Abstract: A thermoelectric generator comprising a plurality of semi-conductor elements of type n an type p alternatingly disposed and connected at the ends thereof to form a plurality of thermocouples on two opposite faces of the generator, said elements being thin polycrystalline semi-conductor ceramic layers deposited on a microporous support by means of serigraphy and fixed to said support by sintering.

Abstract: The present invention relates to a method and to a device intended for spontaneous combustion of a fuel comprising organic, vegetable or mineral materials, the device comprising a combustion chamber, at least one fuel injection means, at least one air inlet, hot fumes discharge means. Chamber (1) comprises a cylindrical shell (11), the discharge means comprise a pipe (6) having the same axis as the chamber and arranged inside said chamber, and fuel injection means (7) is arranged substantially tangential to said cylindrical shell so that the fuel follows a circular motion around said pipe in the chamber.

Abstract: Combustible compositions in the form of homogeneous water-in-oil and/or organic emulsions, deriving from heterogeneous fatty waste and containing solid particles in suspension are prepared by carrying out a dynamic homogenisation operation and an emulsification operation in the presence of an emulsifying agent and/or a base such as an alkali or alkaline-earth metal hydroxide. These combustible compositions can be used for combustion in a variety of furnace types.

Abstract: The present invention relates to a method and to a device intended for spontaneous combustion of a fuel comprising organic, vegetable or mineral materials, the device comprising a combustion chamber, at least one fuel injection means, at least one air inlet, hot fumes discharge means. Chamber (1) comprises a cylindrical shell (11), the discharge means comprise a pipe (6) having the same axis as the chamber and arranged inside said chamber, and fuel injection means (7) is arranged substantially tangential to said cylindrical shell so that the fuel follows a circular motion around said pipe in the chamber.

Abstract: The present invention relates to a combustion chamber of a gas turbine working on liquid fuel, comprising a tubular enclosure (2) having at least one pressurized air inlet, a liquid fuel injection means (6) positioned on or in proximity to the longitudinal axis XX′ of the tubular enclosure, an outlet to the turbine.

Abstract: A combustion chamber of a gas turbine working on liquid fuel includes a tubular enclosure (2) having at least one pressurized air inlet, a liquid fuel injection means (6) positioned on or in proximity to the longitudinal axis (XX′) of the tubular enclosure, and an outlet to the turbine. The fuel injection means (6) includes a series of orifices (62) arranged so as to create separate fuel jets, the jets being arranged in the direction of the generatrices of a cone with an angle ranging between 30° and 60° at the vertex thereof. The chamber includes at least two types of pressurized air inlets placed close to each other, the first one (7) taking in the air helically around the longitudinal axis of the combustion chamber, the second air inlet (8) being tangential to enclosure (2) so as to create, around the fuel jets, counterrotating flows intended to improve mixing of the air and of said fuel.

Abstract: An incinerator fumes processing plant has a first reactor (1) with fumes and injected absorbent flowing longitudinally through it. The flow from the first reactor enters a second reactor tangentially. The second reactor (2) is constructed so that the flow is driven by a rotating motion so as to separate progressively, and by centrifugal effect, the solid particles from the gases. The second reactor includes means (2a, 2b) for recirculating in the plant part of the solid particles separated in the second reactor. The dedusted fumes are then discharged from the plant.

Abstract: The invention describes a nozzle and a burner for oil-well tests comprising a plurality of nozzles. The nozzle comprises means for injecting an air-oil mixture to be burnt in the direction of a combustion zone, the flow of air at the outlet of the nozzle allowing the air in the air-oil mixture to create an air induction effect, that is to say entrainment of air, which is sufficient along the whole length of the jet to ensure the combustion.

Abstract: 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.

Abstract: 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.

Abstract: A method of controlling the attitude of a satellite according to which the direction of a predetermined celestial object is defined in a frame of reference related to the satellite, the instantaneous angular velocity vector of the satellite is detected and, by means of an actuating assembly, torques are applied to the satellite which are defined by a control law so as to rotate the satellite about the direction while orienting an aiming axis related to the satellite in the same direction, involves defining the direction of the predetermined celestial object in a frame of reference related to the satellite by a first quantity representing a first angle measured between an axis of sight and the projection of the direction onto a first reference plane containing the axis of sight and by a second quantity representing a second angle defined by the axis of sight and the projection of the direction onto a second reference plane containing the axis of sight, the second angle being calculated from the first angle and

Abstract: 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.

Abstract: To reacquire the attitude of a satellite wholly or partially stabilized on three axes a test is executed to determine if a terrestrial sensor is sensing the Earth (test 1) and if a star sensor is sensing a star whose magnitude is at least approximately equal to that of a given reference star (test 2).* Phase a. If the results of tests 1 and 2 are positive, the Earth and the star are captured and the consistency of roll information supplied by the Earth and star sensors is checked: if the information is not consistent phase (b) is carried out.* Phase b: If the results of test 1 only is positive, the Earth is captured and the satellite is caused to rotate in yaw until the result of test 2 is positive. The reference star is captured and the phase (a) consistency test is carried out.* Phases c and d: If the result of test 1 is negative, the pitch speed is reversed for at most a given time. If the result of test 1 becomes positive, test 2 is carried out.

Abstract: Roll and yaw attitude control method for a satellite stabilized about its roll, yaw and pitch axes embodying a momentum wheel system generating a continuous angular momentum substantially parallel to the pitch axis and having a variable component at least approximately parallel to the roll-yaw plane and a continuously acting actuator system in which the roll and/or yaw attitude of the satellite is sensed. Control signals are applied to the momentum wheel system that are produced by a fast control loop using a known fast control law and second control signals are applied to the continuously acting actuator system that are produced by a slow control loop using a known slow control law. The continuously acting actuator system is loaded in fixed direction of the satellite parallel to the variable component if the latter has a fixed direction.

Abstract: A parallel flow liquid fuel burner is disclosed which has a device for injecting fuel in a central flame stabilizer; the stabilizer comprises a blade-containing rose situated around a central hub itself situated around the injection device and the injection device comprises several fuel injection orifices adapted to provide separate elementary flames.

Abstract: A method to control the attitude in roll (X) and in yaw (Z) of a satellite including two solar generator panels adapted to be oriented independently of each other about a pitch axis. In a preliminary stage: two geometrical axes x and z are selected in the plane of the roll and yaw axes, there being associated with the z axis a tolerable command torque error much lower than for the x axis, and a correlation law is established between satellite panel depointing angles .gamma..sub.N and .gamma..sub.S and possible command torques due to solar radiation pressure.

Abstract: An attitude control device for a satellite stabilized on three axes including a pitch axis comprises two solar generator wings extending in opposite directions away from a satellite body on respective longitudinal axes at least approximately parallel to the pitch axis. Two drive motors drive these wings independently of each other in rotation about rotation axes at least approximately parallel to the pitch axis to keep the wings facing the Sun with a depointing angle at most equal to a predetermined maximum depointing value. Sensors measure attitude angles and a computation system commands the drive motors according to the attitude angles. On each wing an additional surface in the form at least one vane extends longitudinally beyond the end of the wing parallel to its longitudinal axis. These additional surfaces have substantially the same surface area and are inclined about this axis relative to the wings in opposite directions by at least approximately the same angle which is less than the 90.degree.