Internal Aerodynamics in Solid Rocket Propulsion

468 Pages·2004·18.23 MB·English

NORTH ATLANTIC TREATY RESEARCH AND TECHNOLOGY
ORGANISATION ORGANISATION

www.rta.nato.int
AC/323(AVT-096)TP/70

RTO EDUCATIONAL NOTES EN-023 AVT-096
Internal Aerodynamics in
Solid Rocket Propulsion
(L’aérodynamique interne de la propulsion
par moteurs-fusées à propergols solides)
The material in this publication was assembled to support a RTO/VKI Special
Course under the sponsorship of the Applied Vehicle Technology Panel (AVT)
and the von Kármán Institute for Fluid Dynamics (VKI) presented on
27-31 May 2002 in Rhode-Saint-Genèse, Belgium.

Published January 2004

Distribution and Availability on Back Cover

NORTH ATLANTIC TREATY RESEARCH AND TECHNOLOGY
ORGANISATION ORGANISATION

www.rta.nato.int
AC/323(AVT-096)TP/70

RTO EDUCATIONAL NOTES EN-023 AVT-096
Internal Aerodynamics in
Solid Rocket Propulsion
(L’aérodynamique interne de la propulsion
par moteurs-fusées à propergols solides)
The material in this publication was assembled to support a RTO/VKI Special
Course under the sponsorship of the Applied Vehicle Technology Panel (AVT)
and the von Kármán Institute for Fluid Dynamics (VKI) presented on
27-31 May 2002 in Rhode-Saint-Genèse, Belgium.
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Published January 2004
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ISBN 92-837-1103-3
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ii RTO-EN-023
Internal Aerodynamics in
Solid Rocket Propulsion
(RTO EN-023 / AVT-096)
Executive Summary
Considerations of the optimal approaches to adapt space launchers to a changing market should lead to
significant breakthroughs in solid rocket propulsion technology, mainly in the areas of reduced costs and
improved performance characteristics. The goal of this NATO Research and Technology Organization
(RTO) sponsored lecture series was to provide a forum for the review of various scientific and industrial
aspects of solid rocket propulsion and an assessment of recent advances with emphasis on internal
aerodynamics. The present lecture notes are intended as a natural follow-up to the AGARD-LS-180
“Combustion of Solid Propellants” organized in 1991.
These RTO-AVT / VKI Special Course notes provide the state of the art in internal aerodynamics in solid
rocket propulsion, in a way accessible to attendees coming from both academic and industrial areas.
Two families of solid motors can be identified: tactical rockets and large boosters for launch vehicles.
The military rockets are subjected to combustion instabilities while vortex shedding drives the instabilities
in the large boosters. After an overview of the motor internal flow dynamics, combustion of solid
propellants and metal particulates were presented. Numerical modeling of internal flow aerodynamics,
two-phase flow and flow/structural interactions were addressed, before focusing on the motor flow and
combustion instabilities.
The main objective of these course notes is therefore to allow an information transfer between well-known
scientists, leaders in the solid propulsion field, and demanding industries and laboratories. For these
reasons, this proceeding appeals not only to experts already working in the domain, but also to newcomers
to the field.

