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.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

To prevent a parachute from being damaged. A parachute device (4) includes a flying body (43) including a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, an ejection section (41) having a tube shape and configured to hold the flying body and to eject the held flying body, a gas generating device (60) configured to generate gas, and an extrusion member (42) capable of being at least partially inserted into the ejection section, the extrusion member being configured to extrude the flying body from the ejection section due to receiving pressure of the gas generated from the gas generating device.

A parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. Some versions of the parafoil comprise flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible member may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle.

Disclosed is an apparatus and method for operating a gliding parachute/kite. The gliding parachute/kite has a wing with a flexible material, and a set of suspension lines adapted for coupling a load to the wing, such that the coupling is configurable in any one of a plurality of possible states based on relative lengths of the suspension lines. In some implementations, the possible states include a first state enabling gliding in a first direction, and a second state enabling gliding in a second direction that is opposite to the first direction. Reversing direction is possible with the first and second states. Additionally, or alternatively, the possible states include a spinning state enabling spinning of the gliding parachute/kite. Adjusting a rate of decent is possible with the spinning. Reversing direction and/or spinning operations can be used to improve control of trajectory.

Aspects described herein relate to an apparatus, system, and method for the airborne launch of inflatable, lighter-than-air devices from aircraft. In some instances, a container comprising a drag parachute and a main parachute assembly may be deployed from an aircraft. Drag forces on the container may cause the drag parachute to be expelled from the container. Drag forces on the drag parachute may cause the main parachute assembly to be expelled from the container. The main parachute assembly may include a canopy with an opening and a release channel connecting the opening with the container. The container may further include a balloon inflation mechanism, which may be used to inflate one or more balloon envelopes. The one or more balloon envelopes, after being inflated, may be configured to be released from the container, traverse the release channel, and exit the main parachute assembly through the opening.

Described herein are features for a riser release flaring system for parafoils and other descent flight vehicles for controlled descent and landing of the flight vehicle. The descent flight vehicle may have a payload suspended by a canopy. The descent flight vehicle may be released from a high altitude lighter-than-air (LTA) system, from another system, or may not be associated with any other flight system. The riser release auto flare system is used with the descent system, such as the parafoil, for controlled and safe landing of the payload. Riser lines are released at a controlled rate and for a fixed distance to automatically cause the payload to pull control lines to flare the parafoil and slow a descent and/or forward speed of the vehicle. The riser lines may be released in response to the descent system satisfying a landing criterion, such as altitude.

The present invention generally relates to deformable polymer composites, and more particularly to, deformable polymer composites with controlled electrical performance during deformation through tailored strain-dependent conductive filler contact. According to embodiments, a deformable elastomeric conductive material includes: an elastomeric polymer matrix; and conductive filler material uniformly dispersed in the elastomeric polymer matrix sufficient to render the material electrically or thermally conductive. The conductive filler material comprises a plurality of substantially non-entangled particles having an aspect ratio sufficiently large to enable the particles to substantially remain in contact and/or in close proximity with adjacent particles so as to maintain conductive pathways in the material when the material is subjected to deformation up to and exceeding 10% strain.

The present invention generally relates to deformable polymer composites, and more particularly to, deformable polymer composites with controlled electrical performance during deformation through tailored strain-dependent conductive filler contact. According to embodiments, a deformable elastomeric conductive material includes: an elastomeric polymer matrix; and conductive filler material uniformly dispersed in the elastomeric polymer matrix sufficient to render the material electrically or thermally conductive. The conductive filler material comprises a plurality of substantially non-entangled particles having an aspect ratio sufficiently large to enable the particles to substantially remain in contact and/or in close proximity with adjacent particles so as to maintain conductive pathways in the material when the material is subjected to deformation up to and exceeding 10% strain.