Colorado Space Grant Consortium Gateway To Space ASEN / ASTR 2500 Class #18 Gateway To Space ASEN /...

Colorado Space Grant ConsortiumColorado Space Grant Consortium

Gateway To SpaceASEN / ASTR 2500

Class #18

Gateway To SpaceASEN / ASTR 2500

Class #18

Announcements:

- Guest Speaker next time – Spacecraft Propulsion

- Still waiting to hear about DV recorders

- 18 Days to launch

- Still working grade emails

- Still reviewing DD Bs

- DD C is due 11-08-07

- Marv Luttges

CDR General Comments:CDR General Comments:

Announcements:Announcements:

In Class ExerciseIn Class Exercise

Before we get Before we get started…started…

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


1.) Build a rocket with the right people.You will need…

Payload Specialist Thruster Specialist Fuel Expert Structural Engineer


2.) Calculate total mass of your rocket, must include everything.

Total mass = mass of fuel+payload+

structure+thrusters


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


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)

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

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

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

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)


Composite = 9K kg

(20 kg)


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

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)


Composite = 9K kg

(20 kg)


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

Launch VehiclesLaunch Vehicles

Past, Present, Future & Sci-Fi FuturePast, Present, Future & Sci-Fi Future

http://hea-www.harvard.edu/~jcm/space/images/data/lv/90028.tif

Outline:Outline:

- Fine Print

- Background & Rocket TypesBackground & Rocket Types

- Past

- Present

- Future

- Sci-Fi Future

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

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

PastPast

Past/Present:Past/Present:

Scout Scout

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



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)


Explorer IExplorer I


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


Chimp “Ham”, Shepard, and GrissomChimp “Ham”, Shepard, and Grissom

Past:Past:

Mercury Redstone VideoMercury Redstone Video

Past:Past:

Go to the Moon VideoGo to the Moon Video

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

Past:Past:

The F1 Engine VideoThe F1 Engine Video

Past:Past:


Past:Past:

One Step VideoOne Step Video

Past:Past:

Lunar Rover VideoLunar Rover Video

Past:Past:

Apollo Astronaut VideoApollo Astronaut Video

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…

PresentPresent

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)

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

Present:Present:

First Shuttle Flight VideoFirst Shuttle Flight Video

Present:Present:

SRB Separation VideoSRB Separation Video

Present:Present:

External Tank VideoExternal Tank Video

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

Present:Present:

Atlas II VideoAtlas II Video

Present:Present:

Titan IVTitan IV



Present:Present:

Titan IV VideoTitan IV Video

Present:Present:

Present:Present:

Delta IIDelta II


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

Present:Present:

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

Present:Present:

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


Present:Present:

Present:Present:

Pegasus VideoPegasus Video

Present:Present:

Ariane 44L (France)Ariane 44L (France)




Present:Present:

Ariane 5 (France)Ariane 5 (France)



Present:Present:

Ariane V VideoAriane V Video

Present:Present:

H-2 (Japan)H-2 (Japan)



VideoVideo

Present:Present:

Present:Present:

H2 VideoH2 Video

Present:Present:

Long March CZ2E (China)Long March CZ2E (China)



Yang Liwei

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

Present:Present:

Proton D-1 (Russia)Proton D-1 (Russia)



Present:Present:

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

Present:Present:

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


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


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

FutureFuture

Future/Past:Future/Past:

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

Future:Future:

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)

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)

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

Dragon:Dragon:

- Lifting re-entry for landing precision & low-g’s - Ablative, high-performance heat shield

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

Ares ICrew Launch

Vehicle

Earth Departure Stage

OrionCrew Exploration

Vehicle

LunarLander

ELO Ambassador Briefing – 96

Ares VCargo Launch

Vehicle

Our Exploration Fleet

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 –

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

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

NASA’s Exploration Transportation System

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

Sci-Fi Future:Sci-Fi Future:

- $10 Billion$10 Billion


- Crew Return VehicleCrew Return Vehicle- X-38X-38


X-38 VideoX-38 Video


- X-33

- VentureStar

Future:Future:

- - Delta IV HeavyDelta IV Heavy

Future:Future:

- Shuttle Fly-back boostersShuttle Fly-back boosters

Future:Future:

- Hyper-X

Future:Future:

- X-37

Future:Future:

Ion Drive VideoIon Drive Video

Sci-Fi FutureSci-Fi Future


- Anti-matterAnti-matter


- Boussard Ramjet Fusion PropulsionBoussard Ramjet Fusion Propulsion


- Electrodynamic TetherElectrodynamic Tether


- Jovian Electrodynamic TetherJovian Electrodynamic Tether


- Laser PropulsionLaser Propulsion


- Beamed Energy PropulsionBeamed Energy Propulsion


- Pulsed Detonation RocketPulsed Detonation Rocket


- Space Based Laser Re-boostSpace Based Laser Re-boost


- Plasma RocketPlasma Rocket


- 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!


- $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


- $10 Billion$10 Billion

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