RTO-EN-023 iii
L’aérodynamique interne de la propulsion par
moteurs-fusées à propergols solides
(RTO EN-023 / AVT-096)
Synthèse
La considération des approches optimales de l’adaptation des lanceurs spatiaux à un marché en pleine
évolution devrait conduire à des progrès décisifs dans le domaine des technologies de la propulsion par
moteurs-fusées à propergols solides, principalement du point de vue de la diminution des coûts et de
l’amélioration des caractéristiques de performance. Ce Cycle de conferences, organisé par l’Organisation
OTAN pour la recherche et la technologie (RTO) a eu pour objectif de servir de forum pour l’examen de
différents aspects scientifiques et techniques de la propulsion par moteurs-fusées à propergols solides,
ainsi que pour l’évaluation des derniers progrès réalisés, en particulier en aérodynamique interne. L’actuel
support de cours représente la suite naturelle du cycle de conférences AGARD-LS-180 sur « La
combustion des propergols solides » organisé en 1991.
Ce support de cours spécial RTO-AVT/VKI présente l’état actuel des connaissances dans le domaine de
l’aérodynamique interne de la propulsion par moteurs-fusées à propergols solides, de manière à rendre le
sujet accessible à des participants venant aussi bien de l’industrie que des universités. Deux grandes
familles de moteurs-fusées à propergols solides sont à distinguer : les fusées tactiques et les grandes fusées
d’appoint pour lanceurs. Les fusées militaires sont sujettes à des instabilités de combustion, tandis que les
instabilités des grandes fusées d’appoint sont occasionnées par le décollement des tourbillons. Suite à un
aperçu de la dynamique des écoulements internes des moteurs, la combustion des propergols solides et des
particules métalliques a été présentée. La modélisation numérique de l’aérodynamique des écoulements
internes, ainsi que les interactions des écoulements bi-phase et des écoulements/structures ont été
examinées, avant de considérer les flux internes des moteurs et les instabilités de combustion.
Ce support de cours a donc pour objectif de permettre un échange d’informations entre des scientifiques
renommés, éminents dans le domaine de la propulsion par propergol solide, et les industries et les
laboratoires qui s'intéressent à leur travail. Pour ces raisons, ces documents seront appréciés non seulement
par les spécialistes du domaine, mais aussi par les néophytes.
iv RTO-EN-023
Table of Contents
Page
Executive Summary iii
Synthèse iv
List of Authors/Lecturers vi
Reference
Introduction to Solid Rocket Propulsion 1
by P. Kuentzmann
Overview of Motor Internal Flow Dynamics 2 †
by V. Yang
Flow-Structural Interaction in Solid Rocket Motors 3
by J.W. Murdock and W.A. Johnston
Combustion of Solid Propellants 4
by G. Lengellé, J. Duterque and J.F. Trubert
A Summary of Aluminum Combustion 5
by M.W. Beckstead
Part I – Survey of Recent Al2O3 Droplet Size Data in Solid Rocket Chambers, 6 †
Nozzles, and Plumes
by M. Salita
Motor Flow Instabilities – Part 1 7
by F. Vuillot and G. Casalis
Motor Flow Instabilities – Part 2: Intrinsic Linear Stability of the Flow Induced by 8
Wall Injection
by G. Casalis and F. Vuillot
Numerical Modeling of Internal Flow Aerodynamics Part 1: Steady State Computations 9
by J-F. Guéry
Numerical Modeling of Internal Flow Aerodynamics Part 2: Unsteady Flows 10
by J-F. Guéry
Combustion Instabilities in Solid Propellant Rocket Motors 11
by F.E.C. Culick

† Paper not available at the time of publishing.

RTO-EN-023 v
List of Authors/Lecturers
Special Course Directors
Assis. Prof. Jérôme Anthoine Mr. Paul Kuentzmann
Assistant Professor ONERA/DSG
von Kármán Institute for Fluid Dynamics BP 72
chaussée de Waterloo 72 92322 Chatillon Cedex
1640 Rhode-Saint-Genèse FRANCE
BELGIUM email: [email protected]
email: [email protected]
Lecturers
Mr. Grégoire Casalis Prof. Fred E.C. Culick
ONERA Toulouse Caltech
BP 4025 Mechanical Engineering and Jet Propulsion
2 avenue E. Belin 1200 East California Blvd
BP 4025 Pasadena, California 91125
31055 Toulouse Cedex USA
FRANCE email: [email protected]
email: [email protected]
Dr. John W. Murdock
Dr. J-F. Guéry The Aerospace Corporation
SNPE Vehicle Performance Subdivision
BP 2 M4/964
9171- Vert-le-Petit PO Box 92957
FRANCE Los Angeles, CA 90009-2957
email: [email protected] USA
email: [email protected]
Mr. Guy Lengellé
ONERA Energetics Mr. M. Salita
Centre de Palaiseau TRW
Chemin de la Thumière 875 S 2000 E
91120 Palaiseau Cedex Clearfield, UT 84414
FRANCE USA
email: [email protected] email: [email protected]

Dr. F. Vuillot Prof. Vigor Yang
ONERA The Pennsylvania State University
BP 72 Department of Mechanical Engineering
93222 Chatillon Cedex 104 Research Building East
FRANCE University Park, PA 16802
email: [email protected] USA
email: [email protected]
Prof. Merill Beckstead
Brigham Young University
Dept of Chemical Engineering

