Abstract: Described are systems and methods for a nacelle auxiliary landing gear to be utilized as an alternative landing gear in the event of main landing gear non-deployment. The systems described herein include a nacelle auxiliary landing gear that includes a nacelle auxiliary landing gear strut and a nacelle auxiliary landing gear wheel, coupled to the nacelle auxiliary landing gear strut, wherein at least a first portion of the nacelle auxiliary landing gear wheel is configured to be disposed outside of a nacelle of an aircraft propulsor. The nacelle auxiliary landing gear strut is coupled to a core engine. Techniques for use of the nacelle auxiliary landing gear are also described herein.

Abstract: Described are systems and methods for a nacelle auxiliary landing gear to be utilized as an alternative landing gear in the event of main landing gear non-deployment. The systems described herein include a nacelle auxiliary landing gear that includes a nacelle auxiliary landing gear strut and a nacelle auxiliary landing gear wheel, coupled to the nacelle auxiliary landing gear strut, wherein at least a first portion of the nacelle auxiliary landing gear wheel is configured to be disposed outside of a nacelle of an aircraft propulsor. The nacelle auxiliary landing gear strut is coupled to a core engine. Techniques for use of the nacelle auxiliary landing gear are also described herein.

Abstract: There is provided an aircraft tipping alarm system having a nose landing gear (NLG) shock strut containing hydraulic fluid and having an aperture. The system further has an elongated pressure chamber assembly configured to engage to the aperture. The elongated pressure chamber assembly has an elongated pressure chamber containing hydraulic fluid and having a pressure sensor device, a first check valve configured to restrict hydraulic fluid flow only into the NLG shock strut, a second check valve configured to restrict hydraulic fluid flow only into the elongated pressure chamber, and a reduced diameter breakable neck section. A potential aircraft tipping back position is indicated when a reduction of pressure of the hydraulic fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to a pressure reduction threshold.

Abstract: There is provided an aircraft tipping alarm system having a nose landing gear (NLG) shock strut containing hydraulic fluid and having an aperture. The system further has an elongated pressure chamber assembly configured to engage to the aperture. The elongated pressure chamber assembly has an elongated pressure chamber containing hydraulic fluid and having a pressure sensor device, a first check valve configured to restrict hydraulic fluid flow only into the NLG shock strut, a second check valve configured to restrict hydraulic fluid flow only into the elongated pressure chamber, and a reduced diameter breakable neck section. A potential aircraft tipping back position is indicated when a reduction of pressure of the hydraulic fluid in the NLG shock strut, sensed via the pressure sensor device, is greater than or equal to a pressure reduction threshold.

Abstract: A method of increasing the friction between a tire of a vehicle and an icy surface includes dispensing a cooling agent such that at least a portion of the dispensed cooling agent is distributed between the tire of the vehicle and the icy surface.

Abstract: A tip alarm system for an aircraft having a nose landing gear (NLG) includes a sensor having first and second parts respectively disposed on first and second portions of the NLG that are respectively fixed to the aircraft and moveable relative to the fixed portion and operable to detect the position of the first and second portions relative to each other and to produce a tip alarm signal when the first and second NLG portions are disposed at a selected position relative to each other corresponding to an imminent aircraft tipping condition and thereby prevent the aircraft from tipping back onto the ground due to improper loading of the aircraft.

Abstract: A tilarm system for an aircraft having a nose landing gear (NLG) includes a sensor having first and second parts respectively disposed on first and second portions of the NLG that are respectively fixed to the aircraft and moveable relative to the fixed portion and operable to detect the position of the first and second portions relative to each other and to produce a tip alarm signal when the first and second NLG portions are disposed at a selected position relative to each other corresponding to an imminent aircraft tipping condition and thereby prevent the aircraft from tipping back onto the ground due to improper loading of the aircraft.

Abstract: A load measuring system specially adapted for installation on the support legs of existing storage vessels. The load measuring system includes an attachment plate that is fastened to each support leg of the vessel, a support plate that is mounted on anchor bolts projecting upwardly from the supporting surface, and a load cell positioned between the attachment plate and the support plate. The support plate is supported by nuts threaded on respective anchor bolts. The nuts are rotated to raise the lower ends of the support legs above the supporting surface, thereby transferring the portion of the vessel's weight carried by the support leg to the load measuring system. The space between the support plate and the supporting surface is then filled with a supporting material such as concrete.

Abstract: A load cell adapted to be positioned between a foundation and each of several support members for a storage vessel. The load cell includes a circular flex plate having a pair of concentric cylindrical members of different diameters secured to opposite surfaces. A mounting pad adapted to be fastened to the foundation is secured to one of the cylindrical members. A mounting plate is secured to the other cylindrical member. The mounting plate has either a single threaded bore or a threaded stud positioned at the common axis of the cylindrical members for securing the mounting plate to a vessel support member. A strain sensor mounted on the flex plate measures the load-induced deflection of the flex plate.