Path: ACPro/AircraftPro
% Right-hand-side for a linear rolling missile.
Right hand side for a linear rolling missile
d = RHSRollingMissileLinear
returns the default data structure.
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Form:
xDot = RHSRollingMissileLinear( x, ~, d )
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Inputs
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x (5,1) [pitch/yaw;angle of attack, pitch rate, yaw rate;roll angle]
t (1,1) Time (unused)
d (.) Data structure
.p (1,1) Roll rate (rad/s)
.mAlpha (1,1)
.zDelta (1,1)
.mDelta (1,1)
.mAlphaDot (1,1)
.mQ (1,1)
.zAlpha (1,1)
.zDelta (1,1)
.iX (1,1) Roll inertia (kg/m^2)
.iY (1,1) Pitch inertia (kg/m^2)
.deltaY (1,1) Yaw flap deflection (rad)
.deltaP (1,1) Pitch flap deflection (rad)
.
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Outputs
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xDot (5,1) d[pitch/yaw;angle of attack, pitch rate, yaw rate, roll angle]/dt
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Reference: Richard Lestage, "Analysis of Control and Guidance for
Rolling Missiles with a Singlee Plane of Control Fins,"
AIAA-2000-3971, AIAA Guidance, Navigation, and Control
Conference and Exhibit 14-17 August 2000 Denver,CO.
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