An object is to notify an appropriate intrusion alert by determining whether debris will intrude into an orbit area of a satellite constellation. A passage determination unit (110) determines whether debris will pass through a satellite orbit area, based on satellite orbit forecast information in which a forecast value of an orbit of a satellite is set and debris orbit forecast information in which a forecast value of an orbit of debris is set. When it is determined that debris will pass through the satellite orbit area, an alert generation unit (120) generates an intrusion alert (111) including a predicted time, predicted location coordinates, and predicted velocity vector information that relate to passage of the debris. An alert notification unit (130) notifies the intrusion alert (111) to a management business device (40) used by a management business operator that manages a satellite that flies in the satellite orbit area.

To control a mobile node group that performs a formation flight, mobile nodes constituting the mobile node group and a ground station that wirelessly communicates with each of the mobile nodes are included. The mobile nodes are classified into a follower mobile node and a leader mobile node that collects information on the follower mobile node and controls the follower mobile node. The mobile nodes wirelessly communicate with one another based on beamforming or MIMO. Based on an installed on-board processor, the leader mobile node controls the follower mobile node, and the mobile node controls a position or an attitude of the mobile node itself for performing the formation flight. The ground station performs link control of the wireless communication with the mobile node or link control of the wireless communication between the mobile nodes, and control of selecting any ground station that wirelessly communicates with the mobile node.

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. Clamps may be provided for attaching the enhancement module to an existing structural component of the in-orbit host satellite.

An outer space-based debris detection system may include a network of satellites. A first satellite may be configured to propagate a first series of solitary plasma waves through an outer space detection area having a debris body therein. The debris body propagates second plasma waves therefrom. A second satellite associated with the detection area may be configured to receive the first series of solitary plasma waves from the first satellite after interaction with the second plasma waves from the debris body to thereby detect the debris body.

A network device determines an exposure time associated with an image sensor coupled to a spacecraft for capturing an image of a target object orbiting the Earth. The network device computes a maximum relative angular velocity associated with the target object based on the exposure time and a dimension of a pixel of the image sensor. The network device identifies a first pointing direction of the image sensor for initiating a search for the target object. The network device generates a first angular velocity probability distribution map for the target object and divides the first angular velocity probability distribution map into a first set of angular velocity regions (AVRs). The network device selects a first AVR from the first set of AVRs for scanning by the image sensor and generates a search schedule that includes a first entry for informing the spacecraft to scan the first AVR.

There are provided methods of processing satellite state data, comprising receiving satellite state data in the form of multiple separate files via one or more ground stations and compiling the received satellite state data into a single dataset accessible via an application programming interface and searchable by time range. There are further provided methods of processing satellite state data comprising receiving raw satellite state data; receiving manoeuvre data relating to one or more scheduled manoeuvres of the satellite; and filtering the received raw satellite state data in an orbit determination process to provide filtered satellite state data, wherein the manoeuvre data is used in the filtering of the received raw satellite state data. There are further provided methods of scheduling a satellite manoeuvre comprising: receiving parameters for one or more planned manoeuvres to move the satellite from a current orbit to a new orbit, wherein the parameters include a time and duration of each of the one or more planned manoeuvres; receiving times of eclipses of the Sun by the Earth during future orbits of the satellite; and scheduling the manoeuvre to take place according to the determined parameters and the times of eclipses.

In a search and tracking method for full time-domain laser detection of space debris, a set of latest precision orbital parameters of a debris object and start and end moments of a current transit of the object are first obtained. Search-specific guidance data is generated based on the above information and in combination with estimation of a maximum along-track error of the orbital parameters of the object during the current transit. A DLR system performs multi-elevation search on the object based on the search-specific guidance data, obtains a plurality of pieces of detection data of the object after detecting the object during the search, determines an along-track error of the orbital parameters of the object based on the detection data, and corrects the orbital parameters of the object in real time based on the along-track error, so as to guide the DLR system to subsequently track and detect the object.

In a search and tracking method for full time-domain laser detection of space debris, a set of latest precision orbital parameters of a debris object and start and end moments of a current transit of the object are first obtained. Search-specific guidance data is generated based on the above information and in combination with estimation of a maximum along-track error of the orbital parameters of the object during the current transit. A DLR system performs multi-elevation search on the object based on the search-specific guidance data, obtains a plurality of pieces of detection data of the object after detecting the object during the search, determines an along-track error of the orbital parameters of the object based on the detection data, and corrects the orbital parameters of the object in real time based on the along-track error, so as to guide the DLR system to subsequently track and detect the object.

The disclosed methods, systems, and kits provide the ability to deliver entire clean sheet designs from concept to first hot fire in under six weeks with instant specific impulses above 330 seconds in some of our engines. In examples, thrusters can be delivered that are at less than half of the mass budget allowable for them and they can be delivered in weeks.

The invention relates to a system and method for autonomous navigation of a host satellite equipped with moving and orienting means, a unit for controlling these means, and at least one on-board image-acquisition camera, said method comprising the following steps: acquiring (E1) a plurality of images; default processing of said images, referred to as long-range processing (E2), configured to detect and identify space objects and to calculate their relative orbits; conditional processing of said acquired images, referred to as short-range processing (E3), configured to estimate the attitude of at least one of said space objects, referred to as target object, detected during the long-range processing, this step being implemented when said long-range step detects at least one space object located at a distance estimated to be less than a predetermined threshold distance; determining (E4) a possible rendezvous between at least said target object and the host satellite; preparing and transmitting instructions (E5) to said control unit of said moving means based on at least one rendezvous and/or risk of collision determined in the previous step.