An interactive computer code for preliminary design of solid propellant rocket motors

  • 91 Pages
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  • English
by
ContributionsNetzer, David Willis, 1939-
The Physical Object
Pagination91 p.
ID Numbers
Open LibraryOL25453730M

An interactive computer code for preliminary design of. As a first attempt to predict the performance of solid rocket motors using functionally graded propellants, a computer code as been written that tries to take into account all of the problems that codes that predict performance of conventional solid propellants do not.

Since this ballistics code is to be used as part of larger IDP, care must be Cited by: 6. Solid propellant rocket motors. Chapter. k Downloads; Part of the Springer Praxis Books book series (PRAXIS) Keywords Aerospace Technology Grain.

A modular computer program for prediction of internal ballistic performances of solid propellant rocket motors SPPMEF has been developed. The program consists of following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motor), GEOM (This module consists of two parts: a part for dimensioning the.

The Solid Performance Program (SPP) has become the standard reference computer program throughout the United States for predicting the delivered performance of solid propellant rocket motors.

Solid Rocket Motor Internal Ballistics Simulation Considering Complex 3D Propellant Grain Geometries: /ch Solid rocket motors (SRM) are extensively employed in satellite launchers, missiles and gas generators. Design considers propulsive parameters with.

Description An interactive computer code for preliminary design of solid propellant rocket motors PDF

inert components of solid propellant rocket motors, namely the motor case, nozzle, and igniter case, and then discuss the design of motors. Although the thrust vector control mechanism is also a component of many rocket motors, it is described separately in Chapter The key to.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Functionally Graded Solid Rocket Propellants are being developed at NSWC-Indian Head in conjunction with the University of Maryland.

The approach being used treats these propellants as typical Functionally Graded Materials (FGMs), which by definition are structures that possess gradual variations in material behavior that enhance material and/or structural performance.

Conceptually, solid rocket motors (or SRMs) are simple devices with very few moving parts. An electrical signal is sent to the igniter which creates hot gases which ignite the main propellant grain (see image below).

The propellant contains both fuel and oxidizer; therefore these devices can operate in the vaccuum of space. Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection An interactive computer code for preliminary design of solid propellant rocket motors.

During the past 20 years, requirements on performance, reliability and cost of solid propellant rocket motors (and also on schedules and cost of development) have become more and more stringent. This, in turn, has a direct effect on solid propellant grain design methods and procedures, and on development program content.

directly in the combustion chamber [5]. Since the solid propellant both includes fuel and oxidizer, solid propellant rocket motors can operate in all environmental conditions.

In comparison to other types of rockets, solid propellant rocket motors have simple design, are easy to. an interactive computer code for preliminary design of solid propellant rocket motors.

unclassified it 2 personal author(s) yuan, chung-i. q 13a type of report 13b time covered date of report (year, month, day) 15 page count master's theis from to _ decmber 92 supplementary notation.

Abstract. The solid-propellant rocket motor brings the flight mission capability of high thrust delivery over a short duration. Design issues, such as tailoring the shape of the solid propellant grain (charge) to produce a desired thrust-time profile, are discussed in some detail in this chapter.

This chapter presents the safety characteristics of solid propellants and hazards of solid rocket motors. During the course of their entire life cycle, from production to utilization, solid propellant rocket motors are found in many varied environments and are subjected to stresses corresponding to a series of various activities.

Solid Rocket Motor (SRM) based solid propellant. This project focus on and discusses the study of optimum design based SRM characteristics including the methods of the optimum design selection and fabrication, analysis using COSMOS and static thrust fundamental of solid rocket.

CHAPTER 15SOLID ROCKET MOTOR COMPONENTS AND DESIGN This is the last of four chapters on solid propellant rocket motors. Here, we describe key components such as the motor case, - Selection from Rocket Propulsion Elements, 9th Edition [Book]. The solid propellant is storable, and is relatively safe to handle; no propellant delivery system is required, and this produces a huge improvement in reliability and cost.

