火箭与太空发射器设计：第二版

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"Design of Rockets and Space Launch Vehicles" 是一本由Don Edberg和Willie Costa合著的书籍，第二版在2022年由美国航空航天学会(American Institute of Aeronautics and Astronautics, AIAA)出版。这本书专注于火箭与太空发射器的设计，涵盖了从基础理论到实际应用的广泛知识。书中内容可能包括但不限于以下几个核心知识点： 1. **火箭推进原理**：火箭工作的基础是牛顿第三定律，即“作用力与反作用力”。书中可能会详细解释如何通过燃烧推进剂产生高压气体，然后通过喷嘴排出，产生向上的推力。 2. **热力学与流体力学**：设计火箭时，必须理解热力学过程，如膨胀和压缩，以及流体动力学中的压力、速度和密度变化，这些对于优化火箭发动机性能至关重要。 3. **材料科学**：火箭需要承受极端的温度和压力，因此对材料的选择有极高的要求。书可能会讨论高温合金、复合材料等用于火箭制造的特殊材料。 4. **结构设计与稳定性**：设计稳定的火箭结构，确保在升空过程中抵抗空气动力学负荷和内部压力，是火箭工程的一大挑战。书中会涉及结构分析和稳定性计算。 5. **控制系统**：火箭的轨迹控制和姿态稳定是成功发射的关键。这可能涉及到导航、制导和控制系统的设计，以及火箭喷嘴的可调性。 6. **燃料与氧化剂**：不同的推进剂组合（如液氢/液氧、煤油/液氧等）有不同的性能特点，书会探讨如何选择和储存这些燃料。 7. **发射台和地面支持系统**：书中也会涵盖发射前的准备工作，包括火箭在发射台上的安全性和地面支持设备的运行。 8. **航天器分离与轨道插入**：一旦火箭达到足够的速度和高度，需要将有效载荷（如卫星或飞船）分离并送入预定轨道，这部分涉及复杂的动力学计算。 9. **安全与风险评估**：在火箭工程中，安全性是首要考虑因素。书中可能会讨论风险评估方法、应急系统和故障预防措施。 10. **环境影响与可持续性**：随着环保意识的提升，书中也可能讨论火箭发射对环境的影响，以及如何实现更可持续的太空旅行。 11. **案例研究与历史回顾**：通过回顾过去的成功和失败案例，读者可以更好地理解火箭设计的实践挑战和历史演变，例如SpaceX的Starship Super Heavy项目可能作为现代案例被提及。通过这本由行业专家编写的书籍，读者不仅能获得火箭和太空发射器设计的理论知识，还能了解到实际工程中的问题和解决方案，从而为未来的航天工程师提供宝贵的教育和参考资源。

topics or subjects; corrections or typographical errors, or other pertinent

information.

So now: “Launch is served!” Catherine Edberg, September 8, 2013.

About the book: DoRSLaVe is laid out in a sequence that mimics the par-

ticular sequence of events that might be used to develop the initial or concep-

tual design of a LV from scratch; exceptions are pointed in the summary of

contents of each chapter immediately below. The majority of chapters have

exercises or problems that are intended to highlight the major parts of the

chapters’ contents.

Chapter 1 provides a broad overview of the “world” of launch vehicles. It

provides basic information on what they are used for and the space industry

in general, basic launch vehicle layouts, and typical launch trajectories. We

then describe the design process with a flowchart which indicates the

sequence of events beginning with a set of mission requirements, then carry-

ing out initial vehicle sizing, aerodynamics, performance analysis, ground and

launch environment, structure, stability, and control analyses, design iter-

ations, and ending with a cost analysis. Finally, we present a list of the

world’s launch sites.

Chapter 2 is a background chapter



providing the technical history of

launch vehicles. Knowing this history provides background for current

design practices and also gives knowledge of the vast design space possible

for LVs. The chapter spans early history to the pre-WWII period, where

the Nazis developed the first ballistic missile, to the development of the

ICBM, its evolution into launch vehicles, the moon race, and the develop-

ment of more modern LVs. It ends with a survey of current LVs and some

future developments, including small LVs.

Chapter 3 begins the LV design process by considering how the LV’s

payload mass and orbital requirements will flow down to specify the perform-

ance of the LV. We include a brief explanation of common orbits and their

required orbital mechanics. With a specified orbit, we show how to calculate

the required LV shutdown performance in terms of shutdown speed and

direction. Then, the gravity, drag, and steering losses associated with the tra-

jectory must be vectorially added to the shutdown conditions to determine

the LV’s design speed. Finally, we discuss launch azimuth directions, orbit

injection strategies, and launch windows for both direct and indirect orbits.

Chapter 4 discusses rocket propulsion: how thrust is generated, how

the rocket’s performance is calculated, and different types and propellants

used. We provide details, advantages, and disadvantages of solid and liquid

propulsive methods, and some insights on the liquid propulsion ‘cycles’.

We also discuss hybrid rockets and aerospikes. This information is useful



By “background chapter,” we mean a chapter that is provided for background and historical pur-

poses. Typically these background chapters do not provide assignments at the end and are strictly for

educational purposes.

