Abstract: An apparatus for releasing received command data includes a processor unit with a code generator, a cryptography module, and a comparison module. The code generator generates a transaction code. The apparatus has a transmitting unit which provides the transaction code via an unsecured data connection, a receiving unit which receives an external authentication code and command data via the unsecured data connection, and a memory unit which stores data of a predefined private key. Also disclosed is a transmission apparatus for command data. The transmission apparatus has a basic receiving unit which receives the transaction code, an input unit which receives the command data, a basic memory unit which stores the data of the predefined private key, a basic processor unit which has a basic cryptography module, and a basic transmitting unit which provides the external authentication code and the command data via the unsecured data connection.

Abstract: An airfoil for flow control is disclosed having an outer skin in contact with an ambient air flow, wherein the outer skin extends between a leading edge and a trailing edge with two opposite lateral sides, and surrounds an interior space. The outer skin comprises a porous section in the area of the leading edge, a pressure chamber arranged in the interior space and fluidly connected to the porous section, an air inlet fluidly connected to the pressure chamber, and an air outlet fluidly connected to the pressure chamber.

Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).

Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).

Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).

Abstract: A vertical tail unit (7) including an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25) with opposite lateral sides (27a, 27b), and surrounds an interior space (29), and wherein the outer skin (13) has a porous section at the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13) and fluidly connected to the pressure chamber (15), and an air outlet (19) provided in the outer skin (13) and fluidly connected to the pressure chamber (15).

Abstract: An airfoil for flow control is disclosed having an outer skin in contact with an ambient air flow, wherein the outer skin extends between a leading edge and a trailing edge with two opposite lateral sides, and surrounds an interior space. The outer skin comprises a porous section in the area of the leading edge, a pressure chamber arranged in the interior space and fluidly connected to the porous section, an air inlet fluidly connected to the pressure chamber, and an air outlet fluidly connected to the pressure chamber.

Abstract: A method for operating an at least temporarily unmanned aircraft, wherein a flight is performed according to a prior flight plan in an airspace controlled by a control instance. A flight direction is determined during the flight via a control device influenced via a data connection by a control instance. The data connection is temporarily unavailable, and a hazardous or emergency situation requiring deviation from the flight plan, is identified by the control device based on first sensor data. An avoidance route is determined by the control device based on a second sensor data, the avoidance route including a avoidance manoeuvre avoiding the hazardous or emergency situation, the avoidance route is used in the meantime to fly towards a destination area with the least possible volume of air traffic; and the necessary avoidance manoeuvre(s) are performed based on the second data by the control device in an autonomous staggering procedure.

Abstract: A method for operating an, at least temporarily, unmanned aircraft or spacecraft wherein a flight procedure of the aircraft or spacecraft is carried out in controlled airspace using a previously cleared flight plan, wherein a C2 link is at least temporarily unavailable, and wherein at least one sensor device of the aircraft or spacecraft identifies a dangerous and/or emergency situation which makes it necessary to deviate from the cleared flight plan. To have available a method which makes it possible for an at least temporarily unmanned aircraft or spacecraft to react independently to particular dangerous and/or emergency situations and to avoid damaging events, a control device of the aircraft or spacecraft independently uses a wireless data link to a supervisory authority in order to agree to a changed flight plan containing at least one change.

Abstract: An apparatus for releasing received command data includes a processor unit with a code generator, a cryptography module, and a comparison module. The code generator generates a transaction code. The apparatus has a transmitting unit which provides the transaction code via an unsecured data connection, a receiving unit which receives an external authentication code and command data via the unsecured data connection, and a memory unit which stores data of a predefined private key. Also disclosed is a transmission apparatus for command data. The transmission apparatus has a basic receiving unit which receives the transaction code, an input unit which receives the command data, a basic memory unit which stores the data of the predefined private key, a basic processor unit which has a basic cryptography module, and a basic transmitting unit which provides the external authentication code and the command data via the unsecured data connection.

Abstract: An air-conditioning system for an aircraft has a fresh air line, a recirculation device, an air-mixing device, an air distribution system with multiple cabin air outlets, and a control unit. The control unit is designed to determine or to receive flight-specific parameters characterizing the flight state of the aircraft, and to determine or to receive environment-specific parameters which characterize an air quality in the environment of the aircraft. A first operating state of the air-conditioning system is brought about in the case of a predefined limit value of at least one environment-specific parameter being exceeded, and a second operating state of said system is brought about during a second flight state, which is outside the first flight state. In the second operating state, the fresh air line is fluidically connected to the air-mixing device, and in the first operating state, the fresh air line is separated from the air-mixing device.

Abstract: A vertical tail unit (7) for flow control including: an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25), and surrounds an interior space (29), and wherein the outer skin (13) includes a porous section (31) in the area of the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13), wherein the air inlet (17) is fluidly connected to the pressure chamber (15), wherein the air outlet (19) is fluidly connected to the pressure chamber (15). The vertical tail unit (7) has reduced drag and an increased efficiency because the air inlet (17) is formed as an opening (35) in the outer skin (13) at the leading edge (23).

Abstract: A vertical tail unit (7) including an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25) with opposite lateral sides (27a, 27b), and surrounds an interior space (29), and wherein the outer skin (13) has a porous section at the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13) and fluidly connected to the pressure chamber (15), and an air outlet (19) provided in the outer skin (13) and fluidly connected to the pressure chamber (15).