There are two main disadvantages: the motor cannot be controlled once ignited (although the thrust profile can be preset), and the specific impulse is rather low because of. computer codes, based on analytical models or diagrams that give simple first results.

Second level is level of final design of propellant charge. Tools for this task are more refined and these are handled by experts for propellant grain design.

Details An interactive computer code for preliminary design of solid propellant rocket motors PDF

Computer codes are based on finite difference methods or finite element methods, with 1D. to development of the large solid-rocket motors on Titan 3 and Titan 4 rockets and the solid-rocket boosters on the Space Shuttle. 14 Figure 2 shows a Titan 3E launch vehicle, and Figure 3 shows the Space Shuttle.

Other Developments and Key Questions Many more discoveries were behind these large solid-rocket developments than just these propellant. On this slide, we show a schematic of a solid rocket engine.

Solid rocket engines are used on air-to-air and air-to-ground missiles, on model rockets, and as boosters for satellite launchers. In a solid rocket, the fuel and oxidizer are mixed together into a solid propellant which is packed into a solid cylinder. A hole through the cylinder serves as a combustion chamber.

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tively simple solid propellant rocket motors. The grain is the solid body of the hardened propellant and typically accounts for 82 to 94% of the total motor mass.

Design and stresses of grains are described later in this chapter. Propellants are described in the next chapter. The igniter (electrically activated). A solid-propellant rocket or solid rocket is a rocket with a rocket engine that uses solid propellants (fuel/oxidizer).The earliest rockets were solid-fuel rockets powered by gunpowder; they were used in warfare by the Chinese, Indians, Mongols and Persians, as early as the 13th century.

All rockets used some form of solid or powdered propellant up until the 20th century, when liquid. This study is devoted to present an internal ballistics model for a solid propel-lant rocket motor during the entire combustion of the propellant, i.e., to design and develop a solid propellant rocket motor using a numerical tool, ANSYS FLU-ENT, which creates.

an preliminary sizing of the rocket and access the possible design trade-offs in order to maximize its performance under some criteria. History of Rockets Modern rockets are the result of more than two thousand years of experiences, failures and inventions.

The first reported device to use rocket propulsion was developed in the 4th century. Developing an optimum performance for rocket motors by two primary objectives first to theoretically analyze the operation of small solid propellant rocket motor and to conduct testing with which to compare the theoretical result.

Scope i. Design of a rocket motors (including the COSMOS’s analysis) ii. Fabricate the rocket motors iii. In the design and development of solid propellant rocket motors, an accurate and reliable internal ballistics model provides a physical understanding of the main internal ballistic driving.

This is Volume III of a three-part manual which describes a computer program for the prediction of Solid Propellant Rocket Motor Performance. The computer program described herein will be referred to as the SPP program.

Volume I of this report describes the engineering analysis which was used in developing this computer program. Solid-propellant rocket motor ballistic performance variation analyses the assessment of off-nominal internal ballistic performance including tailoff and thrust imbalance of two large solid-rocket motors (SRMs) firing in parallel.

The revised Monte Carlo and design analysis computer programs along with instructions including format. Solid rocket motors are made with diameter of 10cm to cm or more with various port configurations. Essentially a solid propellant rocket motor consists of a rigid case, an internally bonded insulation with liner, igniter, solid propellant and nozzle.

The propellant in large motors is adhesively bonded to the.An experimental investigation of unstable combustion in solid propellant rocket motors. ARS Progress in Astronautics and Rocketry: Solid Propellant Rocket Research, Vol.

1,p. Peterson J. S., Bartholomae R. C. Design and instrumentation of a large reverberation chamber. Proceedings on Noise-Con,p. Designing Your Own Model Rocket 5 Design Options Clustering Clustering, or using two or more rocket motors at once, allows you to lift heavier rockets and payloads off of the ground.

Clustering black powder motors requires a launch controller that supplies at least 12 Volts DC (VDC) to the igniters to ensure all of the motors ignite at the same.