This paper develops an automatic balancing system for the simulator. This system calculates the system center of mass by analyzing the dynamic sensor data along with the integrated equations of motion. The algorithm uses the method of least squares to estimate the vector from the center of rotation to the center of mass. The center of mass of the simulator is then moved near to the center of rotation by means of movable masses that are adjusted to the correct location. The algorithm is able move the center of mass to a location closer than two hundredths of a millimeter from the center of rotation. This adjustment increases the period of oscillation of the simulator to more than 60 seconds.

]]>The RAMOS program consists of mapping the earth's surface in stereo using two co-orbital satellites. The American Observational Satellite (AOS) will utilize an infrared radiometer with the telescope focal plane assembly (FPA) operating at approximately 60 K. The FPA will be cooled using a multiple cryocooler configuration. The use of multiple coolers introduces redundancy into the cooling system-a redundancy which has been absent from many previously flown satellites. In addition, the cooling system will incorporate various other new technologies, such as thermal disconnects, a thermal storage unit, low-resistance flexible thermal links, etc., to meet the overall system objectives and requirements. Thermal storage units are discussed as a means of eliminating cryocooler self-induced vibration and passively controlling FP A temperatures. Incorporating thermal switches and thermal storage units into a cooling system design can alleviate the concerns of cryocooler vibration and parasitic heat loads. An understanding of these concepts and configurations will assist in the design of similar optical instruments for both space-based and ground-based exploration campaigns.

]]>The information gained in this study will aid in refining burner modeling efforts and allow interpretation of planned aluminum combustion studies in hopes of gaining a greater understanding of distributed combustion as a driving mechanism in the combustion instability of solid propellant rocket motors.

]]>σ^{0} is calculated by dividing the power received by the conversion factor X, which is a function of the spacecraft and antenna positions. Because it is computationally expensive to calculate X for each data point the X factor algorithms proposes the use of a pre-computed table of nomimal X values for various scan angles and orbit positions. Unfortunately, the table does not take into account any variations in the orbit, or perturbations to the attitude of the spacecraft.

A perturbation correction algorithm is developed which uses the shift in baseband frequency (Δ*f*) resulting from various perturbations to correct the nominal values of X. Using the combination of the X factor table and the Δ*f* correction, σ^{0} can be retrieved rapidly and accurately. This algorithm will be used to calculate σ^{0} for the upcomming Quikscat and Sea Winds missions.