bluuebunny/crossref_metadata_2025_split huggingface dataset:
Materials Spaceflight Experiments
Authors: de Groh Kim K. 
Published: December 2010

AbstractSpace environmental effects on spacecraft materials can be severe due to individual and synergistic interactions of orbital environments such as solar ultraviolet radiation, charged particle radiation, temperature extremes and thermal cycling, impacts from micrometeoroids and orbital debris, environment induced contamination, and low Earth orbital atomic oxygen. Space environmental threats vary greatly based on spacecraft materials, thicknesses and stress levels, and the mission environment and duration. Materials spaceflight experiments have been conducted since the early 1970s to help understand the effects of the space environment on spacecraft materials, components and devices. Materials experiments have been flown on Skylab, Salyut and Mir, the space shuttle, and the International Space Station. In addition, there have been free‐flyer experiments such as the Long Duration Exposure Facility. In addition to being critical for understanding the engineering performance of materials exposed to specific space environments, data from spaceflight experiments can be used to determine correlations between exposures in ground‐test facilities and space, thus allowing more accurate in‐space materials performance predictions to be made based on ground‐facility testing. This chapter reviews most major materials spaceflight experiments along with some of the lessons learned from the experiments, and how the results have influenced materials use and selection.
Maneuver Performance of Fixed‐Wing Transport Aircraft
Authors: Young Trevor M. 
Published: December 2010

AbstractManeuver performance of fixed‐wing transport airplanes is discussed and methods for the analysis of the airplane during turning and pitching maneuvers is presented. General equations are developed for the analysis of the airplane in a level turn, and the factors that can limit the airplane's turn rate are discussed (e.g., available thrust, structural limits and maximum lift coefficient). The angle of attack limit for an airplane is associated with the stall condition, which depends on several factors, such as airplane configuration, weight, load factor and thrust setting. Several safety‐critical operational speeds are defined as a fixed multiple of the stall speed. For this purpose, a 1‐greference stall speed is defined. Whereas the stall condition sets a lower speed limit for the airplane, high speed buffet, which is a function of altitude, sets an upper speed limit. TheV–ndiagram, which depicts the airplane's limit load factor as a function of equivalent airspeed, provides engineers with the basis for determining the structural design loads, and it provides the limits within which the airplane can be safely operated. An outline of the methods used to construct aV–ndiagram, as described in the airworthiness regulations, is presented.
Maneuver of Fixed‐Wing Combat Aircraft
Authors: Render Peter M. 
Published: December 2010

AbstractThe importance of energy and specific excess power in assessing the maneuverability of combat aircraft is discussed. This is followed by a discussion on climb and turn performance, which extends the methods presented in other sections. In particular, high angle climbs and the climbing turn are considered. The use of performance metrics to assess aircraft performance is described, and both traditional (e.g., specific excess power plots) and new metrics (e.g., combat cycle time) are described. The article concludes by considering features which have been adopted on the latest combat aircraft, namely relaxed stability, the canard configuration and thrust vectoring.
Rotary‐Wing Static Stability
Authors: Lee David A. 
Published: December 2010

Abstract
The static stability of a rotary‐wing aircraft is established by observing its immediate response following a disturbance from a trimmed flight condition. For a helicopter, this can include rearwards, sideways, forwards, and hovering trimmed flight at constant altitude or in a climb or descent. The disturbance response of the main rotor dominates the helicopter response. Modeling this response is crucial in the development of stability and control derivative data to predict static and maneuver stabilities, the latter term describing a form of static stability where response to variations in angle of attack is assessed. Notwithstanding the complexities of the rotor system modeling, the flight‐testing techniques for static and maneuver stabilities from the pilot's perspective of the cockpit inceptor positions and applied forces are straightforward. The results from these flight tests for static stability contribute significantly to the overall assessment of an aircraft's stability, control, and response characteristics. However, the final assessment must include results from other dynamic stability and control response evaluations and from assigned handling quality ratings (HQRs) awarded by test pilots on completion of carefully planned handling tasks.
Aircraft Navigation
Authors: Hagström Martin , Lennartsson Anders 
Published: December 2010

