A fuel cell vehicle provides improved space utilization and a desired intensity of voltage. The fuel cell vehicle includes a fuel cell, a junction box disposed on the fuel cell, and a power controller disposed between the fuel cell and the passenger compartment. The power controller boosts the output voltage of the fuel cell.

A fuel cell vehicle includes a cabin arranged at a vehicle front portion and provided with a seat therein where an occupant is seated, a fuel cell mounted below the cabin, and an accommodation space formed below the cabin and accommodating the fuel cell. An upper side of the accommodation space is covered with a ceiling surface formed by a bottom portion of the cabin, and a rear side of the accommodation space is opened. The ceiling surface is provided with a detector configured to detect a hydrogen concentration in the accommodation space.

A fuel cell vehicle includes a cabin arranged at a vehicle front portion and provided with a seat therein where an occupant is seated, a fuel cell mounted below the cabin, and an accommodation space formed below the cabin and accommodating the fuel cell. An upper side of the accommodation space is covered with a ceiling surface formed by a bottom portion of the cabin, and a rear side of the accommodation space is opened. The ceiling surface is provided with a detector configured to detect a hydrogen concentration in the accommodation space.

The invention relates to a hybrid electric drive system (10) for multi-motor aircraft (20). The hybrid electric drive system comprises at least a first and a second hybrid electric drive unit (31, 32), each of which comprises: an internal combustion engine (41, 42), a motor-generator unit (71, 72) and a gear box (51, 52) for transmitting drive power to a propeller (61, 62). In order to supply the motor-generator units (71, 72) with electrical energy, the drive system (10) has a fuel cell (73), which in turn is supplied with hydrogen by means of a fuel tank (74). In the fuel cell (73), hydrogen is converted into electricity, which then supplies the motor-generator unit (71, 72) with electrical power by means of the transmission device (80) and power converters (81) and (82), in order to drive the propellers (61, 62). Advantages: On the basis of a turboprop aircraft (20) with approximately 40 to 90 passengers, approximately 40% of the energy during a 1-hour mission can be provided emission-free by means of hydrogen and fuel cell. This means no CO2 emissions at all during the cruising flight and also no climate-damaging exhaust-gas and contrail effects at cruising altitude (FL250), which are a significant share of aviation emissions.

The invention relates to a hybrid electric drive system (10) for multi-motor aircraft (20). The hybrid electric drive system comprises at least a first and a second hybrid electric drive unit (31, 32), each of which comprises: an internal combustion engine (41, 42), a motor-generator unit (71, 72) and a gear box (51, 52) for transmitting drive power to a propeller (61, 62). In order to supply the motor-generator units (71, 72) with electrical energy, the drive system (10) has a fuel cell (73), which in turn is supplied with hydrogen by means of a fuel tank (74). In the fuel cell (73), hydrogen is converted into electricity, which then supplies the motor-generator unit (71, 72) with electrical power by means of the transmission device (80) and power converters (81) and (82), in order to drive the propellers (61, 62). Advantages: On the basis of a turboprop aircraft (20) with approximately 40 to 90 passengers, approximately 40% of the energy during a 1-hour mission can be provided emission-free by means of hydrogen and fuel cell. This means no CO2 emissions at all during the cruising flight and also no climate-damaging exhaust-gas and contrail effects at cruising altitude (FL250), which are a significant share of aviation emissions.

The present invention has an object of functionally and efficiently laying out a cooling system in a fuel cell system. A fuel cell system includes a stack, an anode system, a cathode system, a first cooling system and a second cooling system. The first cooling system includes a first heat exchanger, and circulates coolant between a predetermined first radiator and the first heat exchanger. The second cooling system includes a plurality of second heat exchangers, and circulates coolant between a second radiator and each of the second heat exchangers. The plurality of second heat exchangers are collectively arranged so that, for each of the second heat exchangers, a heat exchanger other than itself closest to itself among all of the heat exchangers including the first heat exchanger and the plurality of second heat exchangers is a second heat exchanger other than itself.

The present invention has an object of functionally and efficiently laying out a cooling system in a fuel cell system. A fuel cell system includes a stack, an anode system, a cathode system, a first cooling system and a second cooling system. The first cooling system includes a first heat exchanger, and circulates coolant between a predetermined first radiator and the first heat exchanger. The second cooling system includes a plurality of second heat exchangers, and circulates coolant between a second radiator and each of the second heat exchangers. The plurality of second heat exchangers are collectively arranged so that, for each of the second heat exchangers, a heat exchanger other than itself closest to itself among all of the heat exchangers including the first heat exchanger and the plurality of second heat exchangers is a second heat exchanger other than itself.

A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

The invention relates to a fuel cell system (100) for a vehicle (F), comprising a vehicle frame or vehicle body part, having: at least one fuel cell module (M1, M2) and a support structure (10) for supporting the fuel cell system (100) on the vehicle frame or the vehicle body part, wherein the support structure (10) has at least one inner component support (13) relative to the at least one fuel cell module (M1, M2), submodules of the at least one fuel cell module (MI, M2) are connected to the at least one inner component support (13), and the at least one component support (13) has at least one securing interface (11, 12) in order to secure the fuel cell system (100) on the vehicle frame or the vehicle body part.

The invention relates to a fuel cell system (100) for a vehicle (F), comprising a vehicle frame or vehicle body part, having: at least one fuel cell module (M1, M2) and a support structure (10) for supporting the fuel cell system (100) on the vehicle frame or the vehicle body part, wherein the support structure (10) has at least one inner component support (13) relative to the at least one fuel cell module (M1, M2), submodules of the at least one fuel cell module (MI, M2) are connected to the at least one inner component support (13), and the at least one component support (13) has at least one securing interface (11, 12) in order to secure the fuel cell system (100) on the vehicle frame or the vehicle body part.