Abstract: A pumping method in a pumping system comprises: a main vacuum pump with a gas inlet port connected to a vacuum chamber and a gas outlet port leading into a conduit before coming out into the gas outlet of the pumping system, a non-return valve positioned in the conduit between the gas outlet port and the gas outlet, and an auxiliary vacuum pump connected in parallel to the non-return valve. The main vacuum pump is activated in order to pump the gases contained in the vacuum chamber through the gas outlet port, simultaneously the auxiliary vacuum pump is activated and continues to operate all the while that the main vacuum pump pumps the gases contained in the vacuum chamber and/or all the while that the main vacuum pump maintains a defined pressure in the vacuum chamber. Also included is a pumping system.

Abstract: The present invention relates to a redundant vacuum pumping system (300) and a pumping method using this system, comprising a primary roots pump (302), a first pumping sub-system (310) and a second pumping sub-system (320), wherein the first pumping sub-system (310) and the second pumping sub-system (320) are arranged to pump in parallel the gas evacuated by the primary roots pump (302), the first pumping sub-system (310) comprising a first secondary roots pump (311) and a first positive displacement pump (312) and a first valve (313) positioned between the gas discharge outlet (302b) of the primary roots pump (302) and the gas suction inlet (311a) of the first secondary roots pump (311), and the second pumping sub-system (320) comprising a second secondary roots pump (311) and a second positive displacement pump (312) and a second valve (323) positioned between the gas discharge outlet (302b) of the primary roots pump (302) and the gas suction inlet (321a) of the second secondary roots pump (321).

Abstract: The present invention relates to a pumping system to generate a vacuum (SP), comprising a main vacuum pump which is a claw pump (3) having a gas suction inlet (2) connected to a vacuum chamber (1) and a gas discharge outlet (4) leading into a gas evacuation conduit (5) in the direction of a gas exhaust outlet (8) outside the pumping system. The pumping system comprises a non-return valve (6) positioned between the gas discharge outlet (4) and the gas exhaust outlet (8), and an auxiliary vacuum pump (7) connected in parallel to the non-return valve. In a pumping method by means of this pumping system (SP), the main vacuum pump (3) is started up in order to pump the gases contained in the vacuum chamber (1) and to discharge these gases through its gas discharge outlet (4), simultaneously to which the auxiliary vacuum pump (7) is started up.

Abstract: A pumping method in a pumping system comprises: a main vacuum pump with a gas inlet port connected to a vacuum chamber and a gas outlet port leading into a conduit before coming out into the gas outlet of the pumping system, a non-return valve positioned in the conduit between the gas outlet port and the gas outlet, and an auxiliary vacuum pump connected in parallel to the non-return valve. The main vacuum pump is activated in order to pump the gases contained in the vacuum chamber through the gas outlet port, simultaneously the auxiliary vacuum pump is activated and continues to operate all the while that the main vacuum pump pumps the gases contained in the vacuum chamber and/or all the while that the main vacuum pump maintains a defined pressure in the vacuum chamber. Also included is a pumping system.

Abstract: The present invention relates to a pumping method in a pumping system (SP, SPP) comprising: a main lubricated rotary vane vacuum pump (3) with a gas inlet port (2) connected to a vacuum chamber (1) and a gas outlet port (4) leading into a conduit (5) before coming out into the gas outlet (8) of the pumping system (SP, SPP), a non-return valve (6) positioned in the conduit (5) between the gas outlet port (4) and the gas outlet (8), and an auxiliary lubricated rotary vane vacuum pump (7) connected in parallel to the non-return valve (6).

Abstract: The present invention relates to a pumping method in a pumping system (SP) comprising: a primary dry screw-type vacuum pump (3) with a gas entry orifice (2) connected to a vacuum chamber (1) and a gas exit orifice (4) leading into a conduit (5) before coming out into the gas outlet (8) of the pumping system (SP), a non-return valve (6) positioned in the conduit (5) between the gas exit orifice (4) and the gas outlet (8), and an ejector (7) connected in parallel to the non-return valve (6).

Abstract: The present invention relates to a pumping system to generate a vacuum (SP), comprising a main vacuum pump which is a dry screw pump (3) having a gas suction inlet (2) connected to a vacuum chamber (1) and a gas discharge outlet (4) leading into a gas evacuation conduit (5) in the direction of a gas exhaust outlet (8) outside the pumping system. The pumping system comprises a non-return valve (6) positioned between the gas discharge outlet (4) and the gas exhaust outlet (8), and an auxiliary vacuum pump (7) connected in parallel to the non-return valve. In a pumping method by means of this pumping system (SP), the main vacuum pump (3) is started up in order to pump the gases contained in the vacuum chamber (1) and to discharge these gases through its gas discharge outlet (4), simultaneously to which the auxiliary vacuum pump (7) is started up.

Abstract: The present invention relates to a pumping system to generate a vacuum (SP), comprising a main vacuum pump which is a claw pump (3) having a gas suction inlet (2) connected to a vacuum chamber (1) and a gas discharge outlet (4) leading into a gas evacuation conduit (5) in the direction of a gas exhaust outlet (8) outside the pumping system. The pumping system comprises a non-return valve (6) positioned between the gas discharge outlet (4) and the gas exhaust outlet (8), and an auxiliary vacuum pump (7) connected in parallel to the non-return valve. In a pumping method by means of this pumping system (SP), the main vacuum pump (3) is started up in order to pump the gases contained in the vacuum chamber (1) and to discharge these gases through its gas discharge outlet (4), simultaneously to which the auxiliary vacuum pump (7) is started up.

