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seekers there are two main types of sensor used in autonomous vehicles seekers and positionattitude sensors - although not all systems have
navigation systems bull traditional guidance systems used mechanical gyroscopes rate gyros to measure the angular velocities of the vehicle or
system dynamics crucial to the development of a guidance system is an understanding of the dynamics of the system in particular it is necessary to
the design and implementation of an autonomous guidance system requires knowledge and an understanding of a wide range of technologies from the
the impact and post-impact behaviour of composites many early studies involved doing charpy tests on small notched samples this is a destructive
thin-skinned structures the scb geometry cant be used because the skins are too flexible instead a centre-notch flexure cnf test can be used a
if the skins are peeled from the core a sandwich structure loses its strength and stiffness this can occur under - wave-slamming in fast ferries
mode iii interlaminar fracture toughness the mode iii interlaminar fracture toughness of a composite can be measured using the split cantilever
the mode ii fracture toughness is measured using the enf typically the specimen length is 120 mm the width b is 20 mm the thickness is between 3
here it is assumed that the crack is effectively longer than the value measured on the side of the specimen if one assumes that it is longer by an
double cantilever beamin the double cantilever configuration the ends of the sample are pulled apart forcing a crack to propagate down the beam from
the energy release rate often denoted by g is the amount of energy per unit area that is supplied by the elastic energy in the body and loading
it is instructive to investigate the pitching motion caused by a disturbance from trim due to a control surface deflection we shall assume that the
a trimmed flight condition is perhaps best thought of as an equilibrium condition the simplest trim condition is straight-and-level flight in which
in the aircraft performance course the aircraft was assumed to be in a steady-state eg steady cruise climb turn glide with the forces and moments
controller requirements the requirements for the stability and performance of fight control systems are specified in the certi-fication
representations of a linear systemthe linear system of section is shown in block diagram to determine the responseof the output of the system yt to
characteristic equationthe characteristic equation ce corresponding to the linear state space equations comprising the state equationx ax buand
linear state space equationslinear state space equations consist of a difierential state equationx ax buand an algebraic output equationy cx
static stability derivativesstatic stability requires that a restoring action to any motions caused by forces and moments is auto-matically produced
rotational stability equations the torque t applied to any rigid vehicle with moving cg is in general determined byt parthvepartte uve
notation for body axesthe standard notation for the body axis sytem for aircraft dynamics this sectionexplains the significance of the term body axis
notation for body axesthe standard notation for the body axis sytem for aircraft dynamics this sectionexplains the signicance of the term body axis
representing vectors in different axesall positions velocities momentums and accelerations are really relative positions relative velocities
the terms roving and yarn are widely used a roving is a collection of untwisted strands wound together a yarn is a generic term for a continuous