Provo, UT 84062

USA
email: [email protected]

vi RTO-EN-023
Introduction to Solid Rocket Propulsion
P. Kuentzmann
Office National d’Etudes et de Recherches Aérospatiales
29, avenue de la Division Leclerc – BP 72
92322 Châtillon Cedex
FRANCE
SUMMARY
The objectives of this introduction are to present the fundamentals of solid rocket motor (SRM), starting
from the elementary analysis of rocket operation and then justifying the need of sophisticated computation
of the internal flow. After a brief reminder of solid rocket history, a description of its main components is
proposed. The elementary parameters controlling the operation are introduced and the basic formula
predicting the steady-state operation pressure is established. The main issues faced by a SRM require an
accurate description of internal aerodynamics, either to predict the pressure/thrust programs and the
normal transient phases like ignition, or to study the motor stability. A short overview of the evolution of
the codes devoted to SRM internal aerodynamics during the last thirty years is given in order to introduce
the more specialized presentations; a discussion of the main limitations concerning these codes is also
proposed. The prospects offered by SRM internal aerodynamics codes are finally described.
1.0 GENERALITIES
1.1 History
The solid rocket motor belongs to the family of the rocket engine (thrust achieved by mass ejection)
and its history can be considered both ancient and recent. It is possible to consider that the black powder is
the precursor of modern solid propellants: composed of natural ingredients (sulfur, charcoal and salpetre),
the black powder has been used from the 13th century in Asia to propelled darts, certainly the first
unguided stand-off weapons. A lot of work has been performed since this time to improve the solid
propellant and to master its combustion but the main military application has been gun propellants up to
the WW2. The WW2 has seen the first aeronautical applications (BACHEM Natter, JATO, RATO).
The main developments for military (missiles) and space activities (launchers) started in 1945.
Regarding the space activities, the first flights were carried out by liquid propellant rockets, following the
world’s first successfully flown rocket on March 15, 1926 (R. Goddard, USA). The first satellites have
been put into orbit by a liquid propellant launcher (R7 Semiorka, October 1957); the first successful US
launch (Jupiter C, January 1958) used solid propellant rockets for the upper stages. The small US Scout
has been the first all solid propellant launcher. Most of the first intercontinental missiles or intermediate
range missiles used also liquid propellant engines, for their first generations.
The current situation is the following:
• Most of the modern strategic and tactical missiles use solid propellant propulsion. The only
competitor for solid propulsion is ramjet propulsion for tactical missiles.
• Space launchers are in the western countries and in Japan based on an assembly of liquid
and solid propelled stages; they remain all liquid propellant in Russia, Ukraine and China.
This difference of design is clearly connected to economical considerations: development and
Paper presented at the RTO/VKI Special Course on “Internal Aerodynamics in Solid Rocket Propulsion”,
held in Rhode-Saint-Genèse, Belgium, 27-31 May 2002, and published in RTO-EN-023.
RTO-EN-023 1 - 1
Introduction to Solid Rocket Propulsion
recurrent costs of a large solid propellant booster are lower than those of a large liquid propellant
booster in the western countries, agreed that performance is better for liquid propellant
propulsion. The orientation towards RLVs (Reusable Launch Vehicles) will favor of course liquid
propulsion in the future.
1.2 The Basic Solid Rocket Motor
A solid propellant rocket is formed by four main components (fig. 1):
• A case containing the solid propellant and withstanding internal pressure when the rocket is
operating.
• The solid propellant charge (or grain), which is usually bonded to the inner wall of the case,
and occupies before ignition the greater part of its volume. When burning, the solid propellant is
transformed into hot combustion products. The volume occupied by the combustion products is
called combustion chamber.
• The nozzle channels the discharge of the combustion products and because of its shape accelerates
them to supersonic velocity.
• The igniter, which can be a pyrotechnic device or a small rocket, starts the rocket operating when
an electrical signal is received.

Figure 1: Basic Solid Rocket Motor.
One can consider that the solid propellant after manufacturing is in a metastable state. It can remain inert
when stored (in appropriate conditions) or it can support after ignition its continuous transformation into
hot combustion products (self-combustion). The velocity of the transformation front is called burning rate
(fig. 2).

Figure 2: Solid Propellant Rocket Motor.
1 - 2 RTO-EN-023