Session
Technical Session XI: Propulsion
Abstract
Two small satellite concepts are presented for low cost Mars system exploration. Both concepts use solar electric propulsion (SEP) to move from a low velocity Earth escape orbit to captured Mars orbits, and so are able to make use of smaller launcher vehicles, while still providing significant payload accommodation, despite their small size. Both missions achieve their Mars system operational orbits in less than 20 months from launch. The Mars Global Atmosphere Survey (MGAS) mission design has a launch mass of 120kg. It uses a QinetiQ T5 ion engine, with around 24kg of Xe propellant, which provides sufficient ÄV for transfer to a low Mars orbit. Payload mass is around 12kg, dependent on Earth escape velocity, required final Mars orbit, and the time permitted for the transfer. The small launch mass allows a number of such spacecraft to be launched together on either Soyuz, DNEPR or Rockot-Breeze launchers, so providing a small Mars constellation. This fact was exploited by the proposed payload which uses the RF occultation method to measure temperature, density and pressure at the limb, aiding the characterisation of global circulation of the Martian atmosphere. The Mars Phobos and Deimos Survey (MPADS), at 320kg launch mass, is a minisatellite. It uses the larger QinetiQ T6 ion engine, with around 50kg of Xe propellant, with payload mass of 60kg. The spacecraft enters a large circular Mars orbit which is gradually reduced in size by electric propulsion in order to rendezvous with the Martian moons. The mission consists of either a single satellite visiting both moons, or two spacecraft, one at each moon, with the option of providing a lander package on one. These concepts have been studied under national funding with the aim of defining highly cost-effective options for the delivery of on-board instrumentation into Mars orbit, for remote sensing, or deployment of lander packages for Mars or Mars moon surface exploration. The mission design process reported considers all aspects of spacecraft bus, payload, trajectory and operations. The low thrust trajectory design and tradeoffs are described in some detail. Mass, power and link budgets are provided for both missions, along with a description of the payloads. Both missions are considered viable using existing or near term technology
Presentation Slides
Small Satellite Mars Missions using Electric Propulsion
Two small satellite concepts are presented for low cost Mars system exploration. Both concepts use solar electric propulsion (SEP) to move from a low velocity Earth escape orbit to captured Mars orbits, and so are able to make use of smaller launcher vehicles, while still providing significant payload accommodation, despite their small size. Both missions achieve their Mars system operational orbits in less than 20 months from launch. The Mars Global Atmosphere Survey (MGAS) mission design has a launch mass of 120kg. It uses a QinetiQ T5 ion engine, with around 24kg of Xe propellant, which provides sufficient ÄV for transfer to a low Mars orbit. Payload mass is around 12kg, dependent on Earth escape velocity, required final Mars orbit, and the time permitted for the transfer. The small launch mass allows a number of such spacecraft to be launched together on either Soyuz, DNEPR or Rockot-Breeze launchers, so providing a small Mars constellation. This fact was exploited by the proposed payload which uses the RF occultation method to measure temperature, density and pressure at the limb, aiding the characterisation of global circulation of the Martian atmosphere. The Mars Phobos and Deimos Survey (MPADS), at 320kg launch mass, is a minisatellite. It uses the larger QinetiQ T6 ion engine, with around 50kg of Xe propellant, with payload mass of 60kg. The spacecraft enters a large circular Mars orbit which is gradually reduced in size by electric propulsion in order to rendezvous with the Martian moons. The mission consists of either a single satellite visiting both moons, or two spacecraft, one at each moon, with the option of providing a lander package on one. These concepts have been studied under national funding with the aim of defining highly cost-effective options for the delivery of on-board instrumentation into Mars orbit, for remote sensing, or deployment of lander packages for Mars or Mars moon surface exploration. The mission design process reported considers all aspects of spacecraft bus, payload, trajectory and operations. The low thrust trajectory design and tradeoffs are described in some detail. Mass, power and link budgets are provided for both missions, along with a description of the payloads. Both missions are considered viable using existing or near term technology
