A Novel Dual-Loop Disturbance Observer-Based Attitude Control for a Space-Based Observation Microsatellite

Table 1

Initial parameters of satellite	Value
Initial attitude angle of satellite	𝜃𝑥=1^∘,  𝜃𝑦=1^∘,  𝜃𝑧=1^∘
Initial attitude angular velocity of satellite	𝜔𝑥=0.1^∘/𝑠,  𝜔𝑦=0.1^∘/𝑠,  𝜔𝑧=0.1^∘/𝑠
Angular velocity of camera turntable	𝛼=(1.2sin𝜔𝑡)^∘/𝑠, 𝛽=(1.2sin𝜔𝑡)^∘/𝑠
	𝜔=0.03rad/𝑠
The uncertainties of the matrix of moment of inertia	Δ𝐼=300040002(kg⋅m^2)
Space environmental disturbance torques	𝑀𝑥=10^−53cos𝜔0𝑀𝑡+1𝑦=10^−51.5sin𝜔0𝑡+3cos𝜔0𝑡𝑀𝑧=10^−53sin𝜔0𝑡+1