1. Rocket Propulsion

2. Rocket History

3. Tsiolkvsky
19세기 말
Russian Mathematician

4. Dr. Goddard US Rocket Scientist
Possible propulsion system for space journey

5. Buzz Bomb in world war II

6. What is the propulsion system?
A device to produce a thrust needed for the flight.
Airbreathing Engine
Rockets

7. Types of Propulsion Jet engines Rocket engines Airbreathing engines
Turbojet
Turbofan
Turboprop
Ram/Scramjet
Solid R.
Liquid R.
Hybrid Rocket
Hybrid engines
Turbojet/Ramjet
Turbofan/Ramjet
Turborocket
Ram-Rocket
ScRam-Rocket

8. Equation for Thrust
Newton’s 2nd Law
Propeller
Gas Turbine
Ramajet

9. Airbreathing Engine Inlet Combustor Nozzle Compressor Turbine
Accessories: Afterburner, Thrust Reverser, Spoiler..

10. Possible for combined cycle
Specific Impulse of various engines
x 10 -2
Possible for combined cycle

11. Application of rocket propulsion
Type
Max accel.
2-6g
Large space launch vehicle booster
Solid
Antiaircraft or antimissile-missile
Solid
5-20g
Liquid
Spacecraft orbit maneuver
0.2-6g
Air launched guided missile
Solid
Up to 25g
Battlefield support-surface launched
Solid/Liquid
Up to 10g
Spacecraft attitude control
Liquid/EP
Less than 0.1g
Space shuttle main engine
Liquid 4g
Antitank
Solid
Up to 20g

12. Rocket Propulsion Chemical Rocket Non-Chemical Rocket Large thrust
Low Isp
Liquid Propellant Rocket
Solid Propellant Rocket
Non-Chemical Rocket
Small thrust
High Isp
Electric Propulsion
Nuclear
Laser

14. Rocket Propulsion Energy Release Rate 0.3MW/m3: Boiler
300MW/m3: Jet Engine
30,000MW/m3: Rocket

15. Thrust Chamber

16. Fundamentals of rocket propulsion

18. Rocket Propulsion Thrust Tsiolkvsky equation Momentum Thrust
Pressure Thrust
Tsiolkvsky equation

19. Specific Impulse
Characteristic Velocity
Thrust Coefficient
A measure of propellant characteristic
A measure of combustion performance
A Function of nozzle geometry

20. Rocket Performance Three Fractions
Initial Mass=Final Mass+Propellant Mass
Initial Mass=Structure Mass+Propellant Mass+Payload Mass
Three Fractions

21. Design Objective to obtain the highest payload ratio
Thrust to Weight Ratio
Desirable to have a low mp/ mi and 

22. Typical mission velocity requirements
Earth to LEO
7600m/sec
LEO to GEO
4200m/sec
LEO to earth escape
3200m/sec
LEO to lunar orbit(7days)
3900m/sec
LEO to Mars orbit(0.7yr)
5700m/sec
LEO to Mars orbit(40days)
85000m/sec
LEO to Neptune orbit(29.9yr)
13400m/sec
LEO to solar escape
8700m/sec
LEO : Low earth orbit 270km

23. Multi-Stage Performance
Consider a vehicle with n stage
When we assume the n stages are identical

24. Optimization of Multistage Rocket
For a special case
Maximize
with Constraint
Lagrange Multiplier
Assume

25. Chemical Rocket
Liquid propellant rocket

26. SSME(Space shuttle main engine)

27. Characteristics of Liquid Propellant
Expansion from 6.94Mpa(1000psia) to 1 atm
Oxidizer
Fuel
OF ratio Ta
Density C*
Isp
4.13
3013
0.29
2416
389
2.58
3676
1.03
1799
300
7.94
3962
0.46
2556
411
2.17
3396
1.19
1745
288
1.98
3368
1.12
1747
288

28. Ideal Complete Combustion
with excess H2
Heat of Reaction /H2O mole

29. Equilibrium Combustion
Composition is determined by thermodynamic equilibrium

30. Non-Equilibrium Combustion

31. Comparison of Isp of 3 chemical model

32. S-3D Thrust : 150,000lbf Burning time : 150sec
Powered Jupiter Intermediate range ballistic missile(IRBM)

33. Solid propellant rocket
Category
Typical Characteristics
Booster and 2nd stage motor
L/D=2~7
t = 60~120sec
High-altitude motors
L/D=1~2
t = 40~120sec
Tactical missile
L/D=4~13
t = 0.25~1sec
Gas generator
To create high-pressure, energetic gas