Abstract
Navigation is an essential part of flying where crew keep track of the position of a moving aircraft relative to the Earth. Early in aviation history the tools for this were maps, compass, airspeed, indicator, clock, and astronavigation. Modern systems in the craft, on the ground and in space, have to a large degree automated this task and provides high accuracy and availability. There are now ground based navigation systems with area coverage, specialized systems for landing procedures, radio beacons, distance measuring equipment, radar and transponders, inertial navigation systems, and satellite navigation receivers. Equally important as these technical aids are air traffic control, maps, and procedures. Today the art of air navigation involves a working knowledge of all these systems.
Guided Weapon andUAVNavigation and Path‐Planning
Authors: Faruqi Farhan A. 
Published: December 2010

AbstractIn this chapter, techniques and technologies used for weapon, unmanned air vehicles (UAV), and aircraft navigation and guidance are described and the basic principles of analysis and synthesis of the techniques are established. Problems associated with inertial navigation system (INS), global positioning system (GPS) for missiles and UAV are discussed including methods for deriving navigation information from GPS, INS, and integrated GPS/INS. The application and principles of terrain reference navigation (TRN) systems such as terrain profile matching (TERPROM), terrain contour matching (TERCOM), and terrain scene matching (TERSMAC) are described and methods for combining these techniques with other navigation systems using the Kalman filter are discussed. Aircraft and UAV path planning is considered and a method for generating an optimum path to achieve a stealthy mission through an enemy territory is described. Guided weapon autonomous guidance strategies commonly used today such as the command to line of sight (CLOS) and proportional navigation (PN) guidance are described. Methods for analysis and synthesis of these guidance techniques are established and their performance discussed. Different guidance phases of weapons during target engagements are discussed and the various guidance modes (active, semi‐active, and passive) are described.
Adaptive and Robust Flight Control
Authors: Wise Kevin A. 
Published: December 2010

AbstractThis chapter presents the theory and application of model reference adaptive control (MRAC) to augment a baseline control to improve performance and robustness to model uncertainties. The adaptive control is derived using a Lyapunov‐type argument and is shown to extend performance and robustness of a baseline linear quadratic regulator control law. A flight control application is used to demonstrate the approach and evaluate the design using nonlinear simulation.
Cooperative Control for Multiple Air Vehicles
Authors: Schumacher Corey J. 
Published: December 2010

AbstractThis chapter provides an overview of topics, technical challenges, and methods involved in cooperative control for multiple air vehicles. This is a broad area, with many subtopics and technical disciplines potentially involved. Subtopics of cooperative control include: cooperative motion and formation control, cooperative search and area coverage, task assignment and scheduling, and cooperative task execution. The particular technical challenges involved can vary depending on the exact type of cooperative control problem discussed, but certain difficulties are ubiquitous, particularly uncertainty, limited communication, and task coupling. This discussion focuses on technical challenges and solution methods related to assignment and scheduling problems for cooperative teams.
Integrated Health Monitoring for Multiple Air Vehicles
Authors: Léchevin Nicolas , Rabbath Camille A. , Su Chun‐Yi 
Published: December 2010

