Comments on Rocket Scaling
Dr. Adam London, Ventions, LCC, President and CEO
Dr. Daniel Kirk, Florida Institute of Technology, Associate Professor
Overview:
On traditional liquid-fueled launch vehicles, the engines themselves tend to weight about twice
as
MAE 4262: ROCKETS AND MISSION ANALYSIS
Introduction to Electric Propulsion
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
ELECTRIC PROPULSION OVERVIEW
Chemical rockets: Energy limited
Limited to energy containe
SUMMARY: Single Stage Rockets
The total mass of the rocket stage can be considered to be the sum of several parts:
ML: Mass of the payload
MP: Mass of the propellant
MS: Structural mass
The structural mass includes all other mass but the payload and the p
MAE 4262: ROCKETS AND MISSION ANALYSIS
Combustion Overview for Rocket Applications
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
1
CONTENTS
Overview
Review of thrust chamber governing equations
Why operate H2
Integral Momentum Theorem
We can learn a great deal about the overall behavior of propulsion systems using the
integral form of the momentum equation. The equation is the same as that used in fluid
mechanics and in air-breathing propulsion.
The momentum t
MAE 4262: ROCKETS AND MISSION ANALYSIS
Basics of Chemical Rocket Performance
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
Schematic Diagram of a Conventional Liquid Rocket
Motor (Figure 11.1 in Sforza)
2
North
MAE 4262: Notes on Gravity Loss and Optimum Acceleration
The rocket equation can be written as:
m t
V Vo Ve ln
m gt
o
1
In this equation we have neglected the effects of drag and have assumed that the rocket is
traveling in vertical flight. Vo is the
MAE 4262: ROCKETS AND MISSION ANALYSIS
Conservation Equations and Examples
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
CONSERVATION OF MASS
d
dV
U n dS 0
dt CV
S
Relative to CS
d
dV
U U CS ndS 0
dt CV
S
I
SOLID ROCKET COMBUSTION STABILITY1
Section 12.5.3 of Theory of Aerospace Propulsion, by Pasquale Sforza, discusses the
burning stability of solid rocket motors, and demonstrates in a qualitative fashion that the
pressure exponent, n, should be less than u
MAE 4262: ROCKETS AND MISSION ANALYSIS
Rocket Nozzles
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
CONTENTS
Review of Nozzle Performance
Review of Converging Nozzle Operation
Review of Converging-Diverging Noz
MAE 4262: ROCKETS AND MISSION ANALYSIS
Overview of Solid Propellant Rockets
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
1
SOLID PROPELLANT ROCKETS
Solid fuel rockets rely on controlled explosion of a mixture
MAE 4262: ROCKETS AND MISSION ANALYSIS
Single and Multi-Stage Rockets
September 9, 2014
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
1
SINGLE-STAGE SOUNDING ROCKET SUMMARY
1 t
V t ue ln 1 1 gt
Rt
b
ln R 1
MAE 4262: ROCKETS AND MISSION ANALYSIS
Rocket Combustion Chambers
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
1
CONTENTS
Overview
Thermal Rocket Combustion Chambers
Liquid Rocket
Solid Rocket
Hybrid Rocket
MAE 4262: ROCKETS AND MISSION ANALYSIS
Method of Characteristics Summary and Rocket Nozzle Examples
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
METHOD OF CHARACTERISTICS
Universal way to examine supersonic fl
MAE 4262: ROCKETS AND MISSION ANALYSIS
Rocket Cycle Analysis
November 27, 2012
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
CONTENTS
Overview
Propellant Feed Systems / Cycle Examples
1. Gas Feed System
2. Turb
CHEMICAL vs. ELECTRIC ROCKET PROPULSION
CHEMICAL
Always thermal
Energy / propellant initially together
Energy source is combustion
Energy limited
Best propellants, Ue ~ 4,500 m/s
Isp ~ 100-500 s
Thrust ~ 0.1 N-10 MN
Propellant and Energy decrease with
MAE 4262: ROCKETS AND MISSION ANALYSIS
Orbital Mechanics and Hohmann Transfer Orbit Summary
Mechanical and Aerospace Engineering Department
Florida Institute of Technology
D. R. Kirk
REVIEW OF CONIC SECTIONS
ORBITAL MECHANICS: SUMMARY
Equation for conic s