Abstract: A transport system intended to be installed on a space launcher comprises: an aircraft which comprises propulsion means configured to propel the aircraft in a direction of flight, and at least one seat intended to receive a passenger which is movable in rotation about an axis perpendicular to the direction of flight of the aircraft, an acceleration sensor being installed on each at least one seat to measure the acceleration of each at least one seat; a passenger interface for each at least one seat which comprises a screen intended to display images to the passenger installed on said at least one seat, the screen being coupled to said at least one seat so to remain fixed relative to said at least one seat; a control unit which is connected to the acceleration sensor and to said at least one seat.

Abstract: The invention relates to a transport system (1) intended to be installed on a space launcher (100) comprising: an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended to receive a passenger which is movable in rotation about an axis (0) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4); a passenger interface for each at least one seat (4) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed relative to said at least one seat (4); a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed on the at least one s

Abstract: Embodiments of the invention relate to a hypersonic transport system including: an aircraft which includes a hypersonic lift-to-drag ratio greater than or equal to 2.5, wherein the aircraft includes a secondary propulsion device and position sensors, and wherein the aircraft also includes a variably shaped aerodynamic surface; a main propulsion device which is removably attached to the aircraft; and a control unit which is configured to monitor the aircraft and the main propulsion device.