A system may include an ad hoc satellite network including multiple satellites, a first terminal, and a second terminal. Each of the first satellite and a second satellite of the multiple satellites may include: a receive high frequency (HF) antenna configured to receive HF signals; a transmit HF antenna configured to transmit HF signals; an inter-satellite transmitter configured to transmit signals to another satellite of the ad hoc satellite network; an inter-satellite receiver configured to receive signals from another satellite of the ad hoc satellite network; and a processor. The first terminal may include an HF transmit antenna configured transmit an HF communication payload to the ad hoc satellite network. The second terminal may include an HF receive antenna configured receive the HF communication payload from the ad hoc satellite network.

The described features generally relate to receiving one or more positioning signals at a satellite terminal during installation of the satellite terminal at a customer premises, and providing position-based access to a satellite communications system based on a satellite terminal installation position determined from the received positioning signals. The determined installation position of the satellite terminal may then be employed for various network access techniques, such as providing access to the satellite communications system, providing position-based content, or restricting content via the satellite communications system based on the determined installation position. In some examples the determined installation position of the satellite terminal may be used to approximate a propagation delay between the satellite terminal and various devices of the satellite communications system, such as a serving satellite and/or a serving gateway, to improve device synchronization and radio frequency spectrum resource utilization.

A formation flight control device for generating and outputting orbit control information for controlling observation satellites in an observation satellite group orbiting a celestial body and sequentially observing a ground surface of the celestial body with an observation interval includes an orbit information acquirer, an orbit control information generator, and an orbit control information outputter. The orbit information acquirer acquires orbit information indicating an observation time of a preceding observation satellite of which an observation order precedes by one, and an orbit of the preceding observation satellite at the observation time. The orbit control information generator generates, based on the orbit information, the orbit control information indicating an orbit and a phase allowing flying, after the observation interval, vertically above an intersection point between the ground surface and a straight line connecting a center of the celestial body and the preceding observation satellite at the observation time.

This application relates to the field of communication technologies, and discloses a communication method and a communication apparatus, to resolve a problem of a poor interference suppression effect caused by closing an edge beam of a satellite. The method includes: A first satellite sends a first message to a second satellite. The first message includes information about a frequency reuse scheme. The information about the frequency reuse scheme includes basic unit information. The basic unit information includes central point locations and frequency information of at least N−1 beams. Herein, N is a frequency reuse factor of the first satellite. At least N−1 different pieces of frequency information exist in the frequency information that is of the at least N−1 beams and that is included in the basic unit information. In addition, N is a positive integer greater than or equal to 3.

The present invention relates to satellite systems and more particularly, to the provision of a satellite system and method for communications applications, with global coverage. An optimal method of providing global broadband connectivity has been discovered which uses two different LEO constellations with inter-satellite links among the satellites in each constellation, and inter-satellite links between the constellations. The first constellation is deployed in a polar LEO orbit with a preferred inclination of 99.5 degrees and a preferred altitude of 1000 km. The second constellation is deployed in an inclined LEO orbit with a preferred inclination of 37.4 degrees and a preferred altitude of 1250 km.

Techniques, systems, devices, and methods for utilizing a mobile communicator for communicating with multiple satellites, e.g., simultaneously over an interval of time, are disclosed. The mobile communicator is disposed on a vehicle, and the multiple satellites may be disposed in different satellite constellations operating in different orbits. The mobile communicator establishes multiple communication links to the multiple satellites by utilizing only the set of antenna resources provided by a single antenna platform or array. Subsets of the antenna resources are dynamically apportioned and adapted, e.g., while the vehicle travels, to establish and maintain different communication links to different satellites via different spatial channels and their respective air interfaces to thereby maintain optimal satellite communicative connectivity. On-board connectivity services for personal electronic devices and/or other on-board applications may be supported by the disclosed techniques.

Aspects of the disclosure describe methods and systems for transmitting data via a satellite to a ground node. In one exemplary aspect, a method comprises splitting, on a satellite, a data segment into a plurality of data chunks, wherein an amount of the data chunks equals a number of ground nodes that the data chunks will be transmitted to. For each respective data chunk, the method comprises determining whether the satellite has a stable connection with the respective ground node. When the satellite has the stable connection with the respective ground node, the method comprises transmitting, by the satellite, the respective data chunk to the respective ground node, and when the satellite does not have the stable connection with the respective ground node, the method comprises transmitting, by the satellite, the respective data chunk to a neighboring satellite for storage until the stable connection is established.

A method is provided for setting an attribute of a link between an aerial network node and another node. The method comprises determining that a geographic condition of the link in relation to the aerial network node is satisfied. The method further comprises setting at least one attribute of the link to match at least one attribute associated with the geographic condition. Further, an aerial network node is provided including a network interface, a processor, and a non-transient computer readable memory for storing instructions which when executed by the processor configure the aerial network node to determine that a geographic condition of a link between the aerial network node and another node, in relation to the aerial network node is satisfied. The network node is further configured to set at least one attribute of the link to match at least one attribute associated with the geographic condition.

A method for determining a maximum transmission power (Pmax, PR, PO) of a non-geostationary satellite (NGSO1, NGSO2) in the direction of a ground station (GSO_SOL), includes the steps of: determining the minimum value of a topocentric angle (αNGSO1, αNGSO2), formed between the non-geostationary satellite, the ground station and a point of the geostationary arc (ARC_GSO); comparing, in terms of absolute value, the minimum value of the topocentric angle with at least two threshold values (αr, αo), such that: if it is less than the first threshold (αr), defining the maximum transmission power at a first value (PR), if it is between the first threshold and the second threshold (αo), defining the maximum transmission power at a second value (PO), greater than the first value, or if it is greater than the second threshold, defining the maximum power at a third value (Pmax), greater than the second value; the maximum transmission power values and the thresholds being determined so as to minimize the deviation between a distribution of the power levels received by the station (GSO_SOL) and added over a time interval and a reference distribution (REF), greater than the distribution of the power levels.

A system, architecture and method for data handling, computation, and communication for Earth-based and space-based activities through the use of ground and space-based systems. The system architecture may include a Core Space Layer. The system architecture may further include an Earth User Layer, a Relay Layer, a Computing Layer, a Terrestrial Communications Layer, and a Space User Layer. The Computing Layer is a cloud-based architecture that serves to reduce bandwidth burdens on Earth-Space trunk by processing data into manageable streams of information. The Core Space Layer contains LEO satellites, one of which may act as a dedicated computing node. The Core Space Layer may operate in a public and/or private mode with a first constellation of LEO satellites operating in a private mode and a second constellation of LEO satellites operating in a public mode.