HORUS COMET

HORUS COMET (Calculation Of Maneuvers & Evaluation Tool) is a module of the HORUS System designed for the detection, characterization, and analysis of orbital maneuvers, as well as to support the definition and evaluation of collision avoidance maneuvers for collision risk mitigation. The solution enables the identification of discrepancies between predicted orbits and actual observations, detection of potential orbital maneuvers, characterization of their physical and operational parameters, assessment of their impact on the orbit, and support for mitigation action planning.

The system is capable of analyzing orbital observations, state vectors, and propagated orbits to detect maneuvers, estimate maneuver magnitude (ΔV), identify maneuver type, determine its direction within the orbital reference frame, and estimate its time of occurrence or duration. In addition, it provides mechanisms for generating, evaluating, comparing, and simulating collision avoidance maneuvers, taking into account orbital parameters, conjunction characteristics, and satellite operational constraints.

Operational Concept

The operational process begins with the analysis of orbital observations, state vectors, and propagated orbits. By comparing measurements with orbital models, the system identifies discrepancies and automatically detects potential orbital maneuvers.

Once a maneuver is detected, its parameters are estimated, including magnitude (ΔV), maneuver type, direction within the orbital reference frame, time of occurrence, and duration. The system then assesses the impact of the maneuver on the satellite's orbital parameters, enabling comparison between the orbit before and after the event.

To support collision risk mitigation, the system uses conjunction information, orbital parameters of the objects involved, time to TCA, and operational constraints to generate collision avoidance maneuver alternatives. The proposed solutions can be simulated, compared, and evaluated in terms of their orbital impacts, residual risks, and operational effectiveness, supporting operator decision-making.

Throughout the process, the operator has access to visualization, analysis, and scenario comparison tools, including graphical representations of maneuvers, orbital trajectories, and conjunction events.

Integration with Surveillance and Tracking Systems

HORUS COMET uses orbital observations, state vectors, and propagated orbits as input data for the detection and characterization of orbital maneuvers.

The system also uses conjunction information and orbital data from the objects involved to plan collision avoidance maneuvers. Additionally, it provides for integration with conjunction systems and orbital propagators to support maneuver analysis, simulation, and evaluation processes.

Target Market

Defense and security organizations; Space agencies; Space operations centers; Satellite operators; Organizations responsible for monitoring conjunctions and collision risks; Institutions involved in space operations and space safety.

Key Capabilities

Automatic detection of orbital maneuvers; Characterization of orbital maneuvers; Estimation of maneuver magnitude (ΔV); Classification of impulsive and continuous maneuvers; Determination of maneuver direction within the orbital reference frame; Estimation of maneuver time of occurrence and duration; Orbital impact analysis; Assessment of changes in orbital parameters; Development of maneuver history and timeline; Collision avoidance maneuver planning; Generation of maneuver alternatives; Specific strategies for GEO orbits; Specific strategies for LEO orbits; Simulation of post-maneuver impacts; Assessment of residual risks; Comparison of maneuver alternatives; Decision support; Graphical orbital visualization; Integration with conjunction systems and orbital propagators.

Key Functions

Orbital Maneuver Detection

Identification of potential orbital maneuvers through the analysis of observations, state vectors, and propagated orbits, using residual calculations and the analysis of discrepancies between measurements and orbital models.

Maneuver Characterization

Estimation of the physical and operational parameters of detected maneuvers, including magnitude (ΔV), maneuver type, direction within the orbital reference frame, time of occurrence, and duration.

Orbital Impact Analysis

Assessment of the changes produced by the maneuver in the satellite's orbital parameters, including inclination, orbital period, perigee altitude, apogee altitude, and semi-major axis.

Maneuver Timeline

Development of an event history and identification of maneuver sequences, enabling temporal analysis of events and detection of operational patterns.

Collision Avoidance Maneuver Planning

Generation of maneuver alternatives for collision risk mitigation, taking into account conjunction information, orbital parameters, time to TCA, and available operational constraints.

GEO Orbit Strategies

Definition of collision avoidance maneuvers based on criteria such as minimizing fuel consumption (ΔV), maintaining the longitudinal slot, compatibility with station-keeping operations, and increasing the minimum distance between objects.

LEO Orbit Strategies

Definition of collision avoidance maneuvers based on minimizing the probability of collision (Pc), maximizing separation at TCA, prioritizing prograde maneuvers, and optimizing maneuver execution timing.

Impact Simulation

Simulation of the effects of proposed maneuvers through post-maneuver orbital propagation, residual risk assessment, analysis of future conjunctions, and identification of new risk events.

Alternative Comparison and Decision Support

Comparison of different maneuver alternatives based on parameters such as ΔV, residual risk, orbital impact, and solution effectiveness, enabling classification, ranking, and selection of the most appropriate alternative.

Operational Visualization

Graphical representation of maneuvers, orbital trajectories, ΔV vectors, conjunction events, and simulated scenarios, supporting monitoring, analysis, and decision-making activities.