Systems, computer-implemented methods and/or computer program products that facilitate measuring weight and balance and optimizing center of gravity are provided. In one embodiment, a system 100 utilizes a processor 106 that executes computer implemented components stored in a memory 104. A compression component 108 calculates compression of landing gear struts based on height above ground of an aircraft. A gravity component 110 determines center of gravity based on differential compression of the landing gear struts. An optimization component 112 automatically optimizes the center of gravity to a rear limit of a center of gravity margin.

An aircraft operation method of providing weight and center of gravity information is used to dispatch the aircraft. The aircraft has telescoping landing gear struts and strut seals that interfere with the free movement of the strut. An event trigger signaling departure is detected from aircraft operations at a loading area. Internal strut pressure is measured and recorded upon detection for a period of time as the aircraft moves away. The recorded pressure measurements are transmitted to a first off-aircraft computer, which determines the total weight and center of gravity of the aircraft and provides the information to an operator of the aircraft.

An aircraft operation method of providing weight and center of gravity information is used to dispatch the aircraft. The aircraft has telescoping landing gear struts and strut seals that interfere with the free movement of the strut. An event trigger signaling departure is detected from aircraft operations at a loading area. Internal strut pressure is measured and recorded upon detection for a period of time as the aircraft moves away. The recorded pressure measurements are transmitted to a first off-aircraft computer, which determines the total weight and center of gravity of the aircraft and provides the information to an operator of the aircraft.

A system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes a sensor configured to detect weight data corresponding to a weight of a user of the ejection system. The system further includes a controller coupled to the ejection system and to the sensor and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the weight data.

A tower stores unmanned aircraft and shipping containers inside. The unmanned aircraft are controlled by the tower's integrated computer to enable immediate distribution of the shipping containers upon a customer request. Upon a customer request, the tower autonomously dispatches the unmanned aircraft stored inside to rapidly fly out of the tower to deliver a shipping container directly to a specified location outside. Once dispatched by the tower's computer system, the unmanned aircraft autonomously fly from storage in the tower through the tower's interior space and exit the tower through internal shafts that lead to an opening in its exterior walls to deliver a shipping container cheaper and faster than traditional means.

A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow a regulated aircraft to operate at increased maximum weight limitations, through the statistical identification of non-recognized weight errors being allowed in today's aircraft weight determination methods, with the recovery and utilization of the non-recognized weight errors to increase weight limitations through a Regulatory Authority finding of an Equivalent Level of Safety. A system for use in measuring aircraft weight and center of gravity, providing a method to reveal non-recognized weight errors. Sensors are attached to the landing gear struts, so to periodically and randomly measure and monitor aircraft weight and center of gravity.

A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow a regulated aircraft to operate at increased maximum weight limitations, through the statistical identification of non-recognized weight errors being allowed in today's aircraft weight determination methods, with the recovery and utilization of the non-recognized weight errors to increase weight limitations through a Regulatory Authority finding of an Equivalent Level of Safety. A system for use in measuring aircraft weight and center of gravity, providing a method to reveal non-recognized weight errors. Sensors are attached to the landing gear struts, so to periodically and randomly measure and monitor aircraft weight and center of gravity.

The invention(s) include embodiments and applications of: a system for package handling, the system including: a flying vehicle comprising a nose portion; a storage region of the flying vehicle; a landing support subsystem coupled to the flying vehicle; one or more thrust generating devices coupled to the flying vehicle 110; a package conveying subsystem configured to interface with the flying vehicle; and a weight and balance detection subsystem comprising a set of sensors coupled to at least one of the flying vehicle and the package conveying subsystem. The system can execute operation modes, associated with loading and unloading of multiple packages, redistributing multiple packages according to weight, and delivering one or more packages to receiving sites.

A system to estimate the good distribution of loading onboard an aircraft capable of carrying out a target mission. The system includes at least one operability index determination module, a module for verifying whether the distribution of loading onboard the aircraft is considered to be a good distribution by comparing the operability index of the target mission with a predetermined operability index threshold. The determination of the operability index makes it possible to know whether the aircraft can carry out a target mission in good conditions.

A system to estimate the good distribution of loading onboard an aircraft capable of carrying out a target mission. The system includes at least one operability index determination module, a module for verifying whether the distribution of loading onboard the aircraft is considered to be a good distribution by comparing the operability index of the target mission with a predetermined operability index threshold. The determination of the operability index makes it possible to know whether the aircraft can carry out a target mission in good conditions.