Abstract
This chapter proposes an integrated health monitoring system whose objective is to maintain the integrity of a fleet of small unmanned aerial vehicles, or UAVs, despite the occurrence of actuator faults and body damage. The monitoring system relies on distributed, team‐level abrupt and nonabrupt fault detectors (NaFDs) and enables UAV teams to compensate for an ineffective individual vehicle fault detection and recovery system, if any. The abrupt and nonabrupt fault detectors utilize relative positions and speeds of vehicles within sensor range, in addition to exploiting information available through the communication network. A special attention is given to the selection of the detector thresholds, at the design phase, to minimize the average time of detection and the probability of missed detections, while constraining the probability of false alarms to an acceptable limit. For such purpose, an automated procedure based on stochastic search is proposed. Integrated health monitoring and control is demonstrated numerically by means of high‐fidelity, nonlinear 6‐degree‐of‐freedom (6‐DOF) simulations of teaming small‐scale UAVs. The chapter shows that concurrent nonabrupt and abrupt faults can be detected and effectively compensated for, thus preserving the integrity of a formation.
Radar Waveforms and Signal Processing
Authors: Levanon Nadav 
Published: December 2010

Abstract
The waveform determines the delay‐Doppler response of a radar system, hence the radar's range and velocity resolution and ambiguities. This chapter shows how narrow‐band signals are described and presents the major signal processing and analysis tools – the matched filter (MF) and the ambiguity function (AF). Basic signals that are discussed are unmodulated rectangular pulse, linear frequency modulated (FM) pulse compression, binary and polyphase‐coded signals, and a coherent pulse train. Additional topics are sidelobe reduction and periodic continuous waveforms.
Automatic target recognition
Authors: Mishra Amit K. , Mulgrew Bernard 
Published: December 2010

AbstractOne of the important forms of military intelligence consists of recognizing the type of target in the battle field. If good‐quality optical image of the battle scene is available, target recognition is done mostly by human experts. However, for sensors like infrared sensors and radars, target recognition solely by human experts is difficult. Hence, application of pattern recognition techniques, mainly in systems based on sensors like these, is prevalent and is known as automatic target recognition (ATR). This chapter will start with a short description of ATR and the challenges involved. Radar‐based ATR, especially synthetic aperture radar (SAR)‐based ATR, is one of the most popular ATR schemes, and hence the rest of the chapter will be devoted to SAR ATR. We will first describe the different stages of a generic ATR system and then elaborate some of the major challenges of radar‐based ATR. This will be followed by a description about the major figures of merit for a SAR ATR algorithm. The chapter will discuss some of the important algorithms from the open literature dealing with radar‐based ATR. We will also discuss some of the recent developments in the field of ATR, for example, bistatic radar‐based ATR, polarimetric radar‐based ATR, and multi‐look radar‐based ATR. The chapter will close with a note on the futuristic radar‐based ATR systems.
Electro‐Optic Imaging and Tracking Systems
Authors: Richardson Mark A. , James David B. 
Published: December 2010

Abstract
In Electro‐optic Sensor Principles the origins of a targets electro‐magnetic signature and the nature of lasers and their operation are presented and discussed. In this chapter the nature of electro‐optic (EO) imaging and tracking systems will be presented and the common applications of laser systems. The evolution and functioning of missile seekers will also be discussed. Since its development in the 1960s the laser has fulfilled many novel roles within both civil and military environments. This chapter will also present the principles of the most common laser applications, such as laser rangefinding and LIDAR, as well as laser target designation. In addition the role of the laser as a potential weapon to cause dazzle and damage to EO sensors will be discussed. Finally, the role of lasers in retro‐reflection detection for counter surveillance will be presented.
Interplanetary Navigation
Authors: Wood Lincoln J. 
Published: December 2010

Abstract
The navigation of interplanetary spacecraft is a complex, multi‐faceted process, with measurement acquisition, flight path estimation, and flight path control as its major constituents. Radio metric data, derived from the spacecraft‐to‐ground communication link, yield information about spacecraft position and velocity and other parameters of interest. Optical data, derived from on‐board imaging systems, yield target‐relative navigational information. Sophisticated computational techniques are used to accurately estimate spacecraft position and velocity and other quantities of interest that affect the spacecraft's motion and the measurement values.
Satellite Orbit Determination
Authors: Born George H. , Jones Brandon A. 
Published: December 2010

