Encyclopedia Astronautica
Nozomi



nozmoi.jpg
Nozmoi
Credit: NASDA
Japanese Mars orbiter. One launch, 1998.07.03.

Nozomi (Japanese for Hope and known before launch as Planet-B) was to have been a Mars orbiting aeronomy mission designed to study the Martian upper atmosphere and its interaction with the solar wind and to develop technologies for use in future planetary missions. However propulsion failures led to its arrival at Mars being delayed from 1999 to 2003. When it finally arrived at Mars its main engine failed, and the spacecraft passed by 1000 km over the surface and then into solar orbit.

Instruments on the spacecraft were to have measured the structure, composition and dynamics of the ionosphere, aeronomy effects of the solar wind, the escape of atmospheric constituents, the intrinsic magnetic field, the penetration of the solar-wind magnetic field, the structure of the magnetosphere, and dust in the upper atmosphere and in orbit around Mars. The mission also would have returned images of Mars' surface.

The Nozomi orbiter was a 0.58 meter high, 1.6 meter square prism with truncated corners. Extending out from two opposite sides were solar panel wings containing silicon solar cells which provided power to the spacecraft directly or via Ni-MH (nickel metal hydride) batteries. On the top surface was a dish antenna, and a propulsion unit protruded from the bottom. A five meter deployable mast and a 1 meter boom extended from the sides, along with two pairs of thin wire antennas which measured 50 m tip to tip. Other instruments were also arranged along the sides of the spacecraft. Spacecraft communications were via X-band at 8410.93 MHz and S-band at 2293.89 MHz.

The 14 instruments carried on Nozomi were an imaging camera, neutral mass spectrometer, dust counter, thermal plasma analyzer, magnetometer, electron and ion spectrum analyzers, ion mass spectrograph, high energy particles experiment, VUV imaging spectrometer, sounder and plasma wave detector, LF wave analyzer, electron temperature probe, and a UV scanner. The total mass budgeted for the science instruments was 33 kg. Radio science experiments were also possible using the existing radio equipment and an ultra-stable oscillator. The total mass of Nozomi at launch including 282 kg of propellant was 540 kg.

Nozomi used multiple lunar and Earth gravity assist passes to increase its energy for solar orbit insertion and the cruise to Mars. Nozomi was to have been inserted into a highly eccentric Mars orbit with a periapsis 300 km above the surface, an apoapsis of 15 Mars radii, and an inclination of 170 degrees with respect to the ecliptic plane. Shortly after insertion the mast and antennas would have been deployed. The periapsis would then be lowered to 150 km, the orbital period to about 38.5 hours.

The spacecraft would be spin stabilized at 7.5 RPM with its spin axis (and the dish antenna) pointed towards Earth. The periapsis portion of the orbit would have allowed in-situ measurements of the thermosphere and lower exosphere and remote sensing of the lower atmosphere and surface. The more distant parts of the orbit would allow study of the ions and neutral gas escaping from Mars and their interactions with the solar wind.

The nominal mission was planned for one Martian year (approximately two Earth years). An extended mission would have allowed operation of the mission for three to five years. The spacecraft also was to have pointed its cameras at the Martian moons Phobos and Deimos.

AKA: Planet-B.
Gross mass: 258 kg (568 lb).
Unfuelled mass: 234 kg (515 lb).
Height: 0.58 m (1.90 ft).
First Launch: 1998.07.03.
Number: 1 .

More... - Chronology...


Associated Countries
See also
  • M-V All-solid Japanese satellite launch vehicle. More...

Associated Launch Vehicles
  • M-V All-solid Japanese satellite launch vehicle. More...

Associated Manufacturers and Agencies
  • ISAS Japanese agency overseeing development of rockets, spacecraft, and rocket engines. Institute of Space and Astronautical Science, Japan. More...
  • NEC Japanese manufacturer of spacecraft. Nippon Electric Corporation, Japan. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • National Space Science Center Planetary Page, As of 19 February 1999.. Web Address when accessed: here.

Associated Launch Sites
  • Kagoshima Japanese launch center for solid fueled sounding rockets and satellite launchers. Limited to two months a year due to disturbance of local fisheries. More...

Nozomi Chronology


1998 July 3 - . 18:12 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V M-V-3.
  • Nozomi - . Mass: 258 kg (568 lb). Nation: Japan. Agency: ISAS. Manufacturer: NEC. Class: Mars. Type: Mars probe. Spacecraft: Nozomi. USAF Sat Cat: 25383 . COSPAR: 1998-041A. Apogee: 489,381 km (304,086 mi). Perigee: 703 km (436 mi). Inclination: 27.3000 deg. Period: 20,910.00 min. Originally known as Planet-B; renamed Nozomi ('Hope') after launch. The third stage and payload entered a 146 x 417 km x 31.1 deg parking orbit. The KM-V1 kick (fourth) stage then fired to place the spacecraft into a circumlunar 359 x 401491 km x 28.6 deg orbit. Nozomi made multiple lunar and Earth gravity assist passes to increase its energy for solar orbit insertion and the cruise to Mars.. The spacecraft used a lunar swingby on 24 September and another on 18 December 1998 to increase the apogee of its orbit. It swung by Earth on 20 December at a perigee of about 1000 km. The gravitational assist from the swingby coupled with a 7 minute burn of the bipropellant engine put Nozomi into an escape trajectory towards Mars. It was scheduled to arrive at Mars on 11 October 1999 at 7:45:14 GMT, but the Earth swingby left the spacecraft with insufficient acceleration and two course correction burns on 21 December used more propellant than planned, leaving the spacecraft short of fuel. The new plan is for Nozomi to remain in heliocentric orbit for an additional four years and encounter Mars at a slower relative velocity in December 2003.

2002 December 20 - .
  • Nozomi, Earth Flyby - . Nation: Japan. Spacecraft: Nozomi.

2003 June 19 - .
  • Nozomi, Earth Flyby, Successful - . Nation: Japan. Spacecraft: Nozomi.

2003 December 14 - .
  • Nozomi, Mars Flyby - . Nation: Japan. Spacecraft: Nozomi. The Japanese Mars probe, Nozomi, flew past the planet at a height of 1000 km. Attempts to operate the spacecraft's main propulsion system failed, and small thrusters were used to increase the flyby distance by about 100 km to ensure a clean miss. The mission was abandoned, and Nozomi entered a new orbit around the Sun.

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