A wireless device receives access network information indicating an access network type. Based on the access network type, a non-access stratum (NAS) period is selected among: a first value associated with a geostationary earth orbit (GEO) non-terrestrial network (NTN) access network type; and a second value associated with a low earth orbit (LEO) NTN access network type. A NAS procedure is initiated by sending a NAS request message. A start of the NAS period is based on the sending. The NAS procedure is aborted based on an expiry of the NAS period.

A wireless device receives access network information indicating an access network type. Based on the access network type, a non-access stratum (NAS) period is selected among: a first value associated with a geostationary earth orbit (GEO) non-terrestrial network (NTN) access network type; and a second value associated with a low earth orbit (LEO) NTN access network type. A NAS procedure is initiated by sending a NAS request message. A start of the NAS period is based on the sending. The NAS procedure is aborted based on an expiry of the NAS period.

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.

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.

An adjustable payload for small geostationary communication satellites is disclosed. In an example, a communication satellite includes a payload system having a software defined payload that is configured to provide communication services. The software defined payload includes a processor for providing at least one of gain control per transponder and carrier/sub-channel, channelization, channel routing, signal conditioning or equalization, spectrum analysis, interference detection, regenerative or modem processing, bandwidth flexibility, digital beamforming, digital pre-distortion or power amplifier linearization, for at least one user slice for a plurality of user terminals and at least one gateway slice for a gateway station. The software defined payload also includes an input side and an output side for each slice. Each input side includes an input filter and an analog-to-digital converter and each output side includes an output filter and a digital-to-analog converter. The payload system also includes antennas communicatively coupled to the software defined payload.

An adjustable payload for small geostationary communication satellites is disclosed. In an example, a communication satellite includes a payload system having a software defined payload that is configured to provide communication services. The software defined payload includes a processor for providing at least one of gain control per transponder and carrier/sub-channel, channelization, channel routing, signal conditioning or equalization, spectrum analysis, interference detection, regenerative or modem processing, bandwidth flexibility, digital beamforming, digital pre-distortion or power amplifier linearization, for at least one user slice for a plurality of user terminals and at least one gateway slice for a gateway station. The software defined payload also includes an input side and an output side for each slice. Each input side includes an input filter and an analog-to-digital converter and each output side includes an output filter and a digital-to-analog converter. The payload system also includes antennas communicatively coupled to the software defined payload.

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 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.

Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite. In-orbit space situational awareness systems, comprising one or more in-orbit host satellites having one or more enhancement modules attached thereto, the enhancement modules comprising sensors such as satellite spatial location/position sensors, range sensors, navigation sensors, and/or proximity sensors for detecting other objects in-orbit, their location, speed, acceleration, orbital trajectory or the like, wherein the enhancement modules communicate to create a mesh network between the satellites.

A multi-mode communication adapter system comprising: a mobile Earth station including: a flat panel antenna configured to receive a down-link satellite packet, wherein the flat panel antenna includes a waveguide interposer, a satellite Rx/Tx, coupled to the flat panel antenna, configured to decode the down-link satellite packet, a storage device, coupled to the satellite Rx/Tx, configured to store satellite data from the down-link satellite packet, a first interface module, coupled to the storage device, configured to encode and transfer the satellite data as a cellular communication packet, a second interface module, coupled to the storage device, configured to encode and transfer the satellite data as a WiFi packet, and a multi-band transceiver, coupled to the first interface module and the second interface module, configured to concurrently transfer the cellular communication packet and the WiFi packet without accessing a local infrastructure; and a protective cover encloses the mobile Earth station.