Orbitziele

Orbitziele are the target orbital parameters and associated mission goals that define where and how a spacecraft should operate around a planet or other body. In mission planning, the Orbitziel guides the design of the trajectory, the choice of launcher or propulsion, and the in‑orbit operations plan. They translate payload requirements into specific constraints on the satellite’s path and duration.

Key components of Orbitziele include orbital altitude (or semi-major axis), inclination, eccentricity, orbital period, and the orientation of the orbital plane (for example RAAN and argument of perigee). They may also specify operational constraints such as coverage geometry, repeat‑cycle or revisit time, sun illumination conditions, thermal and power limits, and lifetime or decommissioning criteria. End‑of‑life and debris‑mitigation requirements are often incorporated as part of the orbit goals.

Derivation and use: Orbitziele arise from payload objectives, mission duration, ground‑segment capabilities, and cost and risk considerations. They are refined through trajectory optimization, simulations, and constraint‑based design. The resulting Orbitziel informs the mission architecture, including launch window selection, transfer maneuvers, insertion strategy, in‑orbit operations, and end‑of‑life planning.

Types: Orbitziele cover a range of geocentric orbits such as low Earth orbit (LEO), medium Earth orbit (MEO), geostationary orbit (GEO), and highly elliptical orbits, as well as specialized configurations like sun‑synchronous and polar orbits. For other planets, equivalent orbital parameters apply to the target orbital path.

Examples: A remote‑sensing mission might target a sun‑synchronous LEO at 600–700 km with near‑polar inclination; a communications satellite may aim for GEO at ~35,786 km; a science mission might require a specific repeat cycle and orbital plane.

See also: orbital mechanics, mission design, trajectory optimization.