bluuebunny/crossref_metadata_2025_split huggingface dataset:
Missions to Dynamic Environments
Authors: Russell Ryan P. 
Published: December 2010

AbstractFrom planets to planetary satellites to comets and asteroids, the solar system beyond the Earth's immediate environment is rich with potential targets for space science missions. The exploration of such exotic space destinations requires a deep understanding of their surrounding dynamic environments. In this chapter, a survey of the dominant perturbations in the dynamical environments of high priority targets is given in the context of the orbit mechanics and preliminary design techniques of past, present, and future missions. The chapter is organized around the three dominant non‐Keplerian perturbations and their respective roles in missions that target three general classes of celestial bodies. The dominant perturbations are non‐spherical gravity, third body gravity, and solar pressure radiation while the bodies are generally classified as planets, large planetary satellites, or small bodies consisting of comets, asteroids, and small planetary satellites. A main contribution is a mission design reference that quantifies the relative importance of these perturbations providing a quick calibration of the dynamic environments of potential target bodies. Mission classes and design techniques considered include low‐ and high‐altitude orbiters, grand tour trajectories, patched conics, gravity assisted flybys, Tisserand graphs, three‐body models, periodic orbits, orbit averaging, and stable/unstable manifold design.
Attitude Dynamics Fundamentals
Authors: Schaub Hanspeter 
Published: December 2010

AbstractThe rotational motion of a rigid body or system of rigid bodies is a fundamental field for the study of spacecraft pointing problems. This chapter presents the fundamental aspects of describing the orientation, angular momentum, energy and differential equations of motion of a rigid body. After discussing the rigid body kinematics, the inertia properties of a body about arbitrary reference points are developed. The angular momentum and energy of a rigid body are critical to discussing the equations of motion, as well as investigating the stability of torque‐free spin solutions. Next, passive methods of attitude stabilization are discussed. Here the spacecraft angular momentum, or external torques such as the gravity gradient torque, are used to stabilize the orientation. These fundamental kinematics and kinetics properties form the foundation for follow‐on chapters discussing more complex pointing scenarios including systems with multiple rigid bodies (reaction wheels, etc.), attitude estimation, as well active attitude pointing problems.
Sensors for Attitude Determination
Authors: Pittelkau Mark E. 
Published: December 2010

AbstractThe various types of attitude sensors and inertial sensors used on spacecraft are presented, including their principle of operation, how they are used, and what accuracy can be expected from the sensors. Attitude sensors include sun sensors, Earth horizon‐sensors, star trackers, and magnetometers. Intertial angular rate sensors include spinning mass gyros, dry‐tuned rotor units, hemispherical resonator gyros, ring‐laser gyros, interferometric fiber optic gyros, and angular displacement sensors.
Statistical Attitude Determination
Authors: Markley Francis Landis 
Published: December 2010

AbstractStatistical attitude determination methods combine, in some optimal sense, the information included in a set of observations containing more than the minimum amount needed to determine a spacecraft's attitude uniquely. Single‐frame methods use observations made at a single point in time, a notable example being a set of unit vectors to stars imaged by a star tracker. The most widely employed single‐frame methods, such as the QUEST algorithm, satisfy an optimality criterion proposed by Wahba. Sequential methods, on the other hand, use spacecraft dynamics knowledge to combine the information from observations made over an extended period of time. Sequential methods generally provide more accurate attitude estimates than can be obtained by single‐frame methods, and are capable of providing estimates when insufficient information is available at a single time for single‐frame estimators to provide any solution at all. The most common sequential estimator is the extended Kalman filter, especially in the multiplicative form employing the quaternion representation of the attitude and a minimal three‐component representation of attitude errors.
Meteorology
Authors: Bedard Alfred. J. 
Published: December 2010

