For Thermal Control Sample Clauses

For Thermal Control. A tabulation of unit operating and non-operating design, acceptance and qualification temperature limits for all units in the spacecraft and the temperature gradients between the qualification temperature control location and the flight sensor. The flight sensor limits necessary to detect that temperatures are within thermal design limits on all units shall be separately defined. A complete set of steady state minimum and maximum thermal predictions for all units at beginning and at end-of-life conditions at solstice and at equinox and in transfer orbit, for thrusters in all operational modes, and transient predictions for the battery in all charge and discharge and reconditioning states. The predictions shall include definition of the configurations assumed in these analyses. The thermal sensitivity to operation of varying numbers and configurations of each type of unit and each heater shall be specified. Sensitivity information shall be provided for payload units at no-drive and at saturation. A description of the minimum and maximum survival thermal configurations including limiting factors. The minimum thermal configuration shall be defined for a nominal operational environment and the minimum survival thermal configuration (non-operational) shall be defined for recovery conditions defined in the contingency plans. The maximum thermal survival configuration shall be defined for the maximum payload configuration which shall not exceed thermal design limits at both beginning-of-life and at end-of-life conditions (worst case season). Figures showing the location of all temperature telemetry and control sensors shall be included. Schematics of all systems indicating type of control, heater resistance, and identification of controlling element (e.g., thermostat, thermistor), shall be provided. Summary data from the Solar Beam and spacecraft thermal vacuum test shall be included in tabular and graphical form.