34. Separation of Solid propellant booster

36. Types of Solid PropellantDB
Double Base
Composite
CMDB
Composite Modified DB

37. Typical Double Base Propellant
Material
Weight %
Purpose
51.40
Polymer
Nitrocellulose
42.93
Explosive plasticizer
Nitroglycerin
Diethyl Pthalate
3.20
Nonexplosive plasticizer
Ethyl Centralite
1.00
Stabilizer
Potassium sulfate
1.20
Flash suppresor
Carbon black
0.20
Opacifying agent
Candelilla wax
0.07
Die lubricant

39. Burning Rate
r: Burning rate(cm/sec)
연소실 압력
a, n
실험상수
0.4<n<0.7

40. Non-chemical propulsion
Electric propulsion

42. Types of Electric propulsion
Electrothermal
-Arcjet
-Resistojet
-MICROWAVE ELECTROTHERMAL THRUSTER (MET)
Electrostatic
-Ion Electron bombardment ion thruster
-Hall Thruster Stationary plasma thruster(SPT)
Electrodynamic
-MPD (magneto-plasma-dynamic)
-PPD (pulsed-plasma-dynamic)

43. Electrothermal
ARCJET
DC ARCJET
AC ARCJET
RF ARCJET
Microwave ARCJET

44. DC Arcjet
Hydrazine
Ammonia
Hydrogen

45. Resistojet

46. Microwave Electrothermal Thruster (MET)

47. Electrostatic Propulsion
Ion Thruster

48. Ion bombardment thruster

49. Hall thruster (gridless ion engine)
Invented by Russia and introduced 1992 to west

50. Stationary Plasma Thruster(SPT)

51. Electrodynamic MPD (magneto-plasmadynamic)
Utilize Lorenz Force in the magnetic field

52. Pulsed MPD thruster from Princeton University using Ar

53. Advanced propulsion Airbreathing engines Rocket engines
SSTO(Single stage to orbit)
Tactical Mission
Airbreathing engines
High specific impulse
Low T/W
Rocket engines
Low specific impulse
High T/W
Any propulsion systems can not be optimum over entire flight regime.

54. Maximum Thrust (Full Augmentation) 23,770 pounds (105.7 kN)
Intermediate Thrust (Nonaugmented) ,590 pounds (64.9 kN)
Weight ,2324 pounds (1467 kg)
Length in. (4.85 m)
Inlet Diameter in. (0.88 m)
Maximum Diameter in. (1. 18 m)
Bypass Ratio
Overall Pressure Ratio to 1

55. F-15

56. Types of Propulsion Jet engines Rocket engines Airbreathing engines
Turbojet
Turbofan
Turboprop
Ram/Scramjet
Solid R.
Liquid R.
Hybrid Rocket
Hybrid engines
Turbojet/Ramjet
Turbofan/Ramjet
Turborocket
Ram-Rocket
ScRam-Rocket

57. Hybrid Rocket

58. Hybrid Rocket 특징 비교적 높은 비추력 높은 안전성, Shutdown 능력 System Isp(sec)
Isp (g-s/cm3)
Liquid Bi-Propellant
(LOX/H2
:399)
:100)
Classic Hybrid
(LOX/HTPB
:330)
:350)
Solid Propellant
(AP/HTPB
:270)
:470)
환경적 친화성
점화의 신속성과 재점화 성능
추력조절이 용이함
경제적인 발사체
재사용 발사체
우주왕복선 Booster
전략 미사일 추진체
우주선 추진체

59. Hybrid rocket test fire(AMROC)

60. Turboramjet for tactical missile
Turbojet at low speed
Ramjet at high speed

61. Air Turbo Rocket(ATR) Combination of turbojet, ramjet and rocket
Up to M=6
Candidate for TSTO
Combination of turbojet, ramjet and rocket

62. 연소실 Configuration 변화 필요
로켓-램제트(IRR) 특징
높은 부피효율과 연소효율
로켓보다 높은 비추력 (1000~1500sec)
저고도, 고속비행 가능  우수한 침투능력, 높은 생존성
현대 무기체계로 매우 적합
정지추력을 위한 부스터 필요
부피 효율 극대화,
부스터와 액체 램제트 연소특성 차이
연소실 Configuration 변화 필요
원활한 IRR 추진 천이(부스터 추진  램제트 추진)

64. 미 해군 IRR-Fasthawk

65. 감사합니다.