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Table 1 Detumbling manoeuvre—simulation parameters

From: Optimal attitude control of satellites

Name

Symbol

Value

Unit

Final time

T

4.5

s

Tensor of inertia

J

diag(1, 0.75, 0.5)

\(kg\ m^2\)

Integrand \(F = \frac{1}{2}( \varvec{x}^tQ\varvec{x} + \varvec{u}^tR\varvec{u})\)

Q

\(I_6\)

 

R

\(I_3\)

Initial angular velocity

\(\varvec{\omega }_0\)

\((\pi /2,\pi /4,\pi /8)\)

rad/s

Final angular velocity

\(\varvec{\omega }_T\)

(0, 0, 0)

rad/s

Initial orientation (Euler angles)

\(\Phi _0\)

(0, 0, 0)

rad

Final orientation (Euler angles)

\(\Phi _T\)

(0, 0, 0)

rad

Number of subintervals in the discretization

 

200