A lunar orbiting satellite system executes orbit planning of assigning a function (positioning, communication, and flashing) to an artificial satellite (AS) depending on a relative position of the AS to the moon at a time when the moon and the AS are observed from an input point on the earth, and correcting the relative position, which changes in accordance with the moon revolution period. The system includes: a satellite orbit planner which assigns a function to each ASs forming an AS group flying around the moon depending on a relative position of each ASs to the moon at a time when the moon and ASs are observed from an input point on the earth, and set a target orbit according to the function; and a satellite controller which causes the each ASs to execute control based on the function to implement switching of the function.

A method and transmission system for amplifying and providing navigation signals. The system comprises a splitter circuit configured to receive a plurality of radio frequency (RF) signals oscillating at at least two different frequencies f.sub.1 and f.sub.2. The splitter circuit is further configured to split and forward the RF signals having the f.sub.1 frequency to a first bandpass filter and the RF signals having the f.sub.2 frequency to a second bandpass filter. The system further comprises a first tunable amplifier configured to receive the RF signals from the first bandpass filter. The system further comprises a second tunable amplifier configured to receive the RF signals from the second bandpass filter at substantially the same time as the first tunable amplifier's receipt of the RF signals from the first bandpass filter. The first tunable amplifier is further configured to amplify its RF signals across a first band centered around the frequency f.sub.1. The second tunable amplifier is further configured to amplify its RF signals across a second band centered around the frequency f.sub.2. The amplified RF signals are fed substantially concurrently into a mixer circuit for transmission via an RF antenna to a navigation receiver.

A method of guidance for placing a satellite on station comprises the following steps carried out during a predefined current cycle: A) determining on the ground a law of orientation of the thrust vector, and a history of state variables and of adjoint state variables of the satellite for the transfer from a starting orbit to a target orbit using optimal control theory, B) determining on the ground a law of evolution of the rotation of the satellite about the thrust vector, on the basis of the orientation law and of the history, C) representing according to a predetermined format the evolution of the state variables and adjoint state variables so as to obtain first parameters, D) representing according to a predetermined format a law of evolution of the rotation so as to obtain second parameters, E) concatenating the first and second parameters so as to obtain a guidance plan for the satellite, F) downloading onboard the guidance plan, G) periodically repeating according to a predefined period which is smaller than the duration of the guidance cycle: g1) reconstructing onboard the satellite a guidance instruction, g2) executing onboard the satellite the instruction by applying a closed control loop, H) measuring on the ground the real orbital trajectory of the satellite, I) repeating steps A) to H) with the trajectory measured at the end of the cycle as starting orbit of the following cycle, until the target orbit is attained.

A method of guidance for placing a satellite on station comprises the following steps carried out during a predefined current cycle: A) determining on the ground a law of orientation of the thrust vector, and a history of state variables and of adjoint state variables of the satellite for the transfer from a starting orbit to a target orbit using optimal control theory, B) determining on the ground a law of evolution of the rotation of the satellite about the thrust vector, on the basis of the orientation law and of the history, C) representing according to a predetermined format the evolution of the state variables and adjoint state variables so as to obtain first parameters, D) representing according to a predetermined format a law of evolution of the rotation so as to obtain second parameters, E) concatenating the first and second parameters so as to obtain a guidance plan for the satellite, F) downloading onboard the guidance plan, G) periodically repeating according to a predefined period which is smaller than the duration of the guidance cycle: g1) reconstructing onboard the satellite a guidance instruction, g2) executing onboard the satellite the instruction by applying a closed control loop, H) measuring on the ground the real orbital trajectory of the satellite, I) repeating steps A) to H) with the trajectory measured at the end of the cycle as starting orbit of the following cycle, until the target orbit is attained.

A low-earth orbit (LEO) satellite includes a non-atomic clock configured to generate a clock signal, a navigation signal receiving and processing module, and a navigation signal generation and transmission module. The navigation signal receiving and processing module is configured to receive the clock signal from the non-atomic clock, receive first signaling including first timing data generated based on a high precision clock, and generate clock state data based on the clock signal and the first timing data. The navigation signal generation and transmission module is configured to receive the clock signal from the non-atomic clock, generate a navigation message that indicates the clock state data, generate a broadcast carrier signal by utilizing the clock signal, generate a navigation signal based on modulating the navigation message upon the broadcast carrier signal, and broadcast the navigation signal for receipt by at least one client device.

It is proposed a determination device, a method for determining navigation information and a navigation device comprising: a receiving circuit configured to receive a first signal from a first navigation satellite, the first signal comprising a first timestamp; a determination circuit configured to determine a velocity of the first navigation satellite at the first timestamp in a second coordinate system based on ephemeris data of the first navigation satellite, the second coordinate system being tilted in relation to the equatorial plane; the determination circuit further configured to determine a velocity of the first navigation satellite in a first coordinate system that is earth fixed and rotating with earth, by applying a transformation matrix to the determined velocity of the first navigation satellite in the second coordinate system and adding a correction term based on a time derivative of the transformation matrix; a navigation circuit configured to determine navigation information of the receiving circuit within the first coordinate system based on at least the determined velocity of at least the first navigation satellite.

Systems and methods for inherent fast Time To First position Fix (TTFF) and high sensitivity are described. An embodiment of a method may include interpolating a satellite position in response to a navigation message having initial conditions for satellite ephemeris data converted into Keplerian format, wherein signal fixation is maintained in response to receiving the navigation signal at least once per day.

Systems and methods for inherent fast Time To First position Fix (TTFF) and high sensitivity are described. An embodiment of a method may include interpolating a satellite position in response to a navigation message having initial conditions for satellite ephemeris data converted into Keplerian format, wherein signal fixation is maintained in response to receiving the navigation signal at least once per day.

Methods and apparatus for processing of GNSS data derived from multi-frequency code and carrier observations are presented which make available correction data for use by a rover located within the region, the correction data comprising: the ionospheric delay over the region, the tropospheric delay over the region, the phase-leveled geometric correction per satellite, and the at least one code bias per satellite. In some embodiments the correction data includes an ionospheric phase bias per satellite. Methods and apparatus for determining a precise position of a rover located within a region are presented in which a GNSS receiver is operated to obtain multi-frequency code and carrier observations and correction data, to create rover corrections from the correction data, and to determine a precise rover position using the rover observations and the rover corrections. The correction data comprises at least one code bias per satellite, a fixed-nature MW bias per satellite and/or values from which a fixed-nature MW bias per satellite is derivable, and an ionospheric delay per satellite for each of multiple regional network stations and/or non-ionospheric corrections. Methods and apparatus for encoding and decoding the correction messages containing correction data are also presented, in which network messages include network elements related to substantially all stations of the network and cluster messages include cluster elements related to subsets of the network.

Antennas used aboard vehicles to communicate with satellites or ground stations may have complex antenna patterns, which may vary as the vehicle moves throughout a given coverage area. Techniques are disclosed for dynamically adjusting the instantaneous power fed to an antenna system to ensure that the antenna transmits at the regulatory or coordinated effective isotropic radiated power (EIRP) spectral limit. The antenna may transmit, in accordance with vehicle location and attitude, steerable beam patterns at different scan and skew angle combinations, causing variations in antenna gain and fluctuations in the transmitted EIRP. Using on-board navigational data, an antenna gain and ESD limit may be calculated for a particular scan and skew angle, which may be used to adjust power fed to the antenna such that the antenna transmits substantially at maximum allowable EIRP as the steerable beam pattern is adjusted.