AbstractThis chapter reviews impacts on aircraft posed by a variety of atmospheric phenomena covering a large range of altitudes, scale sizes, and origins. Such weather hazards can be regional, long‐duration fields of turbulence or, on the other hand, concentrated, short‐duration microbursts. Accident statistics indicate the frequency and severities of encounters with various types of weather. A review of key weather features describes physical processes involved. Methods for prediction and warning discussed suggest hazard mitigation approaches and areas of need for further research.
Launch Environment
Authors: Aglietti Guglielmo S. , Richardson Guy , Quill Padraig. 
Published: December 2010

Abstract
The structural design of spacecraft is mainly driven by their necessity to survive the launch environment and, in mechanical terms, this consists of low frequency vibrations and steady accelerations, combined with random vibrations, acoustic loads, and shocks. The purpose of this chapter is therefore to describe sources and nature of the mechanical loading produced by the launch vehicle, and how these are translated into a “mechanical environment” that has to be withstood by the satellite. In particular, the typical requirements and specification imposed by the launch agencies are presented together with an overview of the test methods that are typically employed to insure compliance with these requirements.
Spacecraft End‐of‐Life Disposal
Authors: Ailor William 
Published: December 2010

AbstractThere is general recognition that space debris, non‐functioning human‐made objects in Earth orbit, will have long‐term effects on satellite operations. As a result, there are increasing calls for slowing the growth of the debris population by limiting debris released during normal satellite deployment and operations, minimizing on‐orbit explosions and breakups, preventing collisions of space objects, and disposing of space hardware at end‐of‐mission. This chapter discusses the latter option: disposing of hardware, both satellites and launch vehicle stages, at end of mission. Disposal options depend on the object's orbit: for example, objects in or passing through low earth orbits may be disposed by allowing orbits to naturally decay within a fixed time limit (hazards posed by debris surviving such reentries can eliminate this option), and objects in geosynchronous orbits should be moved to a disposal orbit several hundred kilometers above that region. This chapter describes the disposal options available for satellites and launch vehicle stages in each orbit regime. Related topics include: techniques for estimating the hazard posed by reentry of space hardware and designing space hardware to minimize reentry hazards, depletion of energy sources (passivation) prior to end‐of‐life to prevent on‐orbit explosions, and disposal techniques that may be available in the future, such as space tugs, electrodynamic and momentum exchange tethers, and drag‐enhancing devices to speed orbit decay.
Machining Aerospace Materials
Authors: Ridgway Keith , Turner Michael. S. , Sharman Adrian. R. C. , Hughes James , Chapman Tim , Durante Sergio 
Published: December 2010

Abstract
The aerospace industry is driving the use of advanced materials such as titanium and heat‐resistant nickel alloys and composites, and demand for large monolithic parts. The desirable properties of these materials also make them difficult to machine, presenting problems such as rapid tool wear and chatter. This chapter surveys the problems of machining these difficult‐to‐cut aerospace materials, with a focus on titanium alloys. Cutting theory is introduced, and common problems and their causes are explained. The mechanisms of tool wear and failure are examined. The chapter outlines machining strategies to avoid these problems, with consideration of a range of tool and cutting parameters.
Applied Aerodynamics and Propulsion Foundations – Fixed Wing Vehicles
Authors: van Tooren Michel , Rao Arvind G. , Obert Ed , van Buijtenen Jos 
Published: December 2010

AbstractAerodynamics and propulsion are probably the most important elements in aircraft design. While aerodynamics is mainly used to shape the aircraft such that it can fulfill all the mission requirements with minimum drag penalty, the aim of the propulsion system is to provide the required amount of thrust to the aircraft under all conditions. This chapter describes general considerations that are taken into account while designing the external shape of an aircraft and selecting the propulsion system for the aircraft. The basic physical phenomenal and the design variables and methods for aircraft design are described. The influence of the flight Mach number on the design variables has been explained. The various considerations involved in making the appropriate choice of the propulsion system are described, with more emphasis on gas turbine engines. The gas turbine system power and efficiencies have been mentioned. The various gas‐turbine‐based aircraft engine configurations have also been described.
Applied Aerodynamics and Propulsion Foundation Rotary Wing
Authors: van Holten Theo , Pavel Marilena D. 
Published: December 2010

