Jump strut landing gear apparatus and system

Claim 2

A jump strut landing gear apparatus for an aircraft comprising: (a) a fluid generator for generating a predetermined quantity of compressed fluid having a known energy; (b) a fluid accumulator for accumulating the compressed fluid to a predetermined pressure; (c) a hydraulic accumulator for receiving the compressed fluid at said predetermined pressure; (d) an extendable landing gear strut driven by said hydraulic accumulator to impart a predetermined vertical acceleration to the aircraft; and (e) an adjustable energy management control means for controlling the quantity of compressed fluid generated by said fluid generator to control the vertical acceleration imparted to the aircraft by said extendable landing gear strut, and including input means for manually inputting a desired acceleration quantity in accordance with the gross weight of the aircraft and desired takeoff distance, said adjustable energy management control means further being adapted to monitor aircraft performance sensors and utilizing data generated by said sensors in order to control said quantity of compressed fluid generated by said fluid generator.

Claim 3

An apparatus according to claim 1, wherein said fluid generator comprises: (a) a housing adapted to be bolted onto a landing gear assembly; (b) a reloadable cartridge for receiving a plurality of individually ignitable pyrotechnic charges for generating a predetermined quantity of compressed fluid, each charge having a known quantity of available energy; (c) a firing initiator of each charge; (d) a fluid generator manifold for conducting the compressed fluid from the charges; (e) a fluid generator plenum for collecting generated compressed fluid from said manifold to a predetermined pressure; and (f) a filter for removing particulate matter from the compressed fluid.

Claim 4

The apparatus according to claim 2 wherein said fluid accumulator further comprises a pressure release valve for releasing the compressed fluid to a predetermined threshold pressure.

Claim 5

The apparatus according to claim 3 wherein said fluid accumulator further comprises a pressure sensor for sensing the internal pressure of said fluid accumulator and for providing over-pressurization signals to said energy management control means for deactivating said firing initiators to prevent further ignition of pyrotechnic charges thereby assuring against further pressurization of said accumulator.

Claim 6

A jump strut landing gear system for an aircraft having an undercarriage for surface support, the undercarriage having at least one landing gear assembly, said system comprising: (a) fluid generator for explosively generating a predetermined quantity of compressed fluid having a known energy; (b) an extendable landing gear strut associated with at least one landing gear assembly, said strut being extendably driven by said predetermined quantity of explosively generated compressed fluid to impart a vertical acceleration to the aircraft; and (c) an adjustable management control means for controlling the quantity of compressed fluid generated by said fluid generator to determine the vertical acceleration imparted to the aircraft by said extendable landing gear strut, and including input means for manually inputting a desired acceleration quantity in accordance with the gross weight of the aircraft and desired takeoff distance, said adjustable energy management control means further being adapted to monitor aircraft performance sensors and utilizing data generated by said sensors in order to control said quantity of compressed fluid generated by said fluid generator.

Claim 7

A jump strut landing gear system for an aircraft having an undercarriage for surface support, the undercarriage having at least one landing gear assembly, said system comprising: (a) fluid generator for explosively generating a predetermined quantity of compressed fluid having a known energy; (b) an extendable landing gear strut associated with at least one landing gear assembly, said strut being extendably driven by said predetermined quantity of explosively generated compressed fluid to impart a vertical acceleration to the aircraft; and (c) an adjustable management control means for controlling the quantity of compressed fluid generated by said fluid generator to determine the vertical acceleration imparted to the aircraft by said extendable landing gear strut, and including input means for manually inputting a desired acceleration quantity in accordance with the gross weight of the aircraft and desired takeoff distance, said adjustable energy management control means further being adapted to monitor aircraft performance sensors and utilizing data generated by said sensors in order to control said quantity of compressed fluid generated by said fluid generator.