This space papercraft is the Mars Polar Lander, the scale of this paper model is 1:24. The Mars Polar Lander (Original Site), also referred to as the Mars Surveyor '98 Lander, was a 290-kilogram robotic spacecraft lander, launched by NASA on January 3, 1999, to study the soil and climate of Planum Australe, a region near the south pole on Mars, as part of the Mars Surveyor '98 mission. However, on December 3, 1999, after the descent phase was expected to be complete, the lander failed to reestablish communication with Earth. It was determined the most likely cause of the mishap was an improperly ceased engine firing prior to the lander touching the surface, causing the lander to impact at a high velocity.
The lander spacecraft is 3-axis stabilized during the cruise phase and during the entry, descent, and landing event except while descending under the parachute. Lander unique hardware required to accomplish the landing include an aeroshell and parachute with Viking and Mars Pathfinder heritage; and a modified, military 4 beam doppler radar to update trajectory estimates during the terminal descent phase. RCS thrusters are used to maintain spacecraft attitude during flight.
The lander employs the same star camera, inertial measurement unit, transponder, solid state power amplifier, RAD6000 processor, and power subsystem electronics as the orbiter. Primary communication between the lander spacecraft and earth during cruise are via an X-band link through a fixed medium gain antenna mounted on the cruise stage. The primary downlink communications during the surface mission are via a relay link through either the Mars Global Surveyor orbiter or the 1998 Mars Surveyor orbiter.
The relay links are backed up by a direct link to Earth via an articulated (2 axis) medium gain antenna mounted on the lander deck. Commands are transmitted direct from Earth to the lander via the medium gain antenna. Power is generated using two gallium arsenide solar array wings (total area 3.1 m2) mounted to the cruise stage during cruise and via two gallium arsenide solar array wings (total area 2.9 m2) deployed from the lander after touchdown on the Martian surface. NiH2 16 amp-hour common pressure vessel batteries provide power during low solar insolation periods and during peak power operations. A loop heat pipe is the primary method of lander thermal control and all temperature sensitive electronics are isolated within an insulated thermal enclosure. The lander structure, like the orbiter, is aluminum honeycomb with composite face sheets. The mass of the lander spacecraft at launch is estimated at 618 kg fully fueled with a dry mass of 562 kg including the micropenetrators.
You can download this space paper model from here: Space Papercraft - Mars Polar Lander (Landed Configuration) Free Download