AbstractRotary wing aerodynamics is a challenging subject because of the compound complexity of the flow passing through the rotor. The present chapter discusses the aerodynamics of hovering and forward flight. Basic theories such as actuator disc theory (momentum theory) and blade element theory are put into light. More detailed models for hover and forward flight including the prescribed wake models and free wake models are discussed qualitatively.
Fixed‐Wing Aircraft Performance
Authors: Ruijgrok Ger J.J. , Voskuijl Mark 
Published: December 2010

AbstractThis chapter deals with aircraft performance, that is, the capability of aircraft to execute certain maneuvers and to meet mission requirements. Aircraft performance is based on the study of the forces acting on an aircraft and the effects that these forces have on its flight path. The resulting motions are grouped into four main classes: (i) accelerated curved symmetric flight; (ii) steady straight symmetric flight; (iii) accelerated straight symmetric flight; and (iv) non‐symmetric flight. The basic forces are weight, thrust, and aerodynamic force (lift and drag). Additionally, in curved flight a centrifugal force appears. Presented are a few of the most important key performance measures of fixed‐wing aircraft together with approximate equations that have been used in aeronautics to assess such performance in the early design stage of an aircraft. Range and endurance expressions are derived and attention is given to the weight breakdown and payload‐range relationship for transport aircraft.
Performance of Rotary Wing Vehicles
Authors: Pavel Marilena D. 
Published: December 2010

Abstract
Rotary wing aircraft and especially helicopters are relatively slow machines that normally fly at altitudes below 3000 m. The continual advances in the fields of smart rotor design, lightweight structures and integrated flight management and avionics systems, alongside improvements of the fuselage aerodynamics and the advances recorded in engine efficiency have resulted in an incredible improvement of the performance of modern rotary wing configurations, compared with 20, 30, and 40 years ago. The present chapter reviews specific methods to calculate the helicopter performance and discusses key helicopter performance characteristics. The chapter includes issues related to both “classical performance” (i.e., how fast, how far, how high and with how much payload a rotorcraft can operate) and “environmental performance” (i.e., how easy and how comfortable it is to fly and maintain, how safe is the rotorcraft).
Materials, Structure, and Dynamics of Insect Wings as Bioinspiration forMAVs
Authors: Combes Stacey A. 
Published: December 2010

AbstractInsect wings are complex, deformable structures that change shape dynamically during flight. Muscles are restricted to the wing base – thus, shape changes are largely passive, determined by the interaction between the wing's architecture and the aerodynamic and inertial forces associated with flapping flight. Because insect wing structure reflects numerous evolutionary trade‐offs and constraints, no single wing represents the “optimal” design for flight, but particular features may enhance certain aspects of flapping flight performance. Wings are primarily composed of tubular supporting veins and deformable membranes, with diverse material and structural properties. Venation pattern and planform shape vary widely, and wings display three‐dimensional corrugation, camber, and twist. Specialized features such as flexion lines, one‐way hinges, patches of rubber‐like protein, and inertial balancers contribute to patterns of wing deformation during flight. Spatial variation in mechanical properties and “smart” structures promote and control dynamic camber generation, transverse bending, and torsional waves. The effects of wing structure and dynamic shape changes on unsteady aerodynamic force production remain unknown, and their exploration requires the development of novel experimental tools.
MAV Guidance Inspired by Principles of Insect Vision
Authors: Srinivasan Mandyam V. , Thurrowgood Saul , Soccol Dean 
Published: December 2010

