General Knowledge Lecture of Science Rocket Science & Satellite Technology Delft University of TechnologyAerospace EngineerSpeaker : Alta Y. N. CHOI : 15- July 2008 Venue : Hong Kong Productivity Council Exhibition Hall

Ancient Chinese Rocket Modern Rocket

Pioneer in Rocket Development K.E. Tsiolkowsky (1857-1935, Russia) - 1903 - Tsiolkowsky V = Vf - Vi == Ispgoln- (Isp)R.H. Goddard (1882-1945, USA) - 1926 - LinkH.J. Oberth (1894 - 1989, Aus. Hon. , German, Romania) - 20 - 1927 W. von Braun (1912-1977, German) - V-2 - V-2

The first real Rocket V-2 / (3:1)

Length 14 mMax. Diameter () 1.65 mLaunch mass 13 tonsThrust 245 kNBurn time 65 secMax. speed 5,750 km/hrMax. altitude96 kmRange 320 km

Saturn V Rocket( 5 )

Delta Series Rocket

Russian Rocket SoyuzProton

Ariane Series ( )PayloadL H2L O2BoosterL H2KickBooster

Series of Long March Rocket -3A-2F

(CF) - 3A (CF) 2F

(CF) -3A (CF) - 2F

Japanese Rocket (H) Series (H II) H-IIAH-IIAH-IIH-IIBH-IIA

Rocket Performance in Different Country Delta Ariane Soyuz Long March H-series(1.68%) (0.80%) (0.45%) (0.75%) (1.28%)

The Launch of CZ-3A with CI-1 3 1

From Launch base into Orbit 1 2 3 3 1 1 2 2 (2.5m) (6.6m) (9.8 min) (15s)

Effect of Earth Rotation & Gravitational Field (360o/24hr)

Controlling of Rocket Engine Tilt the whole engine

Controlling of Rocket Engine 2. Generating one side stall

Launching of Satellite in Geostationary Orbit (35,786 km)() (200 km)

Kick Booster

Launch Bases in China (38o43N)(3850'N)()(28o12N)(19o19N)

Change of Orbit in Space

Change of Orbit of ChangE-1 in Space 1

Change of Orbit of ChangE-1 in Space La Grangian point

Change of Orbit of Kaguya in Space

Classification of Rocket 1Chemical Propulsion System i) Solid-fuel Rocket (Isp~250) ii) Liquid-fuel Rocket (Isp~450)iii) Hybrid-fuel Rocket 2Electrical Propulsion System i) Electronic Power Rocket (Isp=700-1000) ii) Ionian Power Rocket (Isp=8500-20,000)iii) Plasma Power Rocket (Isp=5,000-25,000)3 Thermal-Nuclear Pro. Sys.(Isp~850)4 Photonic Propulsion System( )

Solar Sail of NASA ()

Solid Rocket-propellant

Composition of Propellant Type (kg/m3)Temp(K)I sp(sec)Nitrocellulose (40-55%) Nitroglycerin (25-50%) Additive (10-20%) Homogeneity(Double-base)1,510|1,6201,700|3,100195|250Polymer (20%) Ammonia perchloride (80%)Composite 1,6602,600231Polymer (12.5%) Aluminium (16%) Ammonia perchloride(69.9%)Additive (1.6%) Composite1,7723,480260Nitrocellulose (26%) Nitroglycerine (27.2%) Aluminium (18.9%) Ammonia perchloride(19.5%)Additive (8.4%) Composite(Modified Double-base)1,7454,000263

Working Principal of Solid Rocket Engine

Possible Forms of Loading Solid Rocket-propellant 1. Gradually accelerate to maximum speed 1.

Possible Forms of Loading Solid Rocket-propellant 2. Instantly to maximum speed then gradually decelerate 2.

Liquid Rocket Propellant

Composition of Propellant Proportion ofFuel/Oxidiser(kg/m3)Temp(Ko)I sp(sec)Mono-Propellants:Nitro-Methane (CH3NO2) ()Hydrazine (N2H4) ()Hydrogen-peroxide (H202) () ---1,1371,0111,4422,6469661,278255199165Bi-Propellants:Kerosene () / Oxygen (02) )()Kerosene / Nitrogen tetra-oxide (N2O4) () 1 : 2.45 1 : 31,0201,2253,6873,255301291L. Hydrogen (H2) / L. Oxygen (02)( / ) 1 : 42802,980390Unsymmetrical Di-Methyl-Hydrazine ()(UDMH) / Oxygen (02)()UDMH / Nitrogen tetra-oxide (N2O4) 1 : 1.671 : 2.659701,1853,6233,436310286

