Tsubasa

 2002-003A

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Tsubasa, the MDS-1 Mission Demonstration Satellite is a generic bus built by NEC for NASDA, with a mass of 500 kg. It is possibly derived from the OICETS satellite and the MUSES-B bus. MDS-1 will test commercial satellite components. Launch is Jan 2002 on H2A 2024 No. 2. Mass is 449 kg (or 480 kg?), box + 2 panels. Size is 1.2 x 1.2 x 1.5m launch, 3.3 x 1.6 x 2m deployed. MDS is spin-stabilized. AOCS is 4 x 1N thrusters.

Planned orbit is 500 x 35735 km x 28.5 deg.

The H-IIA-2024 has four Castor IVXL SSBs and two SRB-As. This flight uses the 4/4D-LC fairing.

H-IIA made an experimental SES-3 burn at 60 percent thrust, terminated by depletion.

MDS
Date	Time	Event	Orbit
2002 Feb 4	0245	Launch by H-2A	TNSC
		T+0:10 SSB 1-2 on
		T+1:10 SSB 1-2 sep 20 km 1.1 km/s	-6330 x 20
		T+1:16 SSB 3-4 on
		T+2:16 SSB 3-4 sep 77 km 2.0 km/s	-6190 x 90
		T+2:24? SRB-A sep 84 km 2.0 km/s	-6190 x 100
		T+4:05 Fairing sep 168 km 2.9 km/s
		T+6:30 St 1 MECO
		T+6:38 St 1 sep 309 km 5.3 km/s
	0251	T+6:44 Stage 2 MES
	0257	T+12:19 Stage 2 MECO-1	499 x 500
		T+24:36 Stage 2 MES-2
		T+27:28 Stage 2 MECO-2
	0315	T+30:18 Deployment of DASH failed
	0325	T+40:55? VEP-3 sep
		Adapter side panel sep
		Adapter side panel sep
		Spinup
	0331	T+46:40 Stage 2 deploy MDS-1
		T+1:40:00 Stage 2 MES-3, test burn 50s, 60 percent thrust
		T+1:40:51 MECO-3
2002 Feb 6	0152	Magnetometer mast extended
2003 Feb 26		Primary mission complete
2003 Sep		endof SEDA operations

Payload:

• SEDA Space environment data acquisition (heavy ions, magnetometer, dosimeter); 3-m boom

  • SDOM Standard dose monitor

  • DOS Dosimeter

  • HIT Heavy Ion Telescope

  • MAG. Magnetometer