초록 ▼

An aircraft which is configured for vertically ascending and landing, includes at least two wings (2a, 2b, 4a, 51, 4b, 52), a space (2c, 4c) for the generating during operation of climbing power, and an intermediate portion (3), the intermediate portion (3) being provided with thrust motors (6), and

An aircraft which is configured for vertically ascending and landing, includes at least two wings (2a, 2b, 4a, 51, 4b, 52), a space (2c, 4c) for the generating during operation of climbing power, and an intermediate portion (3), the intermediate portion (3) being provided with thrust motors (6), and the space (2c, 4c) for the generating during operation of climbing power being provided with a quantity of lifting power units (HV). Each lifting power unit includes a first variable volume (V1) for the storage of an amount of relatively light gas which is lighter than atmospheric air, and is configured for the controllable adjustment of an upward force or lifting power by the variable volume taken up by the amount of relatively light gas.

대표청구항 ▼

1. An aircraft configured for vertically ascending and landing, comprising: at least two wings for generating upward force during forward movement;a space for generating lifting power that contributes to an overall climbing power of the aircraft, the space being provided with a quantity of lifting p

1. An aircraft configured for vertically ascending and landing, comprising: at least two wings for generating upward force during forward movement;a space for generating lifting power that contributes to an overall climbing power of the aircraft, the space being provided with a quantity of lifting power units, each lifting power unit comprising a first variable volume for the storage of an amount of relatively light gas which is lighter than atmospheric air, each lifting power unit being configured for the controllable adjustment of the lifting power by means of the first variable volume taken up by the amount of relatively light gas,a gastight total volume in which the first variable volume and a second variable volume are received, the second variable volume being configured for the storage of an amount of gas which is heavier than the relatively light gas, each lifting power unit being configured for the adjustment of a ratio between the first variable volume and the second variable volume within the gastight total volume, the ratio corresponding to a desired lifting power,a flexible wall separating the first variable volume from the second variable volumea first pump configured for the adjustment of the first variable volume,a second pump configured for the adjustment of the second variable volume,a storage vessel configured for the storage of the relatively light gas on expulsion thereof from the first variable volume,a lifting power controller connected to the first pump and the second pump for the controlling of one or more of the first and second pumps in order to adapt the first variable volume or the second variable volume respectively, the lifting power controller being connected to an on-board computer, the lifting power controller being configured for the receiving from the onboard computer of a lifting power control signal for the adjustment of the desired lifting power, the on-board computer being connected to at least one of a position sensor configured for the generating of a position signal for a position of the aircraft, a meteo sensor configured for the generating of a weather condition signal and a load sensor configured for the generating of a load signal of the construction of the aircraft by a load, the on-board computer configured for the receiving of sensor signals from the at least one sensor, the on-board computer being configured to determine, on the basis of the one or more sensor signals, trimming data for the purposes of trimming of the aircraft, the on-board computer being configured to regulate the trimming dynamically based on the upward force generated by the at least two wings contributing to the climbing power of the aircraft; andan intermediate portion provided with thrust motors. 2. The aircraft as claimed in claim 1, wherein the first variable volume comprises at least a first heat exchanger which is configured for exchanging heat with the relatively light gas in the first variable volume. 3. The aircraft as claimed in claim 2, wherein the second variable volume comprises at least a second heat exchanger which is configured for exchanging heat with the relatively heavier gas in the second variable volume. 4. The aircraft as claimed in claim 1, wherein the second variable volume comprises at least a heat exchanger which is configured for exchanging heat with the relatively heavier gas in the second variable volume. 5. The aircraft as claimed in claim 1, wherein the lifting power controller is also connected to one or more heat exchangers for the controlling of the one or more heat exchangers. 6. The aircraft as claimed in claim 1, wherein an at least first sensor is positioned in the first variable volume, an at least second sensor is positioned in the second variable volume, the at least first sensor and at least second sensor are connected to the lifting power controller, each of the first and second sensors being configured for the measuring of one or more relevant physical parameters including one or more of pressure and temperature of the relatively light gas in the first variable volume and/or the relatively heavy gas in the second variable volume, the lifting power controller being configured for the receiving of signals from the respective sensors and configured to control the desired lifting power based on the measured relevant physical parameters. 7. The aircraft as claimed in claim 1, wherein the on-board computer is configured for determining the lifting power of each of the lifting power units. 8. The aircraft as claimed in claim 1, wherein the on-board computer is configured to determine and to control on the basis of the trimming data a desired lifting power. 9. The aircraft as claimed in claim 8, wherein the on-board computer is configured to determine and to control a distribution of lifting power over the amount of lifting power units. 10. The aircraft as claimed in claim 1, wherein the on-board computer is configured to determine and to control on the basis of the trimming data a thrust force and a direction of propulsion of the thrust motors. 11. The aircraft as claimed in claim 1, wherein the on-board computer is configured to regulate the trimming dynamically as a result of the desired lifting power from a lift generating gas volume including the first variable volume and the second variable volume having the adjusted ratio within the gastight total volume in combination with the upward force from the at least two wings that contribute to the climbing power of the aircraft.