Nozomi was designed to learn a martian upper atmosphere & its interaction using a solar wind and to develop technologies for have inside new planetary missions. Specifically, instruments on a ballistic capsule were to measure the structure, composition & kinetics of the ionosphere, aeronomy effects of a solar wind, a escape of atmospherical constituents, the intrinsical magnetic field, a penetration of the solar-wind magnetic field, the structure of the magnetosphere, & dust as much as the upper atmosphere and in orbit around Mars. A mission would keep close at hand too returned images of Mars' surface. Electrical patterns failures processed a probe unable to achieve Mars orbit.

Mission profile

When launch on the third M-V launch vehicle, Nozomi was put into an elliptical geocentric parking orbit sustaining the perigee of 34Klick & an apogee of 400,00Kilometer. the space vehicle utilized a lunar swingby on September 24 and another in December 18, 1998 to increase the apogee of its orbit. It swung by Globe in December 20, 1998 at a perigee of astir M kilometre. A gravitational assist from the swingby coupled by owning the Seven minute burn of the bipropellant rocket put Nozomi into an escape trajectory towards Mars. It was scheduled to make Mars in October 11, 1999 at 7:45:14 UT, but a nonfunctional valve inside the period of the Globe swingby resulted in a loss of fuel & left the space vehicle by owning deficient acceleration to email its plotted flight. 2 course correctiin burns on December 21 used more propellent than plotted, allowing a ballistic capsule short of fuel.

A recently project was for Nozomi to remawithinside in heliocentric orbit for even more, an extra foursome years, including deuce Globe flybys in December 2002 and June 2003, and encounter Mars at the slower proportional speed around December 2003. In April 21, 2002 as Nozomi was approaching Globe for the gravity help maneuver, right solar flares damaged the ballistic capsule's onboard communications & power systems. An electrical short was driven within a power cell utilized to control a attitude control heat, letting the hydrazine fuel to freeze. A fuel thawed retired when a craft approached Globe & maneuvers to put a craft on the right flight for its Globe flyby were successful. A second Globe flyby inside 11,000 kilometer occurred in June 19, 2003. A fuel got totally thawed retired for this maneuver because of the ballistic capsule's proximity to the Sun. Nonetheless, in December 9, 2003, efforts to orient the craft to develop it for the December 14 main thruster orbital insertion burn failed, and efforts to save a mission were abandoned. A little thrusters were fired in December 9, moving a nighest approach few feet away to G kilometer then that a probe would does'nt unwittingly impact in Mars & even contaminate a planet sustaining Globe bacterium, since a satellite got non been arranged to l& and was so non properly sterilized. the ballistic capsule flew by Mars in December 14, 2003 & went into a about Deuce-season heliocentric orbit. Though its mission has been abandoned a space vehicle is however active.

Nozomi was to exist as inserted into a extremely nonconcentric Mars orbit by using the periareion 300 klick above the surface, an apoareion of Xv Mars radii, & an inclination of 170 degrees with respect to the ecliptic plane. Shortly when insertion, a mast & antennas were to exist as deployed. A periareion would keep around been lowered to 150 kilometre, a orbital time to astir 38.Quintuplet hours. A space vehicle was to exist as spin stabilized at Vii.Cinque rpm with its spin axis (and a dish) pointed towards Globe. A point of periapsis part of the orbit would develop let in-unmoved measuring of the thermosphere and lower exosphere & remote sensing of the lower atmosphere and surface. A further distant area of the orbit would become for learn of the ions and neutral gas escaping from Mars & their interactions using a solar wind. A nominal mission was planned for a single martian season (around ii Globe years). A long mission will use allowed operation of the mission for 3 to 5 years. A space vehicle was as well to point its cameras at a martian moons Phobos and Deimos.

Spacecraft and subsystems

A Nozomi satellite occurs as Nought.58 meter high, Unity.Hexad meter square prism with truncated corners. Extending retired from either 2 paired sides come solar panel wings containing silicon solar cells which provide power to the spacecraft directly or even via NiMH (nickel metal hydride) batteries. On a top surface occurs as saucer, & the propulsion unit protrudes from either the bottom. a Cinque m deployable mast & the Ace m boom extend from either the sides, along by having 2 pairs of thinly wire antennas which measure Fifty m tip to tip. More instruments come too intended along a sides of the ballistic capsule. Space vehicle communications come via X-band at 8410.93 MHz and S-band at 2293.89 MHz. the Fourteen instruments carried in Nozomi come an imaging camera, neutral mass mass spectrometer, dust counter, thermal plasma analyser, gaussmeter, negatron & ion spectrum analyser, ion mass spectrograph, high energy particles experiment, VUV imaging spectrometer, sounder & plasma wave detector, LF wave analyser, negatron temperature probe, & a UV market scanner. A number mass budgeted for the science instruments was 33 kilo. Radio science experiments were besides imaginable using the existent radio devices & an ultrastable oscillator. A aggregate mass of Nozomi at launch including 282 kilogram of propellent was 540 kilo.

Canada was a partner inside this international Mars mission, getting provided a $5 million American-built thermal plasma analyzer. This was a Canadian Space Agency's first interplanetary mission.