AbstractThe study of visually guided flight in insects is offering novel, computationally elegant solutions to challenges in machine vision and robot navigation. Insects are remarkably adept at seeing and perceiving the world and navigating in it, despite possessing a brain that weighs less than a milligram and carries fewer than 0.01% as many neurons as ours does. Although most insects lack stereo‐vision, they use a number of ingenious strategies for perceiving their world in three dimensions and navigating successfully in it. For example, distances to objects are gauged in terms of the apparent speeds of motion of the objects' images, rather than by using complex stereo mechanisms. Narrow gaps are negotiated by balancing the apparent speeds of the images in the two eyes. Flight speed is regulated by holding constant the average image velocity as seen by both eyes. Bees landing on a horizontal surface hold constant the image velocity of the surface as they approach it, thus automatically ensuring that flight speed is close to zero at touchdown. This chapter describes how some of the strategies described above are being used to design, implement, and test biologically inspired algorithms for the guidance of autonomous aerial vehicles.
Mechanics and Actuation for Flapping‐Wing Robotic Insects
Authors: Wood Robert J. , Whitney John P. , Finio Benjamin M. 
Published: December 2010

AbstractTechniques for modeling, design, fabrication, and analysis of the mechanics and actuation for a flapping‐wing robotic insect are presented. Passive dynamics can be exploited to efficiently generate wing motions that closely resemble those of hovering insects. These microrobotic structures are enabled by high‐performance piezoelectric actuators and a novel method to produce layered composite flexure‐based articulated mechanisms. By careful design and fabrication, this Chapter concludes by demonstrating an insect‐inspired thoracic design that can asymmetrically modulate wing motions in order to generate controlled body torques.
Spacecraft Technologies: Satellite Reliability
Authors: Castet Jean‐Francois , Saleh Joseph H. 
Published: December 2010

AbstractReliability has long been recognized as a critical design attribute for space systems. Since physical access to these high‐value assets is difficult or impossible, maintenance cannot be relied upon to compensate for substandard reliability. It is therefore imperative to design high reliability into satellites. Statistical analysis of flight data, in particular of actual on‐orbit failure data, would provide particularly useful feedback to spacecraft designers. For example, such analysis can help guide satellite test and screening programs and provide an empirical basis for subsystem redundancy and reliability growth plans.This chapter provides a nonparametric statistical analysis of satellite reliability. Parametric fits using a Weibull and mixture distributions are also provided and discussed. The relative contribution of each subsystem to the failure of satellites is quantified, and the “culprit” subsystems driving unreliability are identified.
Electromagnetic Hazard Vulnerability Verification
Authors: Wraight Anthony 
Published: December 2010

AbstractThe effects of electromagnetic (EM) hazards on aircraft have been understood since the early 1930s when early communication systems were affected by engine interference. Since then, the level of understanding of the issue has been developed significantly and, particularly with the introduction of fly‐by‐wire aircraft, the potential of significant aircraft failure as a result of EM hazards has increased. This chapter discusses the methods available for the assessment of aircraft vulnerability to EM hazards. Details are given on low‐ and high‐level techniques that provide an indication of the severity of the hazard with respect to the aircraft of interest and an indication of its vulnerability. This chapter also discusses the issues of applying these methods to large aircraft.
Product Lifecycle Engineering (
PLE
): An Application
Authors: Schrage Daniel P. 
Published: December 2010

Abstract
Product Lifecycle Engineering (PLE) is the application of Systems Design and Analysis (SDA) to the Systems Engineering (SE) activities during the various phases along a system/product lifecycle. SE is an interdisciplinary approach and means for enabling the realization and deployment of successful systems. Systems engineers deal with whole systems having many separate contributing components/parts. They rely on other engineers to design, analyze, and deliver the individual components/parts which together make up the whole system. The SE effort spans the whole system lifecycle. SE focuses on defining customer needs and required functionality early in the development cycle, documenting requirements, and then proceeding with design synthesis and system validation while considering the complete problem from cradle to grave. This chapter will address PLE during the critical transition from product development to production where necessary Integrated Design and Manufacturing (IDM) tradeoffs are made. The redesign of the wing of an F‐86 Strato Sabre Vintage Jet Fighter, as a case study example for IDM through Product Lifecycle Management (PLM), will be presented. A Georgia Tech Professional Education Certificate Program with a large aerospace company during 2008–2009 served as the basis for this case study example.
Computing Hardware Selection and Integration
Authors: Marshall Joseph R. 
Published: December 2010

