Abstract: Nozzle of a spacecraft engine, comprising a nozzle body extending along a main direction, from a proximal end secured to the engine of the spacecraft, and a free distal end, said nozzle body having a plurality of stiffeners extending from an outer surface of the nozzle body, radially with respect to the main direction, said nozzle comprising a thermal insulation system, comprising at least one strip of insulating material disposed so as to surround the outer surface of the nozzle body over at least part of the height of said nozzle body, said thermal insulation system comprising a plurality of holding elements, each holding element being positioned so as to surround said strips of insulating material, and being disposed between two stiffeners of the nozzle body.

Abstract: A cardan joint spider comprising a body having four right-angled brackets, each bracket presenting two mutually perpendicular arms, the arm of one bracket being assembled to the arm of an adjacent bracket so as to form a cross-shaped spider having four branches.

Abstract: Nozzle of a spacecraft engine, comprising a nozzle body extending along a main direction, from a proximal end secured to the engine of the spacecraft, and a free distal end, said nozzle body having a plurality of stiffeners extending from an outer surface of the nozzle body, radially with respect to the main direction, said nozzle comprising a thermal insulation system, comprising at least one strip of insulating material disposed so as to surround the outer surface of the nozzle body over at least part of the height of said nozzle body-, said thermal insulation system comprising a plurality of holding elements, each holding element being positioned so as to surround said strips of insulating material, and being disposed between two stiffeners of the nozzle body.

Abstract: A rocket engine benefiting from better behavior during its starting stage, the rocket engine (1) including a diverging section (13) and a lashing system (40) configured to hold the diverging section (13) while starting the rocket engine (1), the lashing system (40) comprising: a plurality of radial cables (42) connected at respective first ends to a plurality of points of the diverging section (13), and a peripheral cable (41) connected to the second ends of the radial cables (42) and configured to co-operate with attachment points (43) of a launch platform (3).

Abstract: A cardan joint spider comprising a body having four right-angled brackets, each bracket presenting two mutually perpendicular arms, the arm of one bracket being assembled to the arm of an adjacent bracket so as to form a cross-shaped spider having four branches.

Abstract: A rocket engine benefiting from better behavior during its starting stage, the rocket engine (1) including a diverging section (13) and a lashing system (40) configured to hold the diverging section (13) while starting the rocket engine (1), the lashing system (40) comprising: a plurality of radial cables (42) connected at respective first ends to a plurality of points of the diverging section (13), and a peripheral cable (41) connected to the second ends of the radial cables (42) and configured to co-operate with attachment points (43) of a launch platform (3).

Abstract: The present disclosure relates to a rocket engine obtaining safer and better controlled ground-based ignition, the rocket engine comprising an axisymmetric propulsion chamber (12), including a throat (12c) at which the diameter of the propulsion chamber (12) is a minimum, an injection head (11) configured to inject at least one liquid propellant into the propulsion chamber (12), and a destructible tubular guide (40), applied coaxially in the propulsion chamber (12) so as to channel said propellant downstream of the throat (12c) of the propulsion chamber (12).

Abstract: A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

Abstract: An annular metal static seal (10) comprising a first annular bearing plate (12A), a facing second annular bearing plate (12B), and an annular central portion (14) perpendicularly connecting together the first and second annular bearing plates and secured in sealed manner to each of them via a respective annular weld, the assembly thus presenting a section in the shape of the letter H on its side.

Abstract: An annular metal static seal (10) comprising a first annular bearing plate (12A), a facing second annular bearing plate (12B), and an annular central portion (14) perpendicularly connecting together the first and second annular bearing plates and secured in sealed manner to each of them via a respective annular weld, the assembly thus presenting a section in the shape of the letter H on its side.

Abstract: A system for cooling and holding a testpiece in an effective manner while the testpiece is subjected locally to high heat flux. The testpiece includes an inside face extended by parallel strips that leave between them channels for passing a cooling fluid, and parallel fins of an intermediate part are inserted between the strips.

Abstract: A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment.

Abstract: A system for cooling and holding a testpiece in an effective manner while the testpiece is subjected locally to high heat flux. The testpiece includes an inside face extended by parallel strips that leave between them channels for passing a cooling fluid, and parallel fins of an intermediate part are inserted between the strips.

Abstract: The invention provides an electronic wrench which includes means for measuring the instantaneous applied torque and means for measuring the instantaneous angle of rotation during tightening. The physical parameters of the screw connection for tightening and a setpoint value for the tightening are initially entered into the wrench via a keypad. During the tightening operation, the processor means calculate the instantaneous traction force on the screw fastener as a function of the measured instantaneous values of torque and angle and as a function of the recorded characteristics of the screw fastener.

Abstract: The invention provides an electronic wrench which includes means for measuring the instantaneous applied torque and means for measuring the instantaneous angle of rotation during tightening. The physical parameters of the screw connection for tightening and a setpoint value for the tightening are initially entered into the wrench via a keypad. During the tightening operation, the processor means calculate the instantaneous traction force on the screw fastener as a function of the measured instantaneous values of torque and angle and as a function of the recorded characteristics of the screw fastener.

Abstract: The metal static gasket forms an annular body about an axis ZZ′. The profile of the gasket in axial half-section presents an elongated S-shape and comprises a lateral first portion defining the inner peripheral surface of the gasket, a lateral second portion defining the outer peripheral surface of the gasket, said lateral first and second portions being offset from each other along the direction of the axis of the gasket. The gasket also presents a curved third portion of undulating shape having a substantially rectilinear first contact region at one of its ends, and a curved fourth portion of undulating shape having a substantially rectilinear second contact region at one of its end extending perpendicularly to the axis of the gasket in such a manner that the gasket provides sealing between two flanges solely by means of the axial pressure exerted by the flanges.