Hybrid Rocket Combustion Process & Nozzle John Chambers.

Slides:

Advertisements

Similar presentations

The Third Law of Motion Section 3.

Advertisements

Example 3.4 A converging-diverging nozzle (Fig. 3.7a) has a throat area of m2 and an exit area m2 . Air stagnation conditions are Compute.

Analysis of Rocket Propulsion

Lecture #12 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1.

Operating Characteristics of Nozzles P M V Subbarao Professor Mechanical Engineering Department I I T Delhi From Takeoff to cruising …… Realizing New.

36th Annual Frontiers in Education Conference

Jet Engine Design Idealized air-standard Brayton cycle

Chap 5 Quasi-One- Dimensional Flow. 5.1 Introduction Good approximation for practicing gas dynamicists eq. nozzle flow 、 flow through wind tunnel & rocket.

Rocket Engines Liquid Propellant –Mono propellant Catalysts –Bi-propellant Solid Propellant –Grain Patterns Hybrid Nuclear Electric Performance Energy.

Review AE430 Aircraft Propulsion Systems Gustaaf Jacobs.

Thrust E80 Static Motor Test Spring Forces on a Rocket

Department of Mechanical Engineering ME 322 – Mechanical Engineering Thermodynamics Lect 27b Jet Aircraft Propulsion.

Example 3.1 Air flows from a reservoir where P = 300 kPa and T = 500 K through a throat to section 1 in Fig. 3.4, where there is a normal – shock wave.

Chemistry of Fire.

Hybrid Propulsion System Basics

Rockets and how they work

Uncontrolled copy not subject to amendment Rocketry Revision 1.00.

Discovery of A Strong Discontinuity P M V Subbarao Associate Professor Mechanical Engineering Department I I T Delhi A Break Through Finding To Operate.

Rocket Nomenclature EGR 4347 Analysis and Design of Propulsion Systems.

Introduction to Hypersonic Propulsion Systems

Class 4: Fundamentals of Rocket Propulsion

HTPB Fuel Grain Flow Rate, Sizing, and Thrust. Regression Rate Governs Size The faster the solid propellant is burned, the “fatter” the rocket must be.

The Thrust Generator P M V Subbarao Professor Mechanical Engineering Department Another Passive Device…… An Obvious Concept for Generation of Motive Power.

C & CD Nozzles for Jet Propulsion

MAE 4262: ROCKETS AND MISSION ANALYSIS

AE 1350 Lecture Notes #13.

MAE 4261: AIR-BREATHING ENGINES Exam 2 Review Exam 2: November 18 th, 2008 Mechanical and Aerospace Engineering Department Florida Institute of Technology.

1 CONCEPTION OF MINICHANNEL AS THE SOURCE OF SELF-IGNITION AT HIGH SUPERSONIC SPEED Goldfeld М.А., Starov А.V., Timofeev К.Yu. Khristianovich Institute.

Rocket Engine Physics and Design

Stagnation Properties P M V Subbarao Professor Mechanical Engineering Department I I T Delhi Capacity of A Resource…..

36th Annual Frontiers in Education Conference

Means to Create A Jet P M V Subbarao Professor Mechanical Engineering Department Viable ways of Creating Strong and Reliable Muscles for the Aircraft……

EXTROVERTSpace Propulsion 02 1 Thrust, Rocket Equation, Specific Impulse, Mass Ratio.

Quasi - One Dimensional Flow with Heat Addition P M V Subbarao Professor Mechanical Engineering Department I I T Delhi A Gas Dynamic Model for Combustion.

HYBRID ROCKET PROPULSION SYSTEMS BY: MCDOG SNIZZY ALLEN A.K.A SHAWN.

CP502 Advanced Fluid Mechanics Compressible Flow Lectures 5 and 6 Steady, quasi one-dimensional, isentropic compressible flow of an ideal gas in a variable.

One Dimensional Flow of Blissful Fluid -III P M V Subbarao Professor Mechanical Engineering Department I I T Delhi Always Start with simplest Inventions……..

Gas Dynamics of Variable Area Ducts P M V Subbarao Professor Mechanical Engineering Department I I T Delhi Development of Efficient and Compact Passive.

Design of Supersonic Intake / Nozzle P M V Subbarao Associate Professor Mechanical Engineering Department I I T Delhi Meeting the Cruising Conditions…

VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY

Rocket Science Modeling the motion of a small rocket using a spreadsheet.

Lecture #10 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1.

Design and Performance Analysis of a Hybrid-Motor Powered Model Rocket Ted Kapustka 15 Mar 2011 Photographs from

Solid Rocket Motors A solid rocket motor is a system that uses solid propellants to produce thrust Advantages High thrust Simple Storability High density.

MAE 4261: AIR-BREATHING ENGINES

1 SOLID PROPELLANT ROCKETS Solid fuel rockets rely on controlled explosion of a mixture of substances Nearly a homogeneous material that is burned Similar.

Fanno Flow -1 School of Aerospace Engineering Copyright © 2001 by Jerry M. Seitzman. All rights reserved. AE3450 Fanno Flow - Thermodynamics Steady, 1-d,

Shock waves and expansion waves Rayleigh flow Fanno flow Assignment

Flame Propagation and Stability Unit

THE TSIOLKOVSKY ROCKET EQUATION

Design and analysis of Parabolic nozzle using MOC and CFD

One Dimensional Flow of Blissful Fluid -III

Ramjets By Robert Espey.

MAE 5380: AIR-BREATHING ENGINE INLETS

Design and analysis of a Scramjet combustion Chamber

Gas Dynamics for Design of Nozzles

Figure 2.9 T-s diagram for converging only nozzle

Design of Passive (Adiabatic) Control Volumes

Rocket Engines Liquid Propellant Solid Propellant Hybrid Nuclear

ROCKETS AND MISSION ANALYSIS

Development and Principles of Rocketry

John Beasley 1/31/2008 Propulsion Group: Solid and Hybrid Profiles

John Beasley 3/20/2008 Propulsion Group Contact: Black Boxes and Code Flowchart AAE 450 Spring 2008.

MAE 5380: ROCKETS AND MISSION ANALYSIS

Jet Aircraft Propulsion

Rocket Physics Production of Thrust

Rocket Physics The Rocket Nozzle

Analysis & Selection of Design Space for Turbofan

27. Compressible Flow CH EN 374: Fluid Mechanics.

Presentation transcript:

Hybrid Rocket Combustion Process & Nozzle John Chambers

Hybrid Combustion Oxygen disassociates from Nitrogen in an exothermic process Gaseous oxygen is now present and rapidly combusts the solid fuel Combustion products are mainly CO 2 and H 2 0 Flame Temperature ~3300 K Fuel Grain Wall Temperature ~1000 K Nozzle Throat Temperature ~3000 K

Nozzle The function of the nozzle is to accelerate the combustion products to very high speeds and expel them to produce thrust Thrust = mass flow rate * exit velocity +(exit pressure – back pressure) * area

Nozzle Composed of a subsonic and a supersonic nozzle, connected at the nozzle throat The flow must reach Mach 1 at the throat

Nozzle Design Method of characteristics is used to design a nozzle of minimum length for shock-free, isentropic flow

Nozzle Materials The combination of high temperature and high velocity flow will quickly erode nearly all materials Graphite is one of the few materials that will stand up to these conditions for more than a few seconds Throat erosion will alter the geometry of the nozzle and cause poor performance

References Nozzle diagram: –