1998-041A
THe ISAS Planet B mission will study the Martian atmosphere and its interaction with the solar wind. It will have a periapsis of 150 km. Mass is 540 kg. Fuel is 278 kg. Craft has 4 25-m wire antennae giving 50m span, were to be deployed at Mars; this did not happen because of the failures.
Launch Jul 4 1998, lunar swingby, Mars MOI Oct 1999. Planet B is built by NEC Corp. Planet B's NMS instrument is a modernized version of the one flown on Pioneer Venus.
Named Nozomi (`Desire' or `Hope') after launch. Nozomi made six elliptical orbits from Jul to its first lunar flyby in 1998 Sep. It then arced out to 1.7 Mkm around Nov 10 and fell back to a second lunar swingby in December, followed two days later by an Earth pass for solar orbit injection. The perigee burn didn't provide enough thrust, so the Oct 1999 MOI was delayed to Dec 2003.
A double Earth swingby in Dec 2002 and Jun 2003 has been discussed.
In Apr 2002 solar flares damaged the spacecraft's communication systems and the heaters for the RCS system. The hydrazine froze but warmed up as Nozomi got closer to the Sun. In the absence of telemetry, ISAS used a capability to switch the radio beacon on and off to confirm that commands were being received correctly during the Dec 2002 swingby.
On 2003 Dec 1, Nozomi was on a 894 km x Inf Mars hyperbolic trajectory with periapsis on Dec 14.
Stage 3 burn: M34 mass 11600 900 Isp 301 burn 102 thrust 294 Ve 2952 Mdot is T/Ve = 99.6 kg/s so for 102s have 10160 kg. m1/m2 = 11600+P/900+P, P = 1864 so 13464 / 2764 dV = 4674m/s
Stage 4 burn: KM-V mass 1324 124 + 540. m1/m2 = 1864/664 Ve = 2942 dV = 3036 m/s
| Planet B | |||
| Date | Time | Event | Orbit |
|---|---|---|---|
| 1998 Jul 3 | 1812 | Launch by M-V-3 | KASC |
| Stage 1 burn | |||
| T+1:15 Stage 1 sep | |||
| T+1:15 Stage 2 burn | |||
| T+3:33 St 2 sep? | |||
| T+3:38 Stage 3 burn | |||
| 1817 | T+5:23 Stage 3 burnout | ||
| 161 x 422 x 31.10 (ISAS p319) | |||
| 146 x 417 x 31.7 | |||
| T+19:59 Spin motor ig | ||
| 1832 | T+20:24s? Stage 3 sep | ||
| 1832 | T+20:11s KM burn Isp 300s | ||
| 1833 | T+21:22s KM burnout dV= 3.160km/s | ||
| 1835 | T+23:19? KM-V1 sep | ||
| 359 x 401491 x 28.6 | |||
| 1998 Jul 4 | 0933 | Pass EL1:4 | |
| 1998 Sep 24 | Lunar flyby 1, 4000 km | ||
| 1998 Nov 10? | Apogee | ? x 1.7 Mkm | |
| 1998 Dec 18 | 0734 | Lunar flyby 2 C/A = 4547 km | |
| 1998 Dec 20 | 0809:54 | Perigee C/A=7381 km, 7min TMI burn, underspeed | |
| Earth escape | |||
| 1998 Dec 20 | 2301 | Correction burn 1 | |
| 1998 Dec 20 | 2339 | Correction burn 2 | |
| 1999 Jan | 146 x 216 Mkm x 3.0 485d | ||
| 1999 Jan | 0.978 x 1.446 AU x 2.9 deg 487d | ||
| 1999 Mar 1 | DV10 TCM | ||
| 1999 May 2 | Small gas leak | ||
| 1999 Jul 5 | S-band downlink problem | ||
| 1999 Aug 28 | Mars C/A 5.5Mkm | ||
| 2000 Jun 22 | DV11 TCM | ||
| 2002 Apr 26 | Loss of contact due to solar flare damage | ||
| 2002 Apr 28 | DV12 TCM aborted | ||
| 2002 Jul 14 | Recovered beacon | ||
| 2002 Sep 2 | reorientation | ||
| 2002 Sep 10 | 0737? | DV13 TCM | |
| 2002 Oct 5 | DV14 TCM | ||
| 2002 Nov 22 | DV15 TCM | ||
| 2002 Dec 21 | 0737 | Earth pass 30000 km | |
| 2003 Jan | 0.832 x 1.167 AU x 6.2 deg 365d | ||
| 2003 Jun 19 | 1444 | Earth pass 15872 km (22250 km C/A) | |
| 2003 Jul | 1.013 x 1.508 AU x 7.7 deg 517d | ||
| 2003 Jul 8 | Loss of beacon | ||
| 2003 Dec 9 | TCM attempt failed | ||
| 2003 Dec 9 | 1618 | Enter Mars sphere | |
| 2003 Dec 9 | RCS burn to tweak flyby distance | ||
| 2003 Dec 13 | 1819 | Flyby Mars at 1000 km | |
| 2003 Dec 17 | 2200? | Leave Mars gravity | |
| 2003 Dec 19 | End of mission | ||
Payload:
- Energetic electron detector
- Energetic ion detector
- High energy particle detector
- Electron temperature probe
- Fluxgate magnetometer, 5m mast
- UV spectrometer
- EUV spectrometer
- HF plasma wave detector/sounder
- LF plasma wave detector
- CCD Cameras
- WANT Wire Antennae,4: 25m each
- TPA Thermal Plasma Analyser, CSA
- NMS Neutral Mass spectrometer, NASA GSFC
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