Abstract: A spacecraft includes: a body a surface of revolution connected with the body, and a heat engine positioned at the center of the surface of revolution. The surface of revolution has a substantially open hollow torus shape with a transverse cross-section of a circle and two diametrically opposite portions each having a curvature extending from the circle. A first portion of the diametrically opposite portions has an opening and forms a solar concentrator for concentrating solar radiation in the direction of the heat engine. The first portion forms a primary solar radiation reflector. A second portion of the diametrically opposite portions is coaxial with the first portion and forms a secondary solar radiation reflector. The opening is configured so that the solar radiation passes in the direction of the center of the surface of revolution after reflection at the primary and secondary reflectors.

Abstract: A hybrid power or thrust generator including at least one thermodynamic turbine engine and at least one electric power generator. An electric power generator is electrically connected to at least one electric motor, mechanically and rotatably coupled to one or more rotating portions of the thermodynamic turbine engine, and the electric power generator operates simultaneously with the thermodynamic engine so as to supply the electric motor(s) to reduce the power drawn from the turbines of the thermodynamic turbine engine in operation. The electric power generator may comprise a thermoacoustic engine driving a linear electric alternator. The generator is advantageously implemented in a vehicle, such as an aircraft.

Abstract: An aircraft including a fuselage and at least one wing comprising, on the aerodynamic plane, a plurality of distributed airfoils separated from one another, numbering more than 10, and arranged inside an enclosing space bearing on the airfoils. The shape and dimensions of the enclosing space correspond to the shape and dimensions of a simple wing of conventional structure, which is adapted to the aircraft taking account of the weight and flight speed of the aircraft. Advantageously, the airfoils are arranged such that the cross-section of the enclosing space in a vertical plane XZ of the aircraft matches the shape of the aerodynamic profile of the simple wing of conventional structure. The airfoils are arranged, for example, to produce a V formation in plan view, with the tip pointing forwards.

Abstract: A three-dimensional structural framework having inflatable rings and a T-shaped cross-section along a plane passing through an axis of revolution of the inflatable rings in an inflated state. Shape-stabilizing elements are provided to stabilize the shape of the structural framework in space. Two inflatable rings are connected by at least one shape-stabilizing element. The structural framework is preferably used to produce stratospheric balloons.

Abstract: A spacecraft (10) includes: a body (20), a surface of revolution (40), rigidly connected to the body, the spacecraft including a heat engine positioned at the centre of the surface of revolution (40), and the surface of revolution includes a first portion (411) forming a solar concentrator for concentrating solar radiation in the direction of the heat engine and a second portion (412), coaxial with the first portion (411), and such that the first portion (411) and the second portion (412) form, relative to each other, a Cassegrain solar concentrator, of which a focal point is located at the heat engine.

Abstract: A device for the recovery of a proportion of the energy which is dissipated, by the Joule effect, by the equipment of a predetermined satellite in a vacuum atmosphere, includes at least one radiative panel (10) which is designed to permit the cooling of the satellite (20) payload, and a thermoelectric generator, the heat source (12) of which is supplied with infrared photons by the radiative panels (10), whereby the latter are configured to concentrate the infrared photons towards the heat source (12).

Abstract: A protection system (15) includes an inflatable bag (16) connected to inflation elements able and intended to be activated so as to inflate the inflatable bag in the event of and/or upon the prediction of an impact. The inflatable bag (16) has a substantially annular overall shape when inflated. Such a protection system (15) is advantageously intended to protect the passengers in a helicopter.

Abstract: A propulsion device for exerting a propulsive force on a vehicle generates an impulse of momentum by a piston of non-zero mass, an acceleration produced by a force acting on a structure of the vehicle and the braking produced in isolation inside the propulsion device without any force being applied to the vehicle. The piston moves inside a cross-shaped cavity from a reference position to an end of a cylindrical part of the cavity where it is stopped by a gas that it compresses adiabatically. The cross-shaped cavity is rotated by a quarter turn before the piston is released to return to the reference position. The propulsion device can comprise two cross-shaped cavities rotating in opposite directions.

Abstract: A three-dimensional structural framework has a plurality of inflatable rings, each having a T-shaped cross-section along a plane passing through an axis of revolution of the inflatable ring in an inflated state. A plurality of shape-stabilizing elements to stabilize the shape of the structural framework in space. Two inflatable rings are connected by at least one shape-stabilizing element. The structural framework is preferably used to produce stratospheric balloons.

Abstract: A system includes a plurality of liquid-hydrogen-producing balloon stations that form a total network for distributing liquid hydrogen, and said balloon stations in the network are positioned at the nearest of said target areas of use, substantially above the latter, such that the transfer of the liquid hydrogen between said production balloon stations and said target areas of use is minimal.

Abstract: According to the present disclosure, the system includes a plurality of liquid-hydrogen-producing balloon stations that form a total network for distributing liquid hydrogen, and said balloon stations in the network are positioned at the nearest of said target areas of use, substantially above the latter, such that the transfer of the liquid hydrogen between said production balloon stations and said target areas of use is minimal.

Abstract: A method is disclosed for placing a satellite in an operational orbit. The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device. The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher. The separate propulsion device is controlled by a satellite. The satellite is transferred from the transfer orbit to an intermediate orbit by means of the separate propulsion device. The separate propulsion device is separated from the satellite in the intermediate orbit. The satellite then enters and operational orbit from the intermediate orbit by means of its own satellite propulsion system. The intermediate orbit is disposed between the transfer and operational orbits, and is in relatively close proximity to the operational orbit but is far enough away from the operational orbit to prevent possible interferences.

Abstract: The present disclosure relates to an altitude-adjustable apparatus comprising: a platform; a device for controllably raising the altitude of the platform; a water supply combined with said platform; a device for converting water into the components thereof through solar power; and means for liquefying and storing the resulting liquefied hydrogen in tanks, the latter being built into flying bodies that are designed to arrive at a target area and dispense the liquefied hydrogen.

Abstract: A method is disclosed for placing a satellite in an operational orbit The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher The separate propulsion device is controlled by a satellite. The satellite is transferred from the transfer orbit to an intermediate orbit by means of the separate propulsion device. The separate propulsion device is separated from the satellite in the intermediate orbit.