A weight estimation system for estimating weight of an aerospace vehicle while grounded, the weight estimation system comprising a measurement subsystem including at least one sensor configured to measure a physical property in an interface that interfaces at least one of a fuselage and a wing with an undercarriage of said aerospace vehicle, in at least one area exhibiting a measurable change in geometry that is at least partly due to said weight, said measurement subsystem configured to produce measured data indicative of said weight of said aerospace vehicle; and a processor for receiving at least part of said measured data, said processor configured to estimate said weight, by relating said measured data with predetermined physical-property-to-weight correspondence data associated with said aerospace vehicle.

Disclosed herein is a flying taxi for facilitating the transportation of payloads, in accordance with some embodiments. Accordingly, the flying taxi may include a pod, a processing device, a presentation device, and an aerial vehicle. Further, the pod may be configured to receive a payload. Further, the pod may include a weight sensor disposed on the pod. Further, the weight sensor may be configured to generate a weight data corresponding to a weight of the payload. Further, the processing device may be communicatively coupled with the weight sensor. Further, the processing device may be configured for analyzing the weight data. Further, the processing device may be configured for generating a notification based on the analyzing. Further, the presentation device may be communicatively coupled with the processing device. Further, the aerial vehicle may be detachably couplable with the pod using a coupling mechanism.

During crop dusting application, there is no accurate method to detect the quantity of dry product onboard. This can lead to improper application rates and waste of product. The dry quantity gauge system solves this problem. The system detects strain on select structures of the aircraft during flight. The system monitors other in-flight aircraft characteristics that induce errors on the payload weight estimation. The software filter changes the influence of collected measurements based on the sensor data. The result is a stable and reliable payload estimate for the pilot at any given time during flight even during product application. Since the pilot will always know the amount of product onboard, it builds pilot's intuition, reduces workload, and ensures a more accurate application for the client. There are no similar systems to date that weigh the aircraft payload in flight.

An example method for in-flight determination of a gross weight of an aircraft includes causing an aircraft to perform a first flight operation defined by a first airspeed that is substantially constant and a descent rate that is substantially constant, determining the first airspeed and a first thrust that caused the aircraft to perform the first flight operation, the first thrust being substantially constant during the first flight operation, causing the aircraft to perform a second flight operation defined by a second airspeed that is substantially constant and a descent rate that is substantially constant, determining the second airspeed and a second thrust that caused the aircraft to perform the second flight operation, the second thrust being substantially constant during the second flight operation, and using the first thrust, the second thrust, the first airspeed, and the second airspeed to determine the gross weight of the aircraft.

An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

The present disclosure relates to systems and methods for automatically re-routing unmanned aerial vehicles (UAVs). In one implementation, a system for automatically re-routing a UAV includes at least one processor configured to: retrieve a plurality of requests to deposit currency using the UAV, generate a first route including at least two of the requests such that an associated expected total amount of currency is less than a depository threshold; transmit the first route to the UAV; receive, from the UAV, an indication that an amount of currency collected at a location is greater than an amount of currency included in the request associated with the location; revise the expected total amount accordingly; when the revised expected total amount exceeds the depository threshold, generate a second route having an associated expected total amount below the depository threshold; and transmit the second route to the UAV to override the first route.

A vibratory weight-on-wheels (WOW) sensing system is provided for use with aircraft landing gear and a wheel coupled to the aircraft landing gear. The WOW sensing system includes a vibration sensor disposed proximate to the wheel and configured to sense vibratory characteristics of a component of the aircraft landing gear and to issue a sensing reflective signal and a processing unit disposed in signal communication with the vibration sensor such that the processing unit is receptive of the sensing reflective signal. The processing unit is configured to analyze the sensing reflective signal to thereby identify that a landing condition is in effect.

An aircraft cargo handling system with augmented weight sensing capability is disclosed. In embodiments, the aircraft cargo handling system includes a loadmaster control station including a controller with a user interface communicatively coupled to the controller. The user interface is configured to receive user-input weight data for one or more cargo units. The aircraft cargo handling system further includes one or more sensors configured to detect weight data for the cargo units or one or more carriers for the cargo units. The sensors may be coupled to respective transmitters that are configured to transmit the detected weight data to a data gateway device that is communicatively coupled to the controller. The controller is configured to compare the user-input weight data to the detected weight data and generate an alert when the difference between the user-input weight data and the detected weight data is greater than a threshold weight difference.

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.