A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

A remote control device for an unmanned helicopter includes an orientation sensor that detects a flight orientation of the unmanned helicopter, a GPS antenna and a GPS receiver that detect speed information of the unmanned helicopter, and a CPU that detects a flight distance of the unmanned helicopter by integrating the speed information. A memory stores information concerning a base point of the unmanned helicopter. Based on a flight orientation of the unmanned helicopter and a flight distance of the unmanned helicopter, which is obtained by integration of the speed information, the CPU determines a relative position, which indicates a position of the unmanned helicopter with respect to the base point, and controls the flight of unmanned helicopter based on the relative position.

A remote control device for an unmanned helicopter includes an orientation sensor that detects a flight orientation of the unmanned helicopter, a GPS antenna and a GPS receiver that detect speed information of the unmanned helicopter, and a CPU that detects a flight distance of the unmanned helicopter by integrating the speed information. A memory stores information concerning a base point of the unmanned helicopter. Based on a flight orientation of the unmanned helicopter and a flight distance of the unmanned helicopter, which is obtained by integration of the speed information, the CPU determines a relative position, which indicates a position of the unmanned helicopter with respect to the base point, and controls the flight of unmanned helicopter based on the relative position.

A brake control system 200 and method 300 for controlling a park brake of an aircraft including a controller 201 configured to cause an increase in a brake torque of the park brake based of an indication to the controller. The indication is generated in response to touchdown of the aircraft.

An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation.

Systems and methods of warning a pilot of a helicopter about a servo transparency condition include devices and steps for retrieving, from a design performance database, a plurality of design performance parameters of the helicopter, and receiving avionics data from an avionics data source, the avionics data representative of a plurality of actual performance parameters of the helicopter. The design performance parameters and the avionics data are processed to determine whether one or more of the actual performance parameters exceed the design performance parameters, thereby indicating a servo transparency condition exists. One or more alerts are generated when the servo transparency condition exists.

Systems and methods of warning a pilot of a helicopter about a servo transparency condition include devices and steps for retrieving, from a design performance database, a plurality of design performance parameters of the helicopter, and receiving avionics data from an avionics data source, the avionics data representative of a plurality of actual performance parameters of the helicopter. The design performance parameters and the avionics data are processed to determine whether one or more of the actual performance parameters exceed the design performance parameters, thereby indicating a servo transparency condition exists. One or more alerts are generated when the servo transparency condition exists.

A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.

A water station consisting of a large water tank or bag with a plurality of dangling appendages for lowering toward the ground. These appendages include heat sensors and sprayers, and one or more may be capable of connecting to a fire fighting truck, water tank, fire hydrants, or other pieces of equipment. One or more appendages may also include a bag containing fire-fighting safety gear or ground-based hoses for fighting fires. Cameras and other sensors provide constant feedback to the pilot of the aircraft, such as a helicopter, deploying the water station.