Astrium Sas

Other

Robert Andre Laine

Christophe Balemboy

Christophe Chavagnac

Xavier Sembely

Hugues Laporte-Weywada

Olivier Poulain

Philippe Matharan

Jérôme Bertrand

Jean-Paul Collette

Hugues Favin-Leveque

Mark Kinnersley

Marie-Claire Perkinson

Martin Ripple

Daniel Pelletier De Chambure

Claude Jamar

Jean-Philippe Tock

Yvan Stockman

A landing system of a body and a space probe provided with such a system for landing on a bearing ground. The landing system includes landing legs (), each with a footpad () at the end thereof, intended for braking the landing impact of the body when coming into contact with the ground and for supporting the body on the ground after landing. The footpads () are not coplanar.

Landing system for a body and space probe provided with such a system

A transmitting beacon () having at least two transmitting current loops () that are mutually orthogonal and capable of transmitting electromagnetic waves (), as well as means () for supplying power to the transmitting current loops () in series is disclosed.

System for orienting and positioning an electromagnetic receiver

An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favor lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.

Aerodynamic and spatial composite flight aircraft, and related piloting method

The system comprises terminals that are mounted onto a predetermined number of feeder vessels, comprises means for detecting identification signals sent by surrounding ships, and moreover comprises means for recording identification information that include the detected identification signals and the current position of the feeder vessel. Said system also comprises a system for transmitting data via satellites, said data transmitting system making it possible to transmit data between the terminals and a monitoring center, said monitoring center including a means for generating requests intended for the terminals in order to ask said terminals to provide the recorded identification information. Said monitoring center also includes a means for analyzing the received identification information.

System for tracking ships at sea

A system includes a mother probe forming a carrier space vehicle () and a plurality of daughter probes (2, 2, 2) aligned in a longitudinal axis (A) of the mother probe, in which the attachment of the daughter probes to the mother probe is carried out by a plurality of probe-supporting annular segments (5, 5, 5) each provided with an annular collar (3, 3, 3) for attaching a daughter probe.

System comprising a spatial mother probe forming a spatial carrier vehicle and a plurality of spatial daughter probes

A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle.

Landing device for a space probe, and landing method for a probe provided with such a device

Disclosed are a method and device for supplying a combustion chamber of a space propulsion engine with cryogenic liquid fuel and oxidizer propellants. The propellants are mixed at constant pressure to produce a propellant mixture, with the propellants being mixed at a location upstream of an orifice of a propellant injector. The propellant mixture is fed to an enclosure of the propellant injector, and from the propellant injector enclosure, the propellant mixture is injected into the combustion chamber. The flow rate of the propellant mixture from the propellant injector enclosure into the combustion chamber is varied by adjustment of the propellant injector, with the injection of the propellant mixture from the propellant injector enclosure into the combustion chamber being at constant pressure.

Method and device for supplying a space propulsion engine with liquid cryogenic propellants

Disclosed is a system for positioning a terrestrial user. The system includes navigation satellites placed in medium altitude orbits, management satellites placed in high orbits, able to manage the navigation satellites and communicate with the Earth. The management satellites can include a set of at least three management satellites each placed in a high orbit, having a plane that is inclined with respect to the plane of the terrestrial equator and cuts the equator along a diametral straight intersection line with respect to the Earth. Two external diametral straight intersection lines can form an angle of longitude of at least 90 degrees.

System for positioning a terrestrial user

A satellite terrestrial positioning system is disclosed in which navigation satellites verify, in an autonomous manner, essential information that is transmitted to users using unidirectional links received from reference beacons.

Growing community of inventors

Paris, France

Robert Andre Laine