SpiritCourtesy of NASA's National Space Science Data Center
On-orbit dry mass: 185 kg
Launch Site/Country: Cape Canaveral, United States
Vehicle: Delta II 7925
The "Spirit" rover (Mars Exploration Rover A) is one of the two rovers launched to Mars in mid-2003. The rovers will arrive at Mars in January of 2004 equipped with a battery of scientific instruments and will be able to traverse 100 meters a day. The nominal plan calls for the missions to last for 90 days, until April 2004, but it is likely the mission will last beyond this time. The scientific goals of the rover missions are to gather data to help determine if life ever arose on Mars, characterize the climate of Mars, characterize the geology of Mars, and prepare for human exploration of Mars. To achieve these goals, seven science objectives are called for: 1) search for and characterize a variety of rocks and soils that hold clues to past water activity, 2) determine the distribution and composition of minerals, rocks, and soils surrounding the landing sites, 3) determine what geologic processes have shaped the local terrain and influenced the chemistry 4) perform "ground truth" of surface observations made by Mars orbiter instruments, 5) search for iron-bearing minerals, identify and quantify relative amounts of specific mineral types tha contain water or were formed in water, 6) characterize the mineralogy and textures of rocks and soils and determine the processes that created them, and 7) search for geological clues to the environmental conditions that existed when liquid water was present and assess whether those environments were conducive to life.
The Mars Exploration Rover consists of a box-like chassis mounted on six wheels. The chassis contains the warm electronics box (WEB). On top of the WEB is the triangular rover equipment deck, on which is mounted the Pancam mast assembly, high gain, low gain, and UHF antennas, and a camera calibration target. Attached to the two forward sides of the equipment deck are solar arrays which are level with the deck and extend outward with the appearance of a pair of swept-back wings. Attached to the lower front of the WEB is the instrument deployment device, a long hinged arm which protrudes in front of the rover.
The wheels are attached to a rocker-bogie suspension system. Each wheel has its own motor and the two front and two rear wheels are independently steerable. The rover has a top speed of 5 cm per second, but the average speed over time on flat hard ground would be 1 cm/sec or less due to the hazard avoidance protocols. The rover is designed to withstand a tilt of 45 degrees without falling over, but is programmed to avoid exceeding tilts of 30 degrees. The warm electronics box houses the computer, batteries, and other electronic components. The box is designed to protect these components and control their temperature. Thermal control is achieved through the use of gold paint, aerogel insulation, heaters, thermostats, and radiators.
Power is provided by the solar arrays, generating up to 140 W of power under full Sun conditions. The energy is stored in two rechargeable batteries. Communications with Earth are in X-band via the high gain directional dish antenna and the low gain omni-directional antenna. Communications with orbiting spacecraft are through the UHF antenna. The onboard computer has 128 Mb RAM. An inertial measurement unit provides 3-axis information on position.
The rover carries a suite of instruments for science and navigation. The panoramic camera (Pancam) and navigation cameras are mounted on top of the Pancam mast assembly, at a height of about 1.4 meters from the base of the wheels. The mast, mounted at the front of the equipment deck, also acts as a periscope for the Miniature Thermal Emission Spectrometer (Mini-TES). Attached to the end of the instrument deployment device are the Alpha Particle X-Ray Spectrometer (APXS), Mossbauer Spectrometer (MB), Microscopic Imager (MI), and Rock Abrasion Tool (RAT). A magnet array is attached to the front of the equipment deck. Two hazard avoidance cameras are mounted on the front of the rover and two on the rear. The group of science instruments (Pancam, Mini-TES, APXS, MB, MI, and RAT) is known as the Athena science package.
The rover will be compactly stowed in a tetrahedron shaped landing platform and encased in an aeroshell consisting of a heat shield and a backshell for launch, cruise, and atmospheric entry. The lander platform has a mass of 348 kg, the backshell and parachute 209 kg, and the heat shield 78 kg. The cruise stage mass is 193 kg and propellant mass is 50 kg.
Spirit was launched on a standard Delta II 7925 on 10 June 2003 at 17:58:46.773 UT. After insertion into a circular Earth parking orbit, the spacecraft was despun and the third stage was reignited to put the craft on a trajectory to Mars, after which the aeroshell, lander, and rover separated from the third stage. The cruise phase to Mars ended on 20 November 2003, 45 days before Mars entry. The approach phase lasted from this date until martian atmospheric entry on 4 January 2004. On entry the lander and components had a mass of 827 kg and were travelling at 19,300 km/hr. The aeroshell decelerated the lander in the upper martian atmosphere for about four minutes to a velocity of 1600 km/hr, followed by deployment of a parachute. The parachute slowed the spacecraft to about 300 km/hr. A series of tones was transmitted by the spacecraft during entry and after landing to indicate the successful completion of each phase. Just prior to impact, at an altitude of about 100 m, retrorockets slowed the descent and airbags were inflated to cushion the impact. The craft hit at roughly 50 km/hr and bounced and rolled along the surface. After it stopped the airbags deflated and retracted, the petals opened, and the rover deployed its solar arrays. The landing took place at 04:35 UT on 4 January 2003 (Earth rceived time), (11:35 p.m. Jan. 3 EST) approximately 2:00 p.m. local time, about one hour before Earth set, in Gusev Crater, roughly 15 degrees south of the equator. On Mars it is the latter half of southern summer. The landing ellipse is centered at 14.82 S, 184.85 W and is 96 km by 19 km oriented at 76 degrees. About three hours after landing the first images were returned to Earth, showing a flat plain littered with small rocks. Gusev Crater was chosen as a landing site because it has the appearance of a crater lakebed. If Gusev was at one time filled with water, the bottom of the crater may contain sedimentary deposits laid down in the submarine environment.
An egress phase will take place over the first few days, involving deployment of the Pancam mast and high gain antenna, rover stand up, imaging and calibration, selection of proper egress path, and finally driving of the rover off the lander deck onto the martian surface. Roughly 90 days or more of surface operations, involving driving the rover, imaging, and use of the science instruments will follow. Some time after the 90 day period is over it is expected that a combination of decreasing power generation capability (as the solar panels become covered with dust the batteries lose capacity, and the Sun becomes more distant and moves in the sky north of the landing site), decreasing temperature (again, as the Sun moves further north in the sky) and increased communication power requirements (as Mars and Earth move away from one another) will result in eventual failure due to freezing of components or inadequate power.