Abstract: The present invention relates to a pumping method in a pumping system (SP, SPP) comprising: a main lubricated rotary vane vacuum pump (3) with a gas inlet port (2) connected to a vacuum chamber (1) and a gas outlet port (4) leading into a conduit (5) before coming out into the gas outlet (8) of the pumping system (SP, SPP), a non-return valve (6) positioned in the conduit (5) between the gas outlet port (4) and the gas outlet (8), and an auxiliary lubricated rotary vane vacuum pump (7) connected in parallel to the non-return valve (6).

Abstract: The present invention relates to a pumping method in a pumping system (SP) comprising: a primary dry screw-type vacuum pump (3) with a gas entry orifice (2) connected to a vacuum chamber (1) and a gas exit orifice (4) leading into a conduit (5) before coming out into the gas outlet (8) of the pumping system (SP), a non-return valve (6) positioned in the conduit (5) between the gas exit orifice (4) and the gas outlet (8), and an ejector (7) connected in parallel to the non-return valve (6).

Abstract: The present invention relates to a pumping method in a pumping system (SP, SPP) comprising: a primary lubricated rotary vane vacuum pump (3) with a gas inlet port (2) connected to a vacuum chamber (1) and a gas outlet port (4) leading into a conduit (5) before coming out into the gas outlet (8) of the pumping system (SP, SPP), a non-return valve (6) positioned in the conduit (5) between the gas outlet port (4) and the gas outlet (8), and an ejector (7) connected in parallel to the non-return valve (6). According to this method, the primary lubricated rotary vane vacuum pump (3) is set into action in order to pump the gases contained in the vacuum chamber (1) through the gas outlet port (4).

Abstract: A method for the inertial navigation of a projectile equipped with a mediocre-quality inertial init that is fired from a carrier equipped with a precision inertial unit includes, before firing the projectile, the biases of the accelerometers and of the gyrometers of the inertial unit of the projectile are determined using the inertial unit of the carrier. During the inertial navigation of the projectile, the measurements of the accelermeters and of the gyrometers output by the inertial unit of the projectile are corrected by the biases determined before launching.

Abstract: According to the invention, before firing said projectile (M) from the carrier (L), the mean biases of the accelerometers and of the gyrometers of the inertial unit (IM) of said craft are determined using the inertial unit (IL) of said carrier (L) and, during the inertial navigation of said craft (M), the measurements of the accelerometers and of the gyrometers output by said inertial unit (IM) of said craft (M) are corrected by said mean biases determined before launching.

Abstract: An ionization cell for a mass spectrometer (2) includes: an ionization housing (10) having a first and a second electron input groove (11, 26) and one side (16) of which has an output groove (15) for passing ionized particles (14a, 14b, 14c) therethrough, a first working filament (13) placed opposite the first electron input groove (11) and intended to be supplied to produce an electron beam (12), and a second backup filament (22) placed opposite the second electron input groove (26) and intended to be supplied in the event the first working filament (13) fails so as to produce the electron beam, the input groove (26) being placed outside a front region (F) located opposite the first input groove (11). The invention also relates to a leak detector with a mass spectrometer, which includes such an above-described ionization cell.

Abstract: The invention relates to a guidance system comprising estimation means able to estimate, in the course of flight, the attitude and the aerodynamic speed of a projectile, as well as the variations in the speed of the wind, on the basis of guidance orders formulated by guidance means of the guidance system, of a reference trajectory and of measurements obtained by measurement means of the system, using a model of the dynamic behavior of the projectile and a model of the dynamics of the wind.

Abstract: An ionization cell for a mass spectrometer (2) includes: an ionization housing (10) having a first and a second electron input groove (11, 26) and one side (16) of which has an output groove (15) for passing ionized particles (14a, 14b, 14c) therethrough, a first working filament (13) placed opposite the first electron input groove (11) and intended to be supplied to produce an electron beam (12), and a second backup filament (22) placed opposite the second electron input groove (26) and intended to be supplied in the event the first working filament (13) fails so as to produce the electron beam, the input groove (26) being placed outside a front region (F) located opposite the first input groove (11). The invention also relates to a leak detector with a mass spectrometer, which includes such an above-described ionization cell.

Abstract: The invention relates to a guidance system comprising estimation means able to estimate, in the course of flight, the attitude and the aerodynamic speed of a projectile, as well as the variations in the speed of the wind, on the basis of guidance orders formulated by guidance means of the guidance system, of a reference trajectory and of measurements obtained by measurement means of the system, using a model of the dynamic behaviour of the projectile and a model of the dynamics of the wind.

Abstract: The present invention relates to a process and a device for guiding a flying craft onto a target, the device (1) comprising a detector (D) pointed at the target in such a way that a projection of the latter is situated on a field of measurement of the detector (D), a computation unit (UC) for determining guidance commands, and members (6) carrying out the guidance. According to the invention, the said device (1) furthermore comprises computation means (C3, C4) for determining commands for varying attitudes of the said flying craft making it possible to center the said projection with respect to a first direction of the measurement field, and the line of sight of the detector (D) is moveable and is controlled in such a way as to center the said projection with respect to a second direction of the measurement field, which is different from the said first direction.