000			03507nam a22005415i 4500
001			978-3-540-46573-7
003			DE-He213
005			20161121231200.0
007			cr nn 008mamaa
008			100301s2007 gw | s |||| 0|eng d
020			_a9783540465737 _9978-3-540-46573-7
024	7		_a10.1007/978-3-540-46573-7 _2doi
050		4	_aTL787-4050.22
072		7	_aTRP _2bicssc
072		7	_aTTDS _2bicssc
072		7	_aTEC002000 _2bisacsh
082	0	4	_a629.1 _223
100	1		_aHull, David G. _eauthor.
245	1	0	_aFundamentals of Airplane Flight Mechanics _h[electronic resource] / _cby David G. Hull.
264		1	_aBerlin, Heidelberg : _bSpringer Berlin Heidelberg, _c2007.
300			_aXIII, 298 p. _bonline resource.
336			_atext _btxt _2rdacontent
337			_acomputer _bc _2rdamedia
338			_aonline resource _bcr _2rdacarrier
347			_atext file _bPDF _2rda
505	0		_ato Airplane Flight Mechanics -- 3DOF Equations of Motion -- Atmosphere, Aerodynamics, and Propulsion -- Cruise and Climb of an Arbitrary Airplane -- Cruise and Climb of an Ideal Subsonic Airplane -- Take-off and Landing -- PS and Turns -- 6DOF Model: Wind Axes -- Static Stability and Control -- 6DOF Model: Body Axes -- Dynamic Stability and Control.
520			_aAirplane flight mechanics is the application of Newton's laws to the study of airplane trajectories (performance), stability, and aerodynamic control. This text is limited to flight in a vertical plane and is divided into two parts. The first part, trajectory analysis, is concerned primarily with the derivation of analytical solutions of trajectory problems associated with the sizing of commercial jets, that is, take-off, climb, cruise, descent, and landing, including trajectory optimization. The second part, stability and control, is further classified as static or dynamic. On each iteration of airplane sizing, the center of gravity is placed so that the airplane is statically stable. Dynamic stability and control is included to study the response of an airplane to control and gust inputs, which is needed for the design of automatic flight control systems. Algorithms are presented for estimating lift, drag, pitching moment, and stability derivatives. Flight mechanics is a discipline. As such, it has equations of motion, acceptable approximations, and solution techniques for the approximate equations of motion. Once an analytical solution has been obtained, numbers are calculated in order to compare the answer with the assumptions used to derive it and to acquaint students with the sizes of the numbers. A subsonic business jet is used for these calculations.
650		0	_aEngineering.
650		0	_aMathematical models.
650		0	_aApplied mathematics.
650		0	_aEngineering mathematics.
650		0	_aComputational intelligence.
650		0	_aAutomotive engineering.
650		0	_aAerospace engineering.
650		0	_aAstronautics.
650	1	4	_aEngineering.
650	2	4	_aAerospace Technology and Astronautics.
650	2	4	_aAutomotive Engineering.
650	2	4	_aComputational Intelligence.
650	2	4	_aAppl.Mathematics/Computational Methods of Engineering.
650	2	4	_aMathematical Modeling and Industrial Mathematics.
710	2		_aSpringerLink (Online service)
773	0		_tSpringer eBooks
776	0	8	_iPrinted edition: _z9783540465713
856	4	0	_uhttp://dx.doi.org/10.1007/978-3-540-46573-7
912			_aZDB-2-ENG
950			_aEngineering (Springer-11647)
999			_c509753 _d509753