This paper describes the methodology used to develop the spacecraft pointing stability constraints and instrument disturbance limits for the Geostationary Operational Environmental Satellite (GOES) R series of spacecraft launching on or after 2012. Instrument line of sight stability and control requirements drive the spacecraft pointing stability constraints. In turn, the spacecraft constraints are used to define the instrument disturbance limits. The resulting limits on the spacecraft and instruments are defined in terms of spacecraft pointing error displacement, velocity and acceleration.
An algorithm has been developed to determine deformations of a cantilever honeycomb plate under arbitrary loading conditions. The algorithm utilizes strain information from a set of sixteen fiber Bragg grating sensors, mounted on the plate so that all sensors measure strains along the clamped-free direction. The sensors are interrogated using a wavelength-division multiplexing scheme. A two-dimensional bi-polynomial function which represents the strain field is created using a least-squares algorithm. This function is integrated twice with the known boundary conditions applied to yield the deformation field for the plate. Maximum differences between finite-element solutions and least-squares estimates did not exceed 29.0 percent for any of the 16 investigated load scenarios. However, when considering areas of maximum deflection, the least-squares estimates did not exceed 13.3 percent difference. The algorithms used to interrogate the sensors, perform the strain-displacement calculations, and generate a real-time (approximately 4 Hz) mesh of displacement are encoded in a C program.