Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to enable ignition of squibs of a squib array based on the satellite exiting the launch vehicle, and a squib controller to control the ignition of the squibs based on a firing sequence of the squibs, where the squib controller is to vary the firing sequence to autonomously deploy the solar array.

A magneto-inductive DC magnetometer is provided that is operable to output fluxgate quality measurements in a low mass, volume, power and cost package. The magnetometer enables constellation-class missions not only due to its low-resource requirements, but also due to its potential for commercial integrated circuit fabrication. In addition, the magnetometer will be part of a ground-based Space Weather Underground Citizen Science instrument package that enables dense arrays of space weather-relevant observations at mid-latitudes. The magneto-inductive operating principle is based on a simple resistance-inductor (RL) circuit and involves measurement of the time it takes to charge and discharge the inductor between an upper and lower threshold by means of a Schmitt trigger oscillator. This time is proportional to the inductance that in turn is proportional to the field strength.

A magneto-inductive DC magnetometer is provided that is operable to output fluxgate quality measurements in a low mass, volume, power and cost package. The magnetometer enables constellation-class missions not only due to its low-resource requirements, but also due to its potential for commercial integrated circuit fabrication. In addition, the magnetometer will be part of a ground-based Space Weather Underground Citizen Science instrument package that enables dense arrays of space weather-relevant observations at mid-latitudes. The magneto-inductive operating principle is based on a simple resistance-inductor (RL) circuit and involves measurement of the time it takes to charge and discharge the inductor between an upper and lower threshold by means of a Schmitt trigger oscillator. This time is proportional to the inductance that in turn is proportional to the field strength.

The present invention provides an innovative apparatus and method for onboard spacecraft location determination and navigation by employing observations of extrasolar planetary star systems. In one apparatus embodiment a gas absorption cell is placed between a sensor and the light from a reference star system with at least one exoplanet, such that the sensor can detect the spectrum through the gas absorption cell. Radial velocities can be calculated via Doppler Spectroscopy techniques and incorporated into a spacecraft navigation solution. Additional embodiments incorporate other spacecraft sensor or system data to derive a filtered navigation solution. The present invention can enable and enhance significant mission capabilities for future manned and unmanned space vehicles and missions.

The present invention provides an innovative apparatus and method for onboard spacecraft location determination and navigation by employing observations of extrasolar planetary star systems. In one apparatus embodiment a gas absorption cell is placed between a sensor and the light from a reference star system with at least one exoplanet, such that the sensor can detect the spectrum through the gas absorption cell. Radial velocities can be calculated via Doppler Spectroscopy techniques and incorporated into a spacecraft navigation solution. Additional embodiments incorporate other spacecraft sensor or system data to derive a filtered navigation solution. The present invention can enable and enhance significant mission capabilities for future manned and unmanned space vehicles and missions.

The invention discloses a preferable short arc initial orbit determining method based on Gauss solution cluster, and belongs to the astrodynamics field, including: grouping the observation data, using Gauss method to obtain the target state vector at the corresponding time point for each group of data, forming a solution set of preliminary estimation; dividing the solution set of preliminary estimation into a position component vector solution set and a velocity component vector solution set for clustering to obtain a position component vector solution cluster and a velocity component vector solution cluster; based on the position component vector solution cluster and the velocity component vector solution cluster, generating a two-dimensional trajectory solution set; evaluating each of the two-dimensional trajectories by using a trajectory optimal method, calculating the number of root of orbits corresponding to the optimal two-dimensional trajectory, thereby completing determination of initial orbit.

The invention discloses a preferable short arc initial orbit determining method based on Gauss solution cluster, and belongs to the astrodynamics field, including: grouping the observation data, using Gauss method to obtain the target state vector at the corresponding time point for each group of data, forming a solution set of preliminary estimation; dividing the solution set of preliminary estimation into a position component vector solution set and a velocity component vector solution set for clustering to obtain a position component vector solution cluster and a velocity component vector solution cluster; based on the position component vector solution cluster and the velocity component vector solution cluster, generating a two-dimensional trajectory solution set; evaluating each of the two-dimensional trajectories by using a trajectory optimal method, calculating the number of root of orbits corresponding to the optimal two-dimensional trajectory, thereby completing determination of initial orbit.

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

A device for positioning a functional trihedron of a star tracker in a reference trihedron tied to a structure on which the star tracker is mounted comprises: a fixing interface to connect the device to the star tracker, a set of geometric markers configured to, by means of an optical measurement instrument tied to the structure, position a marker tied to the device in the reference marker tied to the structure, an optical simulator comprising a set of optical markers to be measured by the star tracker, making it possible to position the functional trihedron of the star tracker in the trihedron tied to the device, the measurements of position of the functional trihedron in the trihedron tied to the device, and of position of the trihedron tied to the device in the reference trihedron, making it possible to position by calculation the functional trihedron in the reference trihedron.

A device for positioning a functional trihedron of a star tracker in a reference trihedron tied to a structure on which the star tracker is mounted comprises: a fixing interface to connect the device to the star tracker, a set of geometric markers configured to, by means of an optical measurement instrument tied to the structure, position a marker tied to the device in the reference marker tied to the structure, an optical simulator comprising a set of optical markers to be measured by the star tracker, making it possible to position the functional trihedron of the star tracker in the trihedron tied to the device, the measurements of position of the functional trihedron in the trihedron tied to the device, and of position of the trihedron tied to the device in the reference trihedron, making it possible to position by calculation the functional trihedron in the reference trihedron.