Nuclear Aircraft Transportation System “KARAVAN” with its components is represented by a group of inventions in the technical and organizational relations. The main and basic invention is Nuclear Aircraft Transportation System “KARAVAN” (NATS). This invention includes two other ones: Aircraft Thrust Nuclear Power Plant, (ATNPP), which in turn includes—Thermal Power Cycle of ATNPP, (TPC ATNPP). In addition, the represented group of inventions is made up of two more inventions: Maintenance System of ATNPP, (MS ATNPP) and Emergency Response System of NATSK, (ERS NATSK).

The concept of practical implementation of the presented group of inventions involves the fact that ATNPP, which is a large unmanned drone aircraft “Tiagach”, supplies the aero-train composed of a number of passenger liners and cargo transport planes using electric motors with traction electric energy in the air.

The power supply of such an aero-train is based on the onboard Nuclear Power Plant of the aircraft “Tiagach”. In this case, the transmission of electric power to the towed electric aircraft of the aero-train is carried out by means of electric split feeders and cables, connecting and disconnecting of which between airplanes of the aero-train is carried out in the air, by analogy with refueling of airplanes in the air with JP fuel.

During the flight of the aero-train on a logistically optimized route, electric airplanes can detach from and attach to the aero-train, taking off and landing along the flight route of the aero-train using their own electric accumulators. In addition, extra ATNPP may be included in the aero-train during its flight, if it is necessary to increase the thrust. At the same time, due to the use of nuclear power, such ATNPP can remain in the air for a conditionally indefinite period of time.

The invention is aimed at creating cost-effective air freight and passenger traffic.

Nuclear Aircraft Transportation System “KARAVAN” with its components is represented by a group of inventions in the technical and organizational relations. The main and basic invention is Nuclear Aircraft Transportation System “KARAVAN” (NATS). This invention includes two other ones: Aircraft Thrust Nuclear Power Plant, (ATNPP), which in turn includes—Thermal Power Cycle of ATNPP, (TPC ATNPP). In addition, the represented group of inventions is made up of two more inventions: Maintenance System of ATNPP, (MS ATNPP) and Emergency Response System of NATSK, (ERS NATSK).

The concept of practical implementation of the presented group of inventions involves the fact that ATNPP, which is a large unmanned drone aircraft “Tiagach”, supplies the aero-train composed of a number of passenger liners and cargo transport planes using electric motors with traction electric energy in the air.

The power supply of such an aero-train is based on the onboard Nuclear Power Plant of the aircraft “Tiagach”. In this case, the transmission of electric power to the towed electric aircraft of the aero-train is carried out by means of electric split feeders and cables, connecting and disconnecting of which between airplanes of the aero-train is carried out in the air, by analogy with refueling of airplanes in the air with JP fuel.

During the flight of the aero-train on a logistically optimized route, electric airplanes can detach from and attach to the aero-train, taking off and landing along the flight route of the aero-train using their own electric accumulators. In addition, extra ATNPP may be included in the aero-train during its flight, if it is necessary to increase the thrust. At the same time, due to the use of nuclear power, such ATNPP can remain in the air for a conditionally indefinite period of time.

The invention is aimed at creating cost-effective air freight and passenger traffic.

A system for airborne remote sensing comprises an array of remote sensing devices configured for being towed by an aircraft. Each of the array of remote sensing devices is configured for lateral separation in flight, to provide a large coverage area than any of the array of remote sensing devices can cover by itself. Onboard electronics comprise sensors, such as a forward imaging infrared camera for capturing data in flight. By analyzing the data collected by the remote sensing system, various types of information can be generated, such as hydrocarbon leak detection.

An assembly is configured for connection to an unmanned aerial vehicle (UAV) and comprises a plurality of emulator devices each configured for attachment to the UAV and a plurality of first connection tethers each configured to operably couple a respective one of the plurality of emulator devices to the UAV at a respective spacing from the UAV. The emulator devices each comprise an emulation component configured to provide, to a target detection system, a characteristic associated with a respective type of airborne object. The plurality of respective first connection tethers each comprises material that does not substantially reflect RF energy. During flight of the UAV, when the assembly is connected, each respective emulator device maintains the respective spacing from the UAV and emulates the characteristic to the target detection system, such that the assembly emulates, to the target detection system, a plurality of airborne objects.

An assembly is configured for connection to an unmanned aerial vehicle (UAV) and comprises a plurality of emulator devices each configured for attachment to the UAV and a plurality of first connection tethers each configured to operably couple a respective one of the plurality of emulator devices to the UAV at a respective spacing from the UAV. The emulator devices each comprise an emulation component configured to provide, to a target detection system, a characteristic associated with a respective type of airborne object. The plurality of respective first connection tethers each comprises material that does not substantially reflect RF energy. During flight of the UAV, when the assembly is connected, each respective emulator device maintains the respective spacing from the UAV and emulates the characteristic to the target detection system, such that the assembly emulates, to the target detection system, a plurality of airborne objects.

The present disclosure relates to a remote sensing system, comprising: an air towable housing for carrying one or more sensors, the air towable housing and/or a comprising at least a first pulley.

The present disclosure relates to a remote sensing system, comprising: an air towable housing for carrying one or more sensors, the air towable housing and/or a comprising at least a first pulley.

A driving device includes a frame, a screw-nut system comprising a threaded rod and a first nut helicoidally connected to the threaded rod, the threaded rod being connected to the frame by a pivot connection that allows the threaded rod to rotate with respect to the frame about a longitudinal axis of the threaded rod, a first position sensor making it possible to detect a limit position of the first nut along the longitudinal axis, the first position sensor comprising a first part and a second part, the first position sensor being sensitive to a variation in a distance between the first part and the second part of the first position sensor along the axis, the first part being fixed to the first nut and the second part being connected to the threaded rod without passing via the pivot connection and in such a way that rotation of the threaded rod about the longitudinal axis leads to a variation in the distance between the first part and the second part of the first position sensor along the longitudinal axis.

An active countermeasure for military rotorcraft against a heat-seeking missile threat involves one or more telescoping booms or poles that are articulated at their proximal end to the fuselage of the rotorcraft and have an IR-radiating decoy mounted on their distal tip. When a missile launch is detected the missile flight path is computed and one or more of the booms are extended and swung out to place the decoy on the shot line of the missile. The decoy is then switched on and lures the missile away from the vulnerable components of the craft, such as the engine, rotors, and fuselage so as to cause a miss or failing that a detonation away from the rotorcraft. The countermeasures are stored compactly against or within the tail when not deployed.

An active countermeasure for military rotorcraft against a heat-seeking missile threat involves one or more telescoping booms or poles that are articulated at their proximal end to the fuselage of the rotorcraft and have an IR-radiating decoy mounted on their distal tip. When a missile launch is detected the missile flight path is computed and one or more of the booms are extended and swung out to place the decoy on the shot line of the missile. The decoy is then switched on and lures the missile away from the vulnerable components of the craft, such as the engine, rotors, and fuselage so as to cause a miss or failing that a detonation away from the rotorcraft. The countermeasures are stored compactly against or within the tail when not deployed.