s12_ps09_fall03

s12_ps09_fall03 - Unified Engineering I Fall 2003 Problem...

Info iconThis preview shows pages 1–2. Sign up to view the full content.

View Full Document Right Arrow Icon

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: Unified Engineering I Fall 2003 Problem S12 (Signals and Systems) The longitudinal dynamics of an aircraft ying are given in state-space form as dh dt = V sin (1) dV T D dt = g sin + m m (2) d dt = L mg mV (3) where h = altitude V = velocity of aircraft = ight path angle g = acceleration due to gravity L = lift T = thrust D = drag m = mass of aircraft We assume that (1) the thrust is constant, (2) the aircraft ies at constant coeeficient of lift, and (3) the aircraft ies at constant drag coeeficient. These assumptions are not bad for the case whent he pilot releases all the controls, and makes no adjustments, say, for altitude variations. In this case, we can rewrite the equations as dh = V sin (4) dt dV T D 0 V 2 = g sin + (5) dt m m V 2 d L ( V/V ) 2 mg = (6) dt mV where L 0 and D 0 are the lift and drag at the nominal velocity, V . If the aircraft is intially in trim, it must also be true that T = D 0 (7) L 0 = mg (8) Equations (4)(6) are the equations of motion in state-space form, although the...
View Full Document

Page1 / 2

s12_ps09_fall03 - Unified Engineering I Fall 2003 Problem...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online