AbstractModern orbit determination methodology dates back to the beginning of the nineteenth century, when Legendre attempted to determine the orbits of the planets. Both he and Gauss recognized the importance of observational errors and proposed the least‐squares solution as a method for minimizing the effect of such errors. Over the past four decades the accuracy of determining Earth orbiter positions has evolved from hundreds of meters to a few centimeters. This chapter provides an overview of the history of satellite orbit determination and a review of the numerical algorithms needed for a basic orbit determination software system.
Libration Point Orbits and the Three‐Body Problem
Authors: Davis Kathryn , Anderson Rodney L. 
Published: December 2010

AbstractLibration point orbits in the three‐body problem play an important role in mission design. Their size, shape, location, and dynamical features are attractive for many different science and exploration missions, with objectives ranging from the collection of solar observations and measurements, to a search for the first massive black holes, to the direct imaging of planets within the habitable zone of stars beyond our solar system. The gravitational forces of two massive bodies govern the dynamics in the vicinity of the libration points and the motion in this regime is vastly different from traditional Keplerian motion. This chapter presents a historical overview of the three‐body problem, its formulation and assumptions, and the corresponding equations of motion. Methods of analytically and numerically computing libration point orbits are presented, along with a discussion on orbit stability. Invariant manifolds, trajectories that asymptotically approach or depart a nominal orbit, are described, as is their application for constructing transfers between orbits. Additionally, a brief survey of past, future, and proposed libration point orbit missions is presented.
Fault Detection, Isolation, and Recovery of Guidance, Navigation and Control
Authors: Chen George , Burt J. Brad 
Published: December 2010

AbstractThe subject of spacecraft fault detection, isolation, and recovery, also known as fault protection, is introduced along with standard terminology. A general description of a typical fault protection system is presented with a specific emphasis on the application to guidance, navigation, and control (GN&C) subsystems. The functions of a fault protection system for a notional three‐axis controlled GN&C subsystem are presented as examples. Finally, the role of various types of redundancy and the desire for graceful degradation in the presence of failures in fault protection systems are discussed.
Close Proximity Rendezvous and Docking (RVD)
Authors: Fehse Wigbert 
Published: December 2010

AbstractRendezvous and docking (RVD) techniques are required in most of the space operations, which involve more than one spacecraft. This chapter describes the basic tasks, the scenarios, and the phases of a rendezvous mission. Since the first phases are not much different from other space missions, the chapter concentrates on the rendezvous phases with relative navigation. Typical rendezvous trajectories and strategies are shown. Onboard control systems and relative navigation sensors for automatic RVD in low earth orbit (LEO) are described. The principle of docking and berthing is addressed also and types of docking mechanism are discussed. The chapter addresses the differences between LEO of rendezvous operations in other orbits and the role of human operators in various rendezvous scenarios.
Atmospheric Composition
Authors: Schlatter Thomas W. 
Published: December 2010

Abstract
This chapter considers the gases constituting Earth's atmosphere and how the mixture of atmospheric gases varies with altitude up to roughly 1000 km. Turbulent mixing keeps the relative concentrations of gases nearly constant in the lowest 100 km. At higher altitudes, molecular diffusion controls the concentrations, with the lighter gases becoming relatively more abundant with increasing altitude. Atmospheric gases are electrically neutral up to about 60‐km altitude. At higher altitudes, energetic solar radiation from the sun ionizes neutral molecules, creating charged particles (ions and free electrons), which mix with the neutral particles.
The Earth's Magnetic Field
Authors: Macmillan Susan , Rycroft Michael J. 
Published: December 2010