Preface to the First Edition xv

for understanding available propulsion options, and for selecting the propul-

sion system for a particular mission or requirement.

Chapter 5 is an important chapter on LV performance. We show that

there are just three parts of a rocket for performance calculations: payload,

propellant, and inert mass. The rocket equation is introduced, and we

discuss the need for multi-stage vehicles to achieve needed speeds. We

discuss theoretical optimization processes (where optimization here means

minimum mass to fly a specified payload) and “brute force” methods to opti-

mize. We consider the effect of different propellants to accomplish a specific

mission, and consider what an all-hydrolox Saturn V would have looked like

(compared to the existing version which used kerolox in its first stage). We

discuss and show how to analyze both serial and parallel staging methods,

and look at design sensitivities, which indicate the best places to add propel-

lant, reduce mass, and improve rocket performance. Finally, we provide a set

of useful formulas that will be used to calculate useful rocket parameters such

as propellant mass, structure mass, etc. for sizing purposes.

Once we have some idea of performance and staging requirements, we

look at trajectory analysis in . This chapter looks at vertical andChapter 6

inclined flight near bodies with and without an atmosphere. We introduce

LV aerodynamics and their effect on ascent. We show a simple way to do tra-

jectory simulations using a simple spreadsheet or numerical integration

approach. The elegant mathematics of trajectory optimization are intro-

duced, and various methods and techniques of optimization are demon-

strated by providing a number of examples of actual launch vehicle

trajectories.

Chapter 7 is a background chapter intended to provide a comprehensive

introduction to the structures and possible layouts that might be used

on various LVs with different propulsion systems. We present a number of

ICBMs that evolved into space launchers, as well as dedicated launchers

such as the Saturn family, the Space Shuttle and SLS, Atlas V, and Delta

IV. We discuss the geometry of tanks, domes, feedlines, and layouts and

their ramifications on layout. Finally, we present a survey of structure types

and commonly-used structural materials.

With structure and layout knowledge available, begins theChapter 8

physical layout process of the inboard profile of a LV and finishes with an

estimate of the LV’s mass, center of mass location, and mass moments of

inertia. First, the required speeds along with the rocket equation are used

to determine the ideal amounts of solid or liquid propellants needed to

accomplish the mission. Then, “real life” additions are made for factors

such as engine startup, unusable propellant, tank shrinkage, and so on.

The tanks or casings are sized to incorporate these factors, and guidelines

are given for interconnecting structure such as intertanks, interstages,

payload fairings, and thrust structures. Then, we illustrate the process of

mass estimation, and show how to calculate the LV’s center of mass (CM).

xvi Design of Rockets and Space Launch Vehicles

This is used to find the LV’s mass moments of inertia, which are critical to the

maneuvering and stability of a LV.

Chapter 9 introduces the calculation of aerodynamic loads on the LV’s

structure caused by ground winds on the pad, as well as crosswind “wind

shears” that strike the LV during ascent. We show how to estimate the mag-

nitude of the wind loads, their point of application, and how to “march” from

top to bottom of the launch vehicle to assess the shear and bending moment

distribution along the LV’s length, and the axial load distribution. As an

example, these processes are used to calculate the wind loads on a Saturn

V in flight during the max-q condition. We finish by discussing some “load

relief” techniques.

Chapter 10 continues with the calculation of stresses that are induced by

the aerodynamic loads from Ch. 9. After providing the terminology and defi-

nitions, we show how to calculate axial, shear, and bending stresses using the

simple cylinder analysis. We then consider structural stability or “buckling”

and show seven ways to improve stability. Pressurization has a strong

stabilizing and unloading quality that makes it ideal for LVs in flight. We

then show how to size the walls of the propellant containers and their

interconnecting structures.

Chapter 11 deals with the transient environments on board a LV

which include vibration and shock, acoustic, and thermal loading. We

discuss each of these environments and show where and when they are

most critical. Finally, we discuss the process of “coupled-loads analysis”

and the environment that the payload, the LV’s paying customer, will be

exposed to.

Chapter 12 is fairly involved exposition of LV stability and control, and

also a discussion of many interesting dynamical and stability problems that

can occur. We show how the LV knows at any given time where it is, what

direction it’s pointing, and how fast its direction is changing. With this

knowledge and the LV’s aerodynamic loading, we can predict the motion

of the LV. By gimbaling the engine(s) or using other control effectors, we

can “close the loop” and write the equations of motion to assess the LV’s stab-

ility and controllability. After this controls assessment, we consider several

instabilities that can occur, such as structure flexibility, “tail wags dog”

instability, propellant sloshing, and propulsion instabilities such as pogo

and resonant burn phenomena.

Chapter 13 is a background chapter providing information on the

process of LV manufacturing. We show examples of basic machining

needed to assemble LVs, and provide a detailed description of the fabrication

of the Saturn I’s S-IV second step, whose structure is primarily aluminum

alloys. We then consider composite materials such as fiberglass-epoxy and

graphite-epoxy structures and the techniques used to manufacture them.

