Thermal - Lamar 2/23/96 Progress Report

From: Mark A. Magee This Week:

Work has begun on revising the proposal. The revised proposal will include the revised scope of the project, a time schedule, as well as more information from the work that was done in the previous semester. The new propsed scope for this semester is similar to the following:

Concerning the Active Thermal Control System (ATCS):
1. Define heat loads and operating temperatures of the components of the spacecraft.
2. Devise a system layout, including:

a. A general schematic of the ATCS.
b. Study each component in the schematic.
c. Look into gas, liquid, and two-phase radiators.
d. Look into the necessary pumps, radiator configurations, and fluids to be used in the ATCS.
3. Build an analytical model of the ATCS.
4. Run design studies on the analytical model.
5. Analyze the data obtained from the model.
6. Research the necessary components to be used in the ATCS that correspond to the system specifications
7. Documentation - such as: figures, data, report, presentation, etc...

Research has also continued on Aerogel, Thermal Insulation, and Radiator Design. This information listed below was not obtained until today (2-22-96); therefore, the information has not been looked into in depth. This information has been supplied by the U.T. System Integration team (Aerogel information) and Dr. William Simon (thermal insulation and radiator design). Following is a short summary of what is expected to be found in this literature:

1. Integrated Lightweight Structure and Thermal Insulation for Mars Rover.

a. Thermal performance of Aerogel
b. Thermal conductivity vs. Density (silica Aerogel)
c. The insulation configuration on the Mars Rover
2. Use of Insulation on Spacecraft.
a. Various Materials
- Thermal Conductivities
b. Multi-Layer Insulation (MLI)
- Blanket Construction
c. Theory of Radiation Shields
- Radiation Shield Materials
3. Aerogel Properties
a. Physical, Thermal, Optical,
b. Thermal Conductivity vs. Pressure
c. Radiation Transmission vs. Wavelength
d. Compressive Strength
e. Conductivity vs. Pressure
f. How to model the heat transfer

Thermal Insulation
1. Thermal Insulations Systems

a. Applications of Thermal Insulations
b. Principles of Therma Insulation Systems

Radiator Design
1. Radiator Design for Space Vehicles.

a. Thermal Design
b. Meteroids and Meteroid Protection
c. Radiator Thermal Control
d. Selection of Heat-Transport Fluids
e. Surface Coatings
f. Special Radiator Coatings

Next Week:
More information will be given on the information that was gathered (listed above). Also, the revised proposal will be turned in, including a detailed time-line for the semester.

mass: 45 kg
power: 45 W