4results about "Non-rigid airships" patented technology

The invention relates to an aircraft (2) comprising a wing (4) and means (6, 30) for propelling the aircraft (2); the wing (4) having a flexible, airtight envelope (18) designed to contain air; the flexible envelope (18) being configured such that, when it contains air in a nominal inflation state, the aerodynamic profile of the flexible envelope (18) alone generates the lift of the wing (4). The aircraft (2) may be a piloted aircraft of the airplane type or an unpiloted aircraft of the drone type. Abstract figure: Fig. 1

To provide an inflatable aircraft that can regulate pressure more efficiently. [Solution] An inflatable aircraft comprises a pressure regulating device for adjusting the internal pressure of the inflatable aircraft, a pressure sensor for acquiring information on the internal pressure of the inflatable aircraft, and an altitude sensor for acquiring altitude information. The pressure regulating device adjusts the pressure to fill the internal pressure deficit according to the difference between a set pressure, which is set to decrease as the altitude decreases based on the altitude information obtained from the altitude sensor, and the internal pressure obtained from the pressure sensor.

The invention relates to an aircraft (2) comprising a wing (4) and means (6, 30) for propelling the aircraft (2); the wing (4) comprising an airtight flexible envelope (18) intended to contain air; the flexible envelope (18) being configured such that, when it contains air in a nominal inflation state, the aerodynamic profile of the flexible envelope (18) is sufficient on its own to generate the lift of the wing (4). The aircraft (2) may be a piloted aircraft of the aeroplane type or an unpiloted aircraft of the drone type.

The system according to this embodiment aims to calculate the optimal launch window and orbit insertion parameters, taking into account weather conditions and rocket characteristics, and to plan the launch order and timing of multiple small satellites. [Solution] The system according to the embodiment comprises a weather forecasting unit, a characteristics analysis unit, an orbit calculation unit, and a planning unit. The weather forecasting unit predicts weather conditions. The characteristics analysis unit analyzes the characteristics of the rocket and payload based on the weather conditions predicted by the weather forecasting unit. The orbit calculation unit calculates the optimal launch window and orbit insertion parameters based on the characteristics analyzed by the characteristics analysis unit. The planning unit plans the launch order and timing of multiple small satellites based on the launch window and orbit insertion parameters calculated by the orbit calculation unit.