payload toward a selected azimuth direction in fig2 the the monoprop embodiment of the lander 10 is shown to scale 36 in feet with other notable lunar artifacts such as the surveyor lander 38 an apollo moonwalking astronaut 40 the lunar roving vehicle 42 and lunar excursion module 44 it is especially poignant to compare the relative size of the spinning lander to surveyor demonstrating how efficient the spinning lander architecture can be since the functionality of the two systems on the lunar surface is comparable again a key feature of the present invention is that landing legs have been added to the despun section of the lander in fig3 the top end of the spinning section 12 is shown as a rotor mechanically connected to the despun section 14 via the despin motor bearing assembly 48 a triaxial rf antenna 50 essentially of the same design as the syncom geosynchronous satellite from the early 1960s is shown rigidly attached the spinning section aligned with its spin axis not all details of this antenna design are drawn all communications with the lander u2014 telemetry command and wideband data from the moon u2014 are via this antenna and the communication system on the spinning section of the lander the despun section structure consists of a despun shelf structure 46 which overlays and protects the spinning rotor below it the landing legs 20 1 or more and microwave transparent antenna mast 16 the separately rotatable despun payload module 18 is shown at the top of the antenna mast affixed to the payload module pan platform 54 with its.