The invention concerns a suborbital space traffic control system that comprises: a radar system configured to monitor a predetermined suborbital region and detect and track objects in the predetermined suborbital region. The objects include vehicles and space debris; and a suborbital space traffic monitoring system configured to: receive, from the radar system, tracking data related to the objects detected and tracked by the radar system; monitor, on the basis of the tracking data, trajectories of the objects in the predetermined suborbital region using one or more predetermined machine-learning techniques to detect potentially hazardous situations for the vehicles in the predetermined suborbital region; and, if it detects a potentially hazardous situation for one or more given vehicles, transmit corresponding alarm messages to the given vehicle(s).

A projection unit (12) of an interference power estimation device (1) projects an orbit of a satellite onto a map representing a ground surface. A range acquisition unit (13) determines a plurality of ranges on the map so that the projected orbit is included in the ranges. An altitude calculation unit (14) calculates an altitude of the orbit of the satellite in each of the ranges. A range interference calculation unit (16) calculates, for each of the ranges, an interference power between the satellite at a position determined by a latitude and a longitude of the range and the altitude calculated for the range and a radio station installed on the ground surface. An estimation result calculation unit (17) selects, as an estimation result, a maximum value among the interference powers calculated for each of the ranges.

A signal receiver method to achieve satellite position fix by improving satellite orbit prediction includes: acquiring satellite signals and navigation data and calculating a position solution, which includes predicting the state or orbit of one or more satellites. The prediction includes using a model of the solar radiation pressure operating on a selected satellite. The method includes: expressing the model of the solar radiation pressure operating on the satellite as a Fourier series having a frequency function of the satellite-Earth-Sun angle and having respective Fourier coefficients, calculating position approximation errors comparing true satellite positions at given time points against predicted satellite positions at corresponding time points, estimating said Fourier coefficients as a function of the position approximation errors, and using the estimated Fourier coefficients in the model of the solar radiation pressure operating on the satellites as a Fourier series used in the model to predict the state or orbit of the satellite.

For power-enhanced slew maneuvers, a method determines a power collection function for a satellite. The method determines a power cost function for the satellite. The method calculates a power enhanced slew maneuver based on the power collection function and the power cost function.

A transfer type contra-rotating geomagnetic energy storage-release delivery system is disclosed. The system includes a control system, a three-axis control moment canceller and an energy system, which are arranged on a delivery mother spacecraft, and the delivery mother spacecraft is connected, through support rod structures, with a strong magnetic moment generating device, a contra-rotating transmission mechanism and two delivery connection rod structures arranged at the two ends of the contra-rotating transmission mechanism, the strong magnetic moment generating device is arranged between the contra-rotating transmission mechanism and the delivery mother spacecraft, the two delivery connection rod structures are provided with slidable mass blocks respectively, and the strong magnetic moment generating device and the contra-rotating transmission mechanism provide energy through the energy system. The strong magnetic moment generating device is free of accelerated rotation of an attitude, thereby decoupling the dual coupling.

A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.

A modular satellite for converting solar energy to microwave energy and transmitting the microwave energy to the earth to be converted into electricity includes solar panels configured to convert solar energy into direct current; a magnetron operatively connected to the solar panels to receive the direct current and configured to convert the direct current into microwave energy; a planar wave guide antenna operatively connected to the magnetron to receive the microwave energy and direct the microwave energy to a station on earth; and a coupling system for coupling with another satellite to form an array in response to at least one of locking, unlocking, and navigational commands. The satellite has a mass equal to or less than four kilograms, and a volume equal to or less than three liters.

An operation of a spacecraft is controlled using an inner-loop control determining first control inputs for momentum exchange devices to control an orientation of the spacecraft and an outer-loop control determining second control inputs for thrusters of the spacecraft to concurrently control a pose of the spacecraft and a momentum stored by the momentum exchange devices of the spacecraft. The outer-loop control determines the second control inputs using a model of dynamics of the spacecraft including dynamics of the inner-loop control, such that the outer-loop control accounts for effects of actuation of the momentum exchange devices according to the first control inputs determined by the inner-loop control. The thrusters and the momentum exchange devices are controlled according to at least a portion of the first and the second control inputs.

A method and apparatus for the control of the attitude of earth orbiting satellites and the orbit and attitude control of a novel gravitational wave detection satellite configuration located near the sun-earth Lagrangian points L3, L4 and L5, utilizing the control of solar radiation pressure by the use of electrically controllable variable reflection glass panels to provide the torques and forces needed.

Apparatus and methods for stationkeeping in a satellite. The satellite includes a north electric thruster and a south electric installed on a zenith side. An orbit controller selects a duration of a burn of the north electric thruster proximate to an ascending node that differs from a duration of a burn of the south electric thruster proximate to a descending node. The orbit controller is configured to select an offset of the burn of the north electric thruster in relation to the ascending node that differs from an offset of the burn of the south electric thruster in relation to the descending node.