Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27). The rear end of the fuselage supports an engine (21) provided with a propeller (22). The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.

The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27). The rear end of the fuselage supports an engine (21) provided with a propeller (22). The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.

A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.

A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.

A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

An aircraft having a systems cabinet positioned in an avionics bay to the rear of a landing gear compartment and connected to the fuselage by at least one lower connecting system. The systems cabinet and/or the lower connecting system comprises at least one longitudinal beam, which has a front end connected by a front connection to a wall separating the avionics bay and the landing gear compartment, the front connection comprising a sliding connection sliding in a direction substantially parallel to the longitudinal axis.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.