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false alarms amp cm the mis-association of false alarms with target tracks has two main eects - it tends to increase the actual tracking errors
state vectors in engineering - particularly control engineering - most systems are represented by a state vector - the state vector contains
radar systemsradar is an acronym for radio detection and ranging a radar uses an antenna to transmit a series of electromagnetic waves or
imaging infrared seekers a more common approach is to use an infrared waveband where there is a large amount of ambient light from the thermal
imaging seekers although there are a wide variety of imaging sensors cameras the majority of modern aircraft systems are based on conventional
actuators the actuator consists of the control surfaces and associated servomechanisms and is used to change the missile attitude and
fins vs canards canard control - good liftlatax control for moderate angles of attack - shed vortices can interfere with tail to generate roll
control surfaces as with a flight control system a guidance algorithm uses control surfaces to control the behaviour of an airframe
guidance control systemthe control aspect of the guidance system is intended to stabilise the behaviour of the airframe the fact that the
the guidance law is used to generate a requirement usually an required acceleration that will achieve the guidance objective in this course we will
kalman filtering all of the measurements generated by the seeker and the navigation systemrate gyros are noisy and therefore need to be
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