Space Systems/loral, LLC

Saghir Munir

Xen Price

Darren R Stratemeier

Jorge Delgado

Yassir Azziz

Matthew Machlis

Jared Kauffman Gill

Justo Jacinto

Cloud mask image data is obtained by a secondary imaging payload disposed on a communications or broadcast satellite operating in geosynchronous orbit. The obtained cloud mask image data is provisioned for use, in near real time, by one or more low earth orbit imaging satellite systems. Provisioning the obtained cloud mask image data may include collecting the data on the ground and making it available to one or more operators of the one or more LEO imaging satellite systems and/or transmitting the data from the communications or broadcast satellite to at least one spacecraft in the one or more LEO imaging satellite systems.

Cloud mask data acquisition and distribution using geosynchronous communications or broadcast satellites

Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile. The desired profile places the satellite in an Earth-pointed attitude when the satellite is at a predefined point in the orbit, slews the satellite from the Earth-pointed attitude to an ideal orbit raising attitude, steers the satellite according to the ideal profile during orbit raising, and steers the satellite from the desired attitude to the Earth-pointed attitude.

Satellite orbit raising using electric propulsion

Spacecraft payload orientation steering is provided for an orbiting spacecraft in motion along an orbit track around a celestial body, the orbit track having a nominal inclination with respect to an equatorial orbit, a substantial eccentricity, and a drift angle with respect to the nominal inclination. Coordinates of an optimal payload target location as a function of a spacecraft position along the orbit track are determined, the target location being on the surface of the celestial body and having a substantial motion with respect to the surface and with respect to a spacecraft nadir. A payload of the spacecraft is substantially aligned with the determined coordinates by steering the satellite body to correct for at least one of the inclination drift angle, and the eccentricity, thereby adjusting the spacecraft orientation as a function of the spacecraft position along the orbit track.

Spacecraft payload orientation steering

Growing community of inventors

Union City, CA, United States of America

Saghir Munir