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Noordwijk - Binnen, Netherlands

The European Space Agency is an intergovernmental organisation dedicated to the exploration of space, with 21 member states. Established in 1975 and headquartered in Paris, France, ESA has a staff of more than 2,000 with an annual budget of about €4.28 billion / US$5.51 billion .ESA's space flight programme includes human spaceflight, mainly through the participation in the International Space Station programme, the launch and operations of unmanned exploration missions to other planets and the Moon, Earth observation, science, telecommunication as well as maintaining a major spaceport, the Guiana Space Centre at Kourou, French Guiana, and designing launch vehicles. The main European launch vehicle Ariane 5 is operated through Arianespace with ESA sharing in the costs of launching and further developing this launch vehicle.ESA science missions are based at ESTEC in Noordwijk, Netherlands, Earth Observation missions at ESRIN in Frascati, Italy, ESA Mission Control is in Darmstadt, Germany, the European Astronaut Centre that trains astronauts for future missions is situated in Cologne, Germany, and the European Space Astronomy Centre is located in Villanueva de la Cañada, Madrid, Spain. Wikipedia.


Patent
European Space Agency | Date: 2012-12-21

The present invention relates to a method of manufacturing a component


Embodiments of an Earth observation satellite comprising a satellite main body having an elongated shape extending in the direction of a roll axis R of the satellite from a first base face of the satellite main body to a second base face of the satellite main body, the satellite main body having a plurality of lateral faces extending from the first base face to the second base face; a solar array; and propulsion means for compensating air-drag being arranged on the base face of the satellite main body. A first solar panel of the solar array is mounted on a first lateral face of the satellite main body, a second lateral face of the satellite main body is configured to radiate heat away from the satellite main body, and a third lateral face of the satellite main body has observation means for Earth observations.


A method for generating a digital signal of tunable frequency may include generating a periodic first analog signal, determining a sign of a first difference between a value of the first analog signal and a first control value to determine sign flips, wherein the first control value is a variable value, and generating the digital signal of tunable frequency on the basis of the determined sign of the first difference, wherein the digital signal of tunable frequency is generated such that a subset of switches of the signal level are coincident with a respective sign flip of the determined sign of the first difference.


Patent
European Space Agency | Date: 2012-03-15

A mechanical support ring structure for supporting a deployable space reflector antenna. The mechanical support ring structure is convertible from a folded state into a deployed state and includes a ring-shaped pantograph having a plurality of circumferentially arranged pantograph sections which are deployable for converting the mechanical support ring structure from the folded state into the deployed state, and a plurality of circumferentially arranged support rods, each pantograph section being arranged between a respective pair of support rods, wherein each pantograph section includes one or more pairs of pantograph rods which intersect crosswise with each other at a respective crossing position.


Patent
European Space Agency | Date: 2012-10-01

A multi-faceted deployable antenna frame including a six-bar linkage structure in a lateral facet of the antenna frame, the six-bar linkage structure being convertible from a folded state into a deployed state and having two first bars and four second bars, each bar being coupled to two others by a hinge to form a closed loop, where in the deployed state, the six-bar linkage structure has a quadrilateral shape. The antenna frame also includes a deployment means for deploying the antenna frame by moving the six-bar linkage structures from the folded state into the deployed state, the deployment means including: a flexible, elongated member of a substantially inextensible material; a first guiding means provided at an end portion of one of the first bars and coupled to the elongated member; a storage means provided at the first bar that includes the first guiding means for storing a part of the elongated member; a driving means that is coupled to the elongated member to pull the elongated member to the storing means when deploying the antenna frame; and a second guiding means between two adjacent second bars, the elongated member being coupled to the second guiding means. A first end of the elongated member is attached to the storing means and a second end of the elongated member is coupled to another first bar, and wherein the elongated member is extending between said first end and said second end along a plurality of second bars.

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