th steering capabilities similar to that on the Apollo spacecraft. The Apollo pointing system is more than sufficient for the communication link with earth.
It is also recommended that a communications satellite for Earth link capabilities be placed in a halo orbit about the L2 Lagrangian point. The satellite would allow transmissions to be made between the lander and earth when the lander is on the far side of the moon.
Communications between the OTV and the lander will be done with a VHF system. This system will be necessary for docking procedures. Once the lander is docked with the OTV a data feed umbilical will be connected to the lander by means of a manipulator arm on the OTV.
Communications between the lander and unloader will be done using a UHF system. The UHF receivers and transmitters are small, lightweight, and require little power. The UHF antennas are also small.
The energy for the power system is provided by the heat generated during engine cool down cycles. A power conversion loop transforms the heat into electrical energy, which is then stored in rechargeable Na-S batteries on the lander and the unloader. The conversion loop also serves to cool down the nuclear motors and keep the batteries at a higher operating temperature.
Two sets of batteries provide 11 kWh of power on both the lander and the unloader. The power for the unloader allows it to carry the payload 5 km at a speed of 2.5 km/hr. In the event that the unloader remains on the surface for an extended period, two solar arrays totalling 20 sq. m. are mounted on the unloader. These GaAs/Ge arrays are able to recharge the batteries fully in about one solar day. The solar arrays are also used to heat the unloader's batteries during payload transport.
Thermal control will be done using several methods. The first method will employ the use of a cryogenic refrigeration system that will be powered by the power generation loop. The second method will employ the use of 2 1/2" of multi-layer insulation on the propellant tanks and other areas that require thermal control. Heat exchangers on the power generation loop will also be used to keep certain areas of the lander warm.
The final method that will be used is the use of two radiation/thermal protection umbrellas. These umbrellas will be deployed from the landing struts after the complete rotation sequence has been performed. The umbrellas will help to reduce the work load on the refrigeration system considerably.
The management structure of RS Landers was designed for speed of communications between all group members. Progress and problems, for example, are reported directly to the C.E.O. and the Technical Supervisor. The final design is the compilation of input from all group members. All milestones for the project were completed on time.
The actual total cost of the project was $27,457. This is 2% less than the cost that was estimated at the start of the project.
CSR/TSGC Team Web