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| Orbit Attitude and Maneuvering System | |
|---|---|
| Name | Orbit Attitude and Maneuvering System |
| Caption | Schematic of typical satellite attitude and maneuvering components |
Orbit Attitude and Maneuvering System
An Orbit Attitude and Maneuvering System provides spacecraft with the capability to control orientation and change orbital parameters. It enables mission objectives for platforms such as Hubble Space Telescope, International Space Station, Voyager 1, Kepler space telescope, and Galileo (spacecraft), supporting operations performed by organizations like NASA, ESA, Roscosmos, JAXA, and ISRO. The system integrates hardware and software drawn from programs including Apollo program, Space Shuttle, Cassini–Huygens, Mars Reconnaissance Orbiter, and Landsat to meet requirements set by agencies and contractors such as Lockheed Martin, Northrop Grumman, Airbus Defence and Space, Boeing, and Ball Aerospace.
An Orbit Attitude and Maneuvering System serves spacecraft mission roles spanning stationkeeping for Geostationary orbit satellites, deorbiting for Skylab-class platforms, rendezvous and docking for vehicles like Soyuz (spacecraft), SpaceX Dragon, and Orbital Sciences Cygnus, and precision pointing for observatories such as Chandra X-ray Observatory and James Webb Space Telescope. Missions driven by programs like Mercury program, Gemini program, Viking program, and Mariner program have refined designs to satisfy requirements from stakeholders including European Southern Observatory and US Department of Defense. Design trades reflect constraints derived from standards such as those used by National Aeronautics and Space Administration mission design offices and commercial practices at firms like Blue Origin.
Typical architectures include discrete subsystems: structural mounts derived from heritage of Skylab and International Space Station United States Orbital Segment, fuel tanks using materials studied by CERN collaborators, and avionics akin to flight computers used on Apollo Guidance Computer and Space Shuttle flight deck. Core components commonly include reaction wheels (employed on Kepler space telescope and Gaia (spacecraft)), control moment gyroscopes (used on International Space Station), thruster clusters (seen on Voyager 2 and Voyager 1), star trackers (as in Hubble Space Telescope and James Webb Space Telescope), sun sensors (used on Voyager program), inertial measurement units (from technologies applied in Apollo program), and propellant management systems used by vehicles such as Dragon 2 and Shenzhou. Integration frequently involves suppliers with histories tied to Honeywell International Inc. and Thales Group.
Control approaches span momentum-biasing heritage from Mercury Seven-era vehicles to three-axis stabilized systems implemented on Hubble Space Telescope and Galileo (spacecraft). Methods include passive stabilization techniques first tested by Sputnik 1 and Explorer 1, active control via reaction wheels employed on Kepler space telescope and Dawn (spacecraft), control moment gyroscopes demonstrated on International Space Station, magnetic torquers used by cubesats inspired by experiments from MIT and Caltech, and thruster-based slewing like maneuvers executed by Apollo lunar modules. Algorithms trace lineage to guidance research at MIT Instrumentation Laboratory and work by pioneers associated with Wernher von Braun and Sverdrup & Parcel-era efforts.
Orbital maneuvers include impulsive burns modeled on trajectories from Apollo 11 and Apollo 13, low-thrust spiral transfers akin to SMART-1 and Dawn (spacecraft), Hohmann transfer concepts formalized in academic work at Princeton University and Caltech, bi-elliptic transfer strategies analyzed in studies by researchers at Stanford University, and aerobraking techniques applied on missions such as Mars Reconnaissance Orbiter and Venus Express. Rendezvous and proximity operations leverage protocols from Gemini program, Soyuz (spacecraft), and Shuttle–Mir program, with mission planning influenced by flight dynamics groups at Jet Propulsion Laboratory and European Space Operations Centre.
Propulsion choices encompass monopropellant thrusters using hydrazine as in Voyager program and Landsat, bipropellant engines used on Orbiter-class craft, electric propulsion exemplified by Hayabusa and DS1 (spacecraft), and cold-gas systems employed on smallsat platforms inspired by CubeSat developments at Cal Poly. Reaction control subsystem (RCS) designs reflect lessons from Space Shuttle OMS/RCS, with valves and injectors manufactured by vendors with ties to Aerojet Rocketdyne and Rolls-Royce plc. Propellant management includes bladder tanks and pressure regulation techniques derived from work at NASA Glenn Research Center and ESA ESTEC.
GN&C integration merges sensors like star trackers used on James Webb Space Telescope, inertial measurement units developed from Apollo Guidance Computer projects, and navigation aids such as GPS receivers adapted for space by teams at Air Force Research Laboratory. Flight software architectures build on frameworks from NASA Deep Space Network operations and onboard autonomy experiments from DARPA and ESA initiatives. Autonomy and fault management draw on methods tested during Mars Pathfinder operations and demonstration projects by Blue Origin and SpaceX.
Performance metrics derive from mission requirements seen in Hubble Space Telescope servicing missions, failure analyses such as post-flight reviews after Challenger disaster and Columbia disaster, and reliability engineering traditions established at Bell Labs and General Electric. Redundancy strategies often follow multicompartmental architectures used on International Space Station and concentric redundancy approaches pursued by Lockheed Martin and Boeing. Qualification and verification processes align with standards promulgated by NASA and industrial contractors, and operational resilience has been informed by lessons from Apollo 13 and contingency responses developed at Johnson Space Center.
Category:Spacecraft subsystems