Aerospatiale Societe Nationale Industrielle

Societe Nationale Industrielle Et Aerospatiale

Michel Perdu

Patrick Flament

Pierre Brunet

Jean Portier

A satellite embodying at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an on board computer having connected thereto an attitude sensing system, an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. The satellite further embodies a device for controlling the tilt of the surface in parallel with a plurality of planes containing the predetermined direction; and, therefore, particularly in parallel with the plane of a solar panel forming the surface. The tilt control device is controlled by the on-board computer. The tilting can generate a moment of pitch or relocate the center of gravity onto the axis of the orbit control system.

Method for controlling the pitch attitude of a satellite by means of

A satellite embodying at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an onboard computer having connected thereto an attitude sensing system, an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. The satellite further embodies a device for controlling the tilt of the surface in parallel with a plurality of planes containing the predetermined direction; and, therefore, particularly in parallel with the plane of a solar panel forming the surface. The tilt control device is controlled by the onboard computer. The tilting can generate a moment of pitch or relocate the center of gravity onto the axis of the orbit control system.

Apparatus controlling the pitch attitude of a satellite by means of

A liquid propellant supply device for satellites comprises an inlet pipe connected to a source of pressurizing gas, an outlet pipe connected to a propellant distribution manifold and a main storage tank connected at an inlet orifice to the inlet pipe and at an outlet orifice to the outlet pipe. The main storage tank contains a capillary action propellant retention device between the interior of the main storage tank and the outlet pipe. The device further comprises, on the outlet pipe, starting from the main storage tank, a gas test device adapted to detect the presence in the outlet pipe of a significant quantity of gas followed by an auxiliary storage tank substantially smaller than the main storage tank and including a second capillary action propellant retention device separating the interior of the auxiliary storage tank and the distribution manifold.

Liquid propellant supply device for spacecraft adapted to predict the

To monitor continuously the propellant consumption of a space vehicle equipped with a plurality of propulsion units operated by activator means according to activation instructions received by the activator means, the number N of activation instructions applied to each propulsion unit from a reference time and their cumulative duration S are memorized. The mass M of propellant consumed since the reference time by each propulsion unit is computed from the equation:

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Frejus, France

Michel Perdu