Working Principal of Liquid Rocket Engine

Liquid Rocket Engine

Transporting of liquid fuel Hydrogen (-253oC, 67kg/s, 0,2 MPa)Oxygen (-162oC, 400kg/s, 0,7 MPa)Exhaust()(467 kg/s) (35 MPa) (1,233 oC) (36 MPa) (1,088 oC)

Comparison Between Solid-fuel and Liquid-fuel Solid fuel 1. 2. 3. ( Isp~250)4. ( )5. , 6. 7. 8. Liquid fuel - ( )- - ( Isp ~450)- (H2)- - - -

Satellite Science and its Related Technology

Development of Satellite 1945 - (Sir Arthur C. Clark)- 1957 - (Sputnik 1)- Link1958 - 1 (Explorer 1)- . (Van Allen Belts)- 1970 - 1Link2007 - - Link

Satellite Anatomy

Classification of Satellite 1. Hubble Link2. - 3. Link

Satellite Orbit 1. (160- 2,000 km) Low Earth Orbit (LEO) - Parking Orbit (200km), Polar Orbit (500-1,000km)2. (2,000- 35,786 km) Medium Earth Orbit (MEO) or Intermediate Circular Orbit (ICO) - Sun-synchronous Orbit (>6,000km)3.(~ 35,786 km)High Earth Orbit (HEO) - Geosynchronous Orbit (GSO) - Geostationary Earth Orbit (GEO)

Satellite Mostly Used Orbit 1. Geostationary Earth Orbit (GEO)

2. Polar Orbit 3. Sun-synchronous Orbit (SSO) Link

1. Geostationary Earth Orbit (GEO) i) () ii) Inclination 0 () iii) Eccentricity0 Cir. Orbit iv) Period (360o/24hrs) v) 35,7862. Polar Orbit i) Inclination 90 ii) iii) iv) 3. Sun-synchronous Orbit (SSO) i) 0.9856(360o/)

The Cosmic Velocity- 4 Initial Velocity

4

The Cosmic Velocity - 1 First Cosmic Velocity (7.8 km/s), Circular Velocity - 2 Second Cosmic Velocity (11.2 km/s) Break Away Velocity - 3 Third Cosmic Velocity (16.7 km/s) Escape Velocity - 4 Fourth Cosmic Velocity (~115 km/s)

End of seminarThanks for your attention Dr. Philip Leung Mr. Louis Lai For the Arrangement of this lecture and Consultant of lecture material Acknowledgement

Mr. Man Wu The first Astronaut in human history

Space Craft of Man Wu

Rocket nozzle improve performance

Robert Goddard and his world first liquid fuel rocketCombustion chamber Exhaust nozzle Liquid oxygen Benzene tank Fairing cap /Fuel pump Support frameFuel pijp First test flight 16-03-1926Link

Sputnik 1 (Elementary Satellite-1) 1 Link

Van Allen Belts . Link

Dong Fang Hong I (Red East 1) 1 Link

ChangE 1 1 Link

Hubble Space Telescope Link

NOAA Polar Orbiting Weather Satellite ()

Global Positioning System (GPS)

ESA Galileo Satellite & Orbit System

The Chinese GPS system (Beidou)

Advanced Extremely High Frequency (AEHF) Communication Satellite

DSP - Link

Geostationary Earth Orbit & Polar Orbit

Polar OrbitSolar OrbitDifference between Polar and Solar Orbit

Sun-synchronous Orbit Link

Ion Thruster

Hall Effect Thruster

Hall Effect Thruster

Plasma Power Rocket Engine

The Cosmic Velocity = (Gravitational Force=Centripetal Force) (1 = 1)

(G = 6.67 X 10-11N m2/kg2, Mearth = 5.98 X 1024 Kg, Rearth = 6,378 km) = eight = Centripetal Force (go = 9.80665 m/s2 ) - 1 First Cosmic Velocity (7.8 km/s), Circular Velocity

The Cosmic Velocity - 2 Second Cosmic Velocity (11.2 km/s) Break Away Velocity Kinetic Energy = Gravitational Potential Energy =

(2 = 2)

The Cosmic Velocity - 3 Third Cosmic Velocity (16.7 km/s) Escape Velocity - 42.1 / - 29.8 /- 12.3 /

(3 = 3 )

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