Abstract: A sensing orifice for an aircraft, an aircraft with such a sensing orifice and a method for assembling a sensing orifice for an aircraft are provided. The aircraft may be an airplane, a helicopter, a UAV, a drone or similar. The static sensing orifice includes a passage through an outer skin of the aircraft and a moisture protection body. The passage is designed to connect with a pressure line in the interior of the aircraft. The moisture protection body is gas-permeable and water-impermeable, and the moisture protection body is disposed such that the passage is gas-permeably and water-impermeably sealed. The method for assembling the static sensing orifice for the aircraft, includes the following steps: providing the passage through the outer skin of the aircraft for connecting to the pressure line in the interior of the aircraft, providing a gas-permeable and water-impermeable moisture protection body, and gas-permeable and water-impermeable sealing of the passage by the moisture protection body.

Abstract: A method for operating an, at least temporarily, unmanned aircraft or spacecraft wherein a flight procedure of the aircraft or spacecraft is carried out in controlled airspace using a previously cleared flight plan, wherein a C2 link is at least temporarily unavailable, and wherein at least one sensor device of the aircraft or spacecraft identifies a dangerous and/or emergency situation which makes it necessary to deviate from the cleared flight plan. To have available a method which makes it possible for an at least temporarily unmanned aircraft or spacecraft to react independently to particular dangerous and/or emergency situations and to avoid damaging events, a control device of the aircraft or spacecraft independently uses a wireless data link to a supervisory authority in order to agree to a changed flight plan containing at least one change.

Abstract: A sensing orifice for an aircraft, an aircraft with such a sensing orifice and a method for assembling a sensing orifice for an aircraft are provided. The aircraft may be an airplane, a helicopter, a UAV, a drone or similar. The static sensing orifice includes a passage through an outer skin of the aircraft and a moisture protection body. The passage is designed to connect with a pressure line in the interior of the aircraft. The moisture protection body is gas-permeable and water-impermeable, and the moisture protection body is disposed such that the passage is gas-permeably and water-impermeably sealed. The method for assembling the static sensing orifice for the aircraft, includes the following steps: providing the passage through the outer skin of the aircraft for connecting to the pressure line in the interior of the aircraft, providing a gas-permeable and water-impermeable moisture protection body, and gas-permeable and water-impermeable sealing of the passage by the moisture protection body.

Abstract: A method for emergency ventilation of an aircraft cabin is provided. The method includes controlling a first valve to supply air from the aircraft environment into a first aircraft fuselage area through the opened first valve and into the aircraft cabin. The method further includes controlling a second valve to conduct air from the aircraft cabin into a second aircraft fuselage area and out to the aircraft environment through the opened second valve. In their normal operation, the first and second valves serve as air outlet valves of an aircraft cabin pressure control system. The method further includes controlling a recirculation fan of an air-conditioning system to draw air supplied through the first valve into a mixing chamber of the air-conditioning system and to direct air from the mixing chamber into the aircraft cabin.

Abstract: An air outlet valve for use in an aircraft is adapted during normal operation of the aircraft as a component of a cabin pressure control system for adjusting a desired pressure level in an aircraft cabin to remove air from an interior of the aircraft into the environment around the aircraft. The air outlet valve is further adapted during emergency ventilation operation of the aircraft as a component of a system for emergency ventilation of the aircraft cabin to introduce air from the environment around the aircraft into the interior of the aircraft. The air outlet valve comprises a nose-side valve flap, which is pivotable about an axis and is adapted to open or close a nose-side portion of an air outlet valve aperture, and a tail-side valve flap, which is pivotable about an axis and is adapted to open or close a tail-side portion of the air outlet valve aperture.

Abstract: The invention relates to a method for emergency ventilation of an aircraft cabin (36), comprising controlling a first valve (14) arranged in a first aircraft fuselage area (28), said valve serving as an air outlet valve of an aircraft cabin pressure control system in its normal operation, such that air is supplied from the aircraft environment into the first aircraft fuselage area (28) through the opened first valve (14) and is conducted from the first aircraft fuselage area (28) into the aircraft cabin. A second valve (16), arranged in a second aircraft fuselage area (38) spaced apart from the first aircraft fuselage area (28) along a longitudinal axis (22) of the aircraft (10) and is serving as an additional air outlet valve of the aircraft cabin pressure control system in its normal operation, is controlled such that air from the aircraft cabin (36) is conducted into the second aircraft fuselage area (38) and discharged into the aircraft environment through the opened second valve (16).

Abstract: An air outlet valve for use in an aircraft is adapted during normal operation of the aircraft as a component of a cabin pressure control system for adjusting a desired pressure level in an aircraft cabin to remove air from an interior of the aircraft into the environment around the aircraft. The air outlet valve is further adapted during emergency ventilation operation of the aircraft as a component of a system for emergency ventilation of the aircraft cabin to introduce air from the environment around the aircraft into the interior of the aircraft. The air outlet valve comprises a nose-side valve flap, which is pivotable about an axis and is adapted to open or close a nose-side portion of an air outlet valve aperture, and a tail-side valve flap, which is pivotable about an axis and is adapted to open or close a tail-side portion of the air outlet valve aperture.