Abstract
The Earth's magnetic field is generated in the fluid region deep inside the Earth. Heat convection, buoyancy forces, and planetary rotation cause the iron‐rich fluid in the outer core to flow in a complex way and the movement of this electrical conductor through existing magnetic field generates electrical current. This produces more magnetic field in an advective process. Some of it diffuses away resulting in a reasonably stable magnetic field, which is broadly dipolar outside the planet and which occasionally reverses its polarity. Parameters of the Earth's magnetic field observed near the surface of the planet vary in space and time over wide ranges. As well as processes acting in the deep interior of Earth, the crust, the ionosphere, the magnetosphere, and the Sun all contribute to the observed magnetic field. Indeed, the magnetosphere is formed by the interaction of the solar wind, moving radially outwards from the Sun at supersonic speeds, with the Earth's magnetic field (see also The Plasma and Radiation Environment in Earth Orbit). Geomagnetic observations are made at fixed sites at observatories, and extensive surveys are carried out on land, at sea, and from aircraft and satellites; the magnetic properties of rocks provide further information. The Earth's magnetic field is important for many aerospace applications today, and these areas are especially considered.
Micrometeoroids
Authors: Srama Ralf 
Published: December 2010

Abstract

Micrometeoroids are natural dust particles with masses between 10
−21
and 10
−9
kg (0.01–100 μm). In contrast to space debris, their sources are bodies in the solar system like comets, asteroids or planetary environments.

Although comets are the most obvious source of interplanetary dust in the inner solar system, there exist a variety of dusty phenomena and dust sources.

An recent summary about interplanetary dust was given by gruen 2001. Our current knowledge is based on remote sensing observations (light scattering, thermal emissions),
in‐situ
dust experiments, (Pioneer, Giotto, Helios, Heos, Nozomi, Gorid, Galileo, Cassini, Ulysses, Stardust, New Horizon), crater studies of moon rocks or of planetary moon surfaces, meteor radar studies and laboratory sample analysis. (dust extracted from polar ices, dust collected in the stratosphere, dust returned by Stardust, dust and space debris impact residues of returned satellite parts).

The following sections describe the measurement techniques of micrometeoroids, the properties of interplanetary dust (mass flux, dynamics, or composition) and the dust sources like comets, asteroids, or planetary environments. Two later sections give examples of laboratory simulation facilities. Finally, hazards related to hyper‐velocity micrometeoroid impacts are discussed.
Propulsion System Noise: Turbomachinery
Authors: Astley R. Jeremy 
Published: December 2010

Abstract
Turbomachinery sources are important contributors to whole aircraft noise both at takeoff and approach. The turbomachinery contribution contains both tone and broadband components and is generated by a variety of mechanisms that occur in the fan, turbine, compressor, and combustor. These different sources are reviewed along with technologies that have been developed to mitigate their effect, either by reducing noise at source or by applying sound‐absorbing treatments within the engine. Discussion is limited here to the exterior impact of turbofan noise on communities near airports. The effect on passengers and crew within the aircraft is dealt with separately elsewhere. Attempts to mitigate the environmental impact of aircraft noise are dominated by the metrics that are used to certify and regulate aircraft noise. These are introduced and their implications are discussed.
Interior Noise and Sound Transmission
Authors: Neple Pascale 
Published: December 2010

AbstractAircraft interior noise control as a major factor of cabin and cockpit comfort is considered as an essential design requirement by transport airplane manufacturers. External sources such as the turbulent boundary layer excitation and acoustic radiation from engines being the main interior noise contributors over a large frequency range, this section focuses mainly on sound transmission through fuselage structure and noise control treatments. After describing the existing noise sources and the main characteristics of a fuselage structure including classical noise control treatments, the emphasis will be put on the methodology to assess interior noise, based on typical testing and existing modeling methods. The complexity of the fluid‐structure coupled issue and the main weak and strong points of each modeling method, both at aircraft and fuselage element level, will be addressed. Then, understanding and modeling the vibroacoustic behavior of stiffened structures being necessary to assess overall interior noise level, a dedicated section will describe the main phenomena governing sound transmission through these elements. Finally, the excitation field effect on sound transmission mechanisms and particularly on noise control treatments efficiency will be discussed. Turbulent boundary layer, diffuse sound field, and structure‐borne excitation will be considered.