摘要:
Disclosed is a vehicle propulsion system (1000) comprising a propulsion device (201), a turbine (210) mechanically coupled to the propulsion device (201) and configured to drive the propulsion device (201), a fuel cell (110) having an exhaust outlet (111), and an exhaust duct (220) connecting the exhaust outlet (111) of the fuel cell (110) with the turbine (210). The turbine (210) is driven by exhaust gas of the fuel cell (110) conducted through the exhaust duct (220). Furthermore, a vehicle (1) having such vehicle propulsion system (1000) is also disclosed.
摘要:
A nacelle (250; 350; 450; 550) may comprise an inlet cowling (202; 302; 402; 502) defining an inlet of the nacelle, wherein the inlet cowling (202; 302; 402; 502) comprises an inlet cowling maximum point (207; 307; 407; 507) and an inlet cowling aft edge (210; 310; 410; 510), wherein the inlet cowling aft edge (210; 310; 410; 510) comprises an aft edge length; and a boat tail cowling (230; 330; 430; 530) disposed aft of the inlet cowling (202; 302; 402; 502), wherein the boat tail cowling (230; 330; 430; 530) comprises a boat tail cowling forward edge (224; 324; 424; 524) having a forward edge length, and wherein the boat tail cowling forward edge (224; 324; 424; 524) is disposed adjacent to the inlet cowling aft edge (210; 310; 410; 510). The forward edge length may be smaller than the aft edge length, forming a step, the step being defined by a portion of the inlet cowling aft edge (210; 310; 410; 510) that is radially outward of the boat tail cowling forward edge (224; 324; 424; 524).
摘要:
The present invention includes pilotable capsules, detachable from an aircraft and aircrafts including such capsules. According to some embodiments, there may be provided one or more capsules capable of flight and designed to detachably connect to an aircraft. According to some embodiments, detachable capsules may be designed to carry cargo and/or passengers. According to some embodiments, detachable capsules may, after detachment, be piloted by pilots or by automated systems (unmanned) or a combination of the two.
摘要:
A pitch change mechanism (100:200) for a bladed rotor comprises a driving sleeve (110:210), a drive shaft (102:202), a first pitch-changing element (130:230), a second pitch-changing element (150:250), and a plurality of blade drive gears (180). The driving sleeve (110:210) has, in axial sequence, a first helical connection portion (133:233) and a second helical connection portion (153:253). The driving sleeve (110:210) is positioned concentrically with and surrounding the drive shaft (102:202). The first pitch-changing element (130:230) has a first end (132:232) drivingly engaged with the first helical connection portion (133:233), and a first ring gear portion (140:240) at a second opposite end (138:238), while the second pitch-changing element (150:250) has a first end (152:252) drivingly engaged with the second helical connection portion (153:253), and a second ring gear portion (160:260) at a second opposite end (158:258). The plurality of blade drive gears (180) are arranged in a circumferential array around a longitudinal axis of the drive shaft (102:202). The first pitch-changing element (130:230) is positioned axially adjacent to the second pitch-changing element (150:250) with the first ring gear portion (140:240) facing the second ring gear portion (160:260). Each of the first and second pitch-changing elements (130:230,150:250) is positioned concentrically over the driving sleeve (110:210), such that axial movement of the driving sleeve (110:210) causes the first helical connection portion (133:233) to rotate the first pitch-changing element (130:230) in a first rotational direction (144), and simultaneously causes the second helical connection portion (153:253) to rotate the second pitch-changing element (150:250) in an opposite second rotational direction (164), with the contra-rotation of the first and second pitch-changing elements (130:230,150:250) causing a rotation of the plurality of blade drive gears (180) positioned between and meshingly coupled to each of the first ring gear portion (140:240) and the second ring gear portion (160:260).
摘要:
Aspects of the disclosure are directed to a nacelle of an aircraft, comprising a surface that is profiled such that during cruise flight operation lines of constant static pressure of a boundary layer around the nacelle (322; 422; 522) in a given region are substantially contained within a plane that is normal to an engine axis.