AbstractToday's modern aerospace systems utilize significant proportions of embedded computing hardware. The amount and complexity of this hardware and the embedded software that run on this hardware has increased significantly over the past decades in order to better sense the environments and control the aerospace systems to accomplish the missions the systems are developed to meet. This chapter explores the selection of computing hardware from architecture to integration. It documents how a computing hardware element is specified, how it is architected into multiple approaches, how one approach is selected as a baseline, how that baseline is designed, analyzed, prototyped, reviewed, and released to fabrication, and then brought up, integrated, and tested. The approach covers areas of concern from the smallest elements of computing hardware logic to systems of computing hardware, including any needed test equipment. The selection and integration of computing hardware documented in this chapter continues to increase in its importance and contribution to the success of today's and future aerospace missions.
Aircraft Fuel Systems
Authors: Langton Roy , Clark Chuck , Hewitt Martin , Richards Lonnie 
Published: December 2010

Abstract

Aircraft Fuel Systems covers all aspects of the subject from the refuel source to the delivery of fuel to the engine or engines for both commercial and military aircraft including:

The refuel/defuel process and associated fuel storage issues

All aspects of fuel handling, fuel transfer and fuel feed systems

Fuel measurement and management systems

Aerial refueling systems

Fuel properties and fuel system components

Design practices associated with the protection of fuel systems from electromagnetic, electrostatic and lighting strike hazards

Fuel tank inerting systems

In addition the book describes the design, development and certification process including program management, risk management and mitigation and the application of modern design support tools.
The penultimate chapter contains several real world examples of aircraft fuel systems and the book concludes with a discussion of new and future technologies.
Environmental Control Systems
Authors: Lawson Craig P. 
Published: December 2010

Abstract
An aircraft environmental control system is tasked with maintaining on‐board conditions suitable for equipment operation, and comfortable for vehicle occupants. This chapter covers systems in use today to provide environmental control on aircraft, with both open loop air cycle and closed loop vapor cycle systems described. The major environmental control system components and sub‐systems are then considered in more detail. This includes humidity and pressure control components and principles of operation, ozone conversion performance, filtration of recycled cabin air, cold air units (bootstrap machines) operation and design, and the use of heat exchangers. Oxygen provision systems are also considered in the form of liquid oxygen (LOX) systems and on‐board oxygen gas generation systems (OBOGGS). This chapter culminates by bring many of the aforementioned sub‐systems and components together to present and describe an environmental control system that is typical of that used on many aircraft presently in‐service.
Introduction and Overview
Authors: Seabridge Allan 
Published: December 2010

Abstract
The modern aircraft – the platform, the major systems and its crew – are designed as a tightly integrated system. In this context the vehicle systems have their own specific integration issues, but they cannot be designed without due regard to the rest of the aircraft systems. There are interactions between systems and there are inter‐dependencies that must be considered during the design of the total platform in order that its fitness for purpose can be demonstrated to the satisfaction of the customer or the certification authority.
There are sound reasons for achieving integrated systems or products. The end result is often smaller or lighter, cheaper to manufacture, and perceived by users as being “neater”, more compact, and more user friendly. However, this integration has the potential to lead to a lack of visibility of the behavior of the total system and a lack of understanding of the emergent properties that arise from integration of complex systems and a complex human–machine interface.
These systems can have a severe impact on the performance, testing, and qualification. In this chapter, a number of aspects of integration factors that affect the whole aircraft are examined to determine the potential threat to performance, safety, integrity, and qualification.