in (5.5-m) diameter • Aluminum-Lithium (Al-Li) structures• Instrument unit and interstage• Primary Ares V avionics system• NASA Design / Contractor Production
Core Stage
• Two recoverable five-segment PBAN-fueled boosters (derived from current Shuttle RSRM/B).
• Five Delta IV-derived RS-68 LOx/LH2 engines (expendable).
LSAM• TBD LSAM• TBD
Spacecraft Adapter
Spacecraft Adapter
InterstageInterstage
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NASA’s Exploration Transportation System
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Our Nationwide Team
Dryden
Ames
Kennedy
Langley
Marshall GlennGoddard
Stennis
ATK Launch Systems
Pratt and Whitney Rocketdyne
Jet Propulsion Laboratory
Jet Propulsion Laboratory
JohnsonMichoud Assembly
Facility
Michoud Assembly
Facility
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Sci-Fi Future:Sci-Fi Future:
- $10 Billion$10 Billion
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Future/Past:Future/Past:
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Sci-Fi Future:Sci-Fi Future:
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Future/Past:Future/Past:
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Future/Past:Future/Past:
- Crew Return VehicleCrew Return Vehicle- X-38X-38
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Future/Past:Future/Past:
X-38 VideoX-38 Video
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Future/Past:Future/Past:
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Future/Past:Future/Past:
- X-33
- VentureStar
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Future/Past:Future/Past:
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Future:Future:
- - Delta IV HeavyDelta IV Heavy
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Future:Future:
- - Delta IV HeavyDelta IV Heavy
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Future:Future:
- Shuttle Fly-back boostersShuttle Fly-back boosters
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Future:Future:
- X-37
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Future:Future:
Ion Drive VideoIon Drive Video
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Sci-Fi FutureSci-Fi Future
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Sci-Fi Future:Sci-Fi Future:
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Sci-Fi Future:Sci-Fi Future:
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Sci-Fi Future:Sci-Fi Future:
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Sci-Fi Future:Sci-Fi Future:
- Anti-matterAnti-matter
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Sci-Fi Future:Sci-Fi Future:
- Boussard Ramjet Fusion PropulsionBoussard Ramjet Fusion Propulsion
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Sci-Fi Future:Sci-Fi Future:
- Electrodynamic TetherElectrodynamic Tether
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Sci-Fi Future:Sci-Fi Future:
- Jovian Electrodynamic TetherJovian Electrodynamic Tether
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Sci-Fi Future:Sci-Fi Future:
- Laser PropulsionLaser Propulsion
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Sci-Fi Future:Sci-Fi Future:
- Beamed Energy PropulsionBeamed Energy Propulsion
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Sci-Fi Future:Sci-Fi Future:
- Pulsed Detonation RocketPulsed Detonation Rocket
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Sci-Fi Future:Sci-Fi Future:
- Space Based Laser Re-boostSpace Based Laser Re-boost
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Sci-Fi Future:Sci-Fi Future:
- Plasma RocketPlasma Rocket
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Sci-Fi Future:Sci-Fi Future:
- Plasma RocketPlasma Rocket
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Sci-Fi Future:Sci-Fi Future:
- Space ElevatorSpace Elevator- Original concept as old as Original concept as old as
Mesopotamia: Biblical Mesopotamia: Biblical “Tower of Babel” and “Tower of Babel” and “Jacob’s Ladder”“Jacob’s Ladder”
- Five Critical Technologies Five Critical Technologies (Source: MSFC Study)(Source: MSFC Study)
- High Strength High Strength Materials Materials
- Tension StructuresTension Structures- Compression Compression StructuresStructures
- EM PropulsionEM Propulsion- Supporting Supporting InfrastructureInfrastructure
- May Lower Launch Costs May Lower Launch Costs to <$10/kg!to <$10/kg!
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Sci-Fi Future:Sci-Fi Future:
- $10 Billion$10 Billion- To LEO or GEO?To LEO or GEO?
- LEO: Possible TodayLEO: Possible Today- Lower end just inside atmosphereLower end just inside atmosphere- Space plane flies to lower end for cargoSpace plane flies to lower end for cargo- 10-12 times the cargo lifted by SSTO10-12 times the cargo lifted by SSTO
- GEO: YR 2050+GEO: YR 2050+
- Time Frame:Time Frame:- 10-20 Years for enabling technologies10-20 Years for enabling technologies- YR 2050 + for actual constructionYR 2050 + for actual construction
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Sci-Fi Future:Sci-Fi Future:
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Sci-Fi Future:Sci-Fi Future:
- $10 Billion$10 Billion