The mass properties of ADEOS-II (To Be Revised)

Phase			Satellite Mass (Kg)	Barycentric coordinates (mm)				Moment of inertia (Kg・m2)			Product of inertia (Kg・m2)
				X		Y	Z	lxx	lyy	lzz	lxy	lyz	lzx
Launch Phase			3680.0	2106.6	34.0		111.8	7592	12342	14330	407	213	361
Begin of life	PDL rotation angle	0deg	3563.8	2163.6	-402.5		30.1	46523	13387	51492	-958	750	335
		90deg	3563.8	2169.2	-402.5		24.4	46652	13451	51427	-1286	1078	303
		180deg	3563.8	2163.5	-402.5		18.8	46585	13449	51491	-958	1405	302
		270deg	3563.8	2157.9	-402.5		24.5	46651	13384	51361	-630	1077	334
End of life		0deg	3509.6	2191.7	-413.3		30.6	46479	13201	51264	-887	751	332
		90deg	3509.6	2197.4	-413.3		24.8	46608	13265	51199	-1214	1079	300
		180deg	3509.6	2191.6	-413.3		19.1	46542	13264	51264	-887	1406	300
		270deg	3509.6	2185.9	-413.3		24.8	46608	13200	51135	-559	1078	332

*1 The satellite coordinate defines as a center of the payload separation plane.

*2 The direction of the solar paddle defines the case in which the cell plane has turned to the +Z direction as rotation angle 0 degrees, and it is defines the case in which the cell plane has turned to the right toward the +y direction as a rotation angle.

*3 The value of the mass is made to be "nominal value" + "prediction error" + "buoyancy correction value".

*4 It was analyzed at propellant 186.0kg, pressurized gas 0.4kg, buoyancy compensation 4.4kg.

*5 The propellant consumption made that the 1N thruster was used to be a premise. The total consumption was made to be 170.4kg.

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