A rope deployment mechanism includes a load beam pivotable between an open position and a closed position. Also included is a linkage assembly engaged with the load beam in the closed position and moveable to allow the load beam to pivot to the open position. Further included is a locking rod operatively coupled to the linkage assembly. Yet further included is a sliding member translatable between a locked position and an unlocked position, wherein the sliding member is engaged with the locking rod to prevent movement of the locking rod and the linkage assembly in the locked position, and wherein the locking rod and the linkage assembly are moveable in the unlocked position. Also included is a lever configured to actuate movement of the linkage assembly to allow the load beam to move to the open position.

A position sensor system for a landing gear assembly includes a cylinder operatively coupled to an aircraft. Also included is a piston configured to translate within the cylinder. Further included is a pattern disposed on an outer surface of the piston. Yet further included is a scanner operatively coupled to the cylinder and positioned to optically detect the pattern during translation of the piston. Also included is a microprocessor in operative communication with the scanner and configured to receive data from the scanner for conversion to a quantity of movement of the piston relative to the cylinder.

A position sensor system for a landing gear assembly includes a cylinder operatively coupled to an aircraft. Also included is a piston configured to translate within the cylinder. Further included is a pattern disposed on an outer surface of the piston. Yet further included is a scanner operatively coupled to the cylinder and positioned to optically detect the pattern during translation of the piston. Also included is a microprocessor in operative communication with the scanner and configured to receive data from the scanner for conversion to a quantity of movement of the piston relative to the cylinder.

A system for sensing data in an aircraft, includes a plurality of wireless sensors, a receiver to sample a random subset of the plurality of wireless sensors at each of a plurality of times to generate a data matrix with a plurality of sampled entries and a plurality of missing entries, and an analysis unit to analyze the data matrix to provide a plurality of solutions corresponding to the plurality of missing entries using numerical analysis.

A system for sensing data in an aircraft, includes a plurality of wireless sensors, a receiver to sample a random subset of the plurality of wireless sensors at each of a plurality of times to generate a data matrix with a plurality of sampled entries and a plurality of missing entries, and an analysis unit to analyze the data matrix to provide a plurality of solutions corresponding to the plurality of missing entries using numerical analysis.

Provided is a dropping-type fire extinguishing body that, in fire extinguishing using a gel-like fire extinguishing agent, can allow the fire extinguishing agent to be smoothly conveyed and dropped.

A dropping-type fire extinguishing body 1 to be dropped onto the fire site to extinguish the fire, wherein a gelling agent 3 is contained in a bag body 2 formed of a water-permeable material and water is permeated into the body and is mixed with the gelling agent to prepare a gel-like fire extinguishing agent, thereby filling the gel-like fire extinguishing agent into the inside of the bag body.

Provided is a dropping-type fire extinguishing body that, in fire extinguishing using a gel-like fire extinguishing agent, can allow the fire extinguishing agent to be smoothly conveyed and dropped.

A dropping-type fire extinguishing body 1 to be dropped onto the fire site to extinguish the fire, wherein a gelling agent 3 is contained in a bag body 2 formed of a water-permeable material and water is permeated into the body and is mixed with the gelling agent to prepare a gel-like fire extinguishing agent, thereby filling the gel-like fire extinguishing agent into the inside of the bag body.

A method and system for vector limiting of a rotor control volume for a helicopter with one or more controllers configured to issue a displacement command during a flight maneuver and a computer operably connected to the one or more controllers and configured to receive signals with a processor indicative of a displacement command for a rotor during a flight maneuver; determine with the processor an origination point for a command vector in a reference frame; determine with the processor the command vector in the reference frame; determine with the processor a command radius for the command vector; compare with the processor the command radius with values of estimated command radii in a look-up table; and determine with the processor a control volume limited command in response to the comparing of the command radius with the estimated command radius.

A method and system for vector limiting of a rotor control volume for a helicopter with one or more controllers configured to issue a displacement command during a flight maneuver and a computer operably connected to the one or more controllers and configured to receive signals with a processor indicative of a displacement command for a rotor during a flight maneuver; determine with the processor an origination point for a command vector in a reference frame; determine with the processor the command vector in the reference frame; determine with the processor a command radius for the command vector; compare with the processor the command radius with values of estimated command radii in a look-up table; and determine with the processor a control volume limited command in response to the comparing of the command radius with the estimated command radius.

A cargo hook assembly for a helicopter is provided. The cargo hook assembly comprises a support structure having a forward end portion and a rearward end portion, and an attachment mechanism attached to the rearward end portion. The attachment mechanism is configured to engage a cargo hook mount on the underside of the fuselage of the helicopter. The cargo hook assembly further comprises first and second struts extending from respective opposing sides of the forward end portion. Each of the first and second struts is configured to engage a respective side mount on the fuselage of the helicopter. The cargo hook assembly also comprises a cargo hook suspended from the support structure.