Modelling of Spacecraft Dynamics at Deployment of Large Elastic Structure

Table 1

Key system parameters.

Parameter	Notations	Value
Mass of main body	𝑚1	350 kg
Rods mass	𝑚𝑙	1 kg
Rods bending stiffness	𝐸𝐽	20–80 N m^2
Decrement of oscillations	𝜗	0.001
Nonzero components of the main body inertia tensor	𝐽𝑥𝑥	4000 kg m^2
	𝐽𝑦𝑦	5000 kg m^2
	𝐽𝑧𝑧	2000 kg m^2
	𝑎𝑥	0 m
Shift of main body centre of mass	𝑎𝑦	0 m
	𝑎𝑧	−1 m
Angular momentum of one GD rotor	ℎ𝑟𝑜𝑡	20 kg m^2/s
GD damping coefficient	𝑘3𝛽1,𝛽2	40 N m/s^2
Duration of deployment	𝑇𝑓	100–1000 s