Next, we consider advanced techniques such as filament winding, fiber pla-

cement, and additive manufacturing (AKA “3D printing”). Once the parts

Preface to the First Edition xvii

are manufactured, we discuss how the LV is assembled, also known as vehicle

“stacking”.

Launch vehicle systems and launch pad facilities are discussed in

Chapter 14, another background chapter. Here the Saturn V first step is

used to demonstrate many of the systems needed for a successful LV; as

the expression goes, “the devil is in the details.” Propellant management,

power, environmental controls, data management, telemetry, and many

other aspects of LVs are presented. We also provide ground accommodation

information, including pad services (holddowns, technician access, umbili-

cals, propellant storage, acoustic suppression, lightning protection, engine

startup sequence, and more).

Chapter 15 is a collection of information related to LV testing. We

show many of the types of testing that is done to best try to verify that the

vehicle will operate successfully, including mechanical, shock, vibration,

and acoustics; thermal; RF and electrical; wind tunnel testing on the

ground and in flight; and software testing procedures. We look at scale

model testing for launch pad acoustics and exhaust noise assessment.

Then we move on to discuss design procedures to improve reliability. Redun-

dancy is one method used; we show how to calculate reliability with series

and parallel connections, and we show reliability for ‘k-out-of-n’ systems,

applicable to multiple-engine LVs. Finally, we show the reliability of a LV

range-safety system with multiple failure probabilities.

Chapter 16 is background chapter which provides a number of examples

of LV failures in many disciplines, such as structures, separation systems,

propulsion systems, GN&C, and software. The text provides some lessons

learned and a number of suggestions on questions evaluators can ask to try

to prevent failures in future vehicles. We show how range safety is enhanced

by flight termination systems, and how those systems operate. We close with

a list of best practices to avoid failure.

Chapter 17 is the least “engineering” of the chapters in the book, and

also the last, but it’s certainly NOT the least! Economics of engineering and

systems is critically important in today’s world, and this chapter introduces

the principal aspects of launch vehicle economics. We begin by describing

the design cycle and how decision-making early in the cycle can be a “make-

or-break” contribution to the system’s overall costs. We discuss cost engineer-

ing and considerations that can affect it, and discuss cost estimation methods

through statistical fits and modelling. Finally, we provide some actual cost

modeling examples. Several exercises challenge the reader to estimate costs

on developing their own launch systems, and we provide access to an older

graphical but still useful cost estimating model.

A comprehensive Glossary provides a list of abbreviations and defi-

nitions, followed by an which completes the book.Index

Corrections and supplemental materials such as syllabi and curricula will

be available from AIAA’s electronic library, Aerospace Research Central

xviii Design of Rockets and Space Launch Vehicles

(ARC), at arc.aiaa.org: use the menu bar at the top to navigate to Books. AIAA

Education Series; then, navigate alphanumerically to this book title’s “landing

page.”

Suggested curricula for courses of different student level and duration:

The material in this book has been presented for two different types of

classes: a one-year long undergraduate senior capstone design class, and a

one-quarter-long or one-semester-long survey class. It has worked well for

both, but the scope of the class may be limited for the survey classes.

For the year-long course, we recommend going through the chapters in

numerical order, however the presenter may wish to cover Chapter 17

(cost analysis) before presenting Chapters 13–16 (which are primarily “back-

ground” chapters) so as to allow time for any Ch. 17 homework assignment to

be completed before the course ends. The assignments in Chapters 6, 9, and

10 are significantly time-consuming, so allotting extra completion time is

recommended.

For a survey course, the presenter should follow a similar schedule,

except the following chapters or sections may be omitted without too

much loss of content: 3.8, 4.8, 4.9, 5.8, 5.12, 10.6 (or its homework), 12.4,

12.5, Ch. 13, Ch. 14, 15.2, 16.5. Much of the omitted material is interesting

in its own right, and it should be suggested that the reader examine it on

their own time.

Suggested curricula for one- and two-semester versions of this course, as

well as class syllabi, may be found at the AIAA’s electronic library, listed above.

Disclaimer:

The material presented in this book has been carefully selected to

describe ideas and principles of rocket design and operation. However,

please note that none of the materials provided—engineering formulae,

data, material, results, or conclusions—can be absolutely guaranteed, even

though every effort has been made to insure accuracy and reliability. This

book may include technical inaccuracies as well as typographical errors.

The authors assume no responsibility for errors or omissions in this book,

or other documents which are referenced by or linked to this book. In no

event shall the authors be liable for any special, incidental, indirect, or con-

sequential damages whatsoever, including but not limited to, those resulting

from loss of use, data, or profits, and on any theory of liability, arising out of

or in connection with the use or reliance on this information.

THE FINAL RESPONSIBILITY OF VERIFYING ACCURACY AND

CORRECTNESS OF ANY AND ALL RESULTS REMAINS WITH THE

USER OF THE BOOK, and not with the authors.

Changes made to the information contained herein will be incorporated

in new editions of this book. The authors reserve the right to make improve-

ments and or changes in the book at any time without notice./

Preface to the First Edition xix

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