An integrated wireless data system and method for avionic performance indication for measuring, monitoring and displaying in-use, real-world engine-out characteristics on a propeller driven aircraft for the purposes of health monitoring, performance optimization, and regulatory compliance is provided. Engine-out characteristics may be measured either at the propeller extension hub mounted between the engine and propeller, on the crankshaft flange, or on the propeller itself, and include, but are not limited to, the engine output torque, thrust, vibration, bending loads and temperature. Data may be transmitted wirelessly to a base unit located inside the cockpit and user selected parameters are updated on a display in real-time. The system may also store all collected data, for later download and analysis. The system may also have a software interface that can be used to download, view and analyze all recorded data, as well as to configure the system settings and alerts.

A method and apparatus for measuring the propulsive power required to overcome drag forces on a vehicle mounted within a wind tunnel. The apparatus includes a running belt platform driven by a dynamometer and supporting the vehicle placed inside a wind tunnel and controlled by a closed-loop servo control system, which maintains the vehicle centered on the running belt under varying operating speeds and headwind conditions. The power dissipated in drag is measured as the power transferred through ground contact with the wheels of the vehicle.

Approaches are provided that evaluate overall engine thrust and potentially other engine operating parameters statically on the ground for an engine. The results of the evaluation are used to produce a correlated analytical model that accurately models engine performance. Once testing on the ground is complete and correlated model determined, the engine is placed aboard an aircraft and tested in flight. Thrust of the engine can be determined at least in part using the correlated model and this determined thrust is compared to the desired thrust.

Disclosed are a method, a device, equipment and a medium for dynamic positioning of a semi-submersible offshore platform. The method includes: acquiring a real-time position of the platform; if the real-time position is different from a preset position, detecting an external force torque by a first torque detector; calculating a first target thrust produced by each of propellers, controlling the propellers to produce forces according to a first target thrust torque, and detecting an actual thrust torque; obtaining a fault condition of each of the propellers if the actual thrust torque is different from the first target thrust torque, indicating that the propellers have faults; recalculating a thrust of each of the propellers, a second target thrust torque, according to the fault condition, the external force torque and the preset formula set; and controlling each of the propellers to generate the thrust according to a corresponding second target thrust torque.

Disclosed is an apparatus for testing a water rocket and a method for use thereof, comprising a load cell assembly, a launcher assembly, a rocket assembly, and a base piston, all situated within a housing. Air and/or water pressurizes the rocket assembly and the launcher assembly, which is released to cause the rocket to exert a propelling force on the rocket. The load cell is adapted to capture and record the thrust of the water rocket. The housing is adapted to retain the released water within the housing. The base piston is adapted to move the launcher assembly out of the way of the releasing water and air, whereby the launcher assembly does not impede the exit of the water or air that could result in inaccurate data.

An apparatus measuring thrust of an aircraft gas turbine engine includes a core shaft connecting a turbine and compressor, a fan and gearbox with a sun gear driven by the core shaft, a plurality of planet gears, an annulus gear mounted in a static structure, and a planet carrier driven by the fan via fan shaft. The apparatus includes a sensor to measure force applied by the annulus gear on the static structure and first and second sensors to measure rotational speed of the core and fan shafts. A processor determines restoring torque on the annulus gear from measurement of force applied by the gear on the static structure, torque applied to the fan by the planet carrier using rotational speeds of core and fan shafts and restoring torque on the annulus gear, and thrust of the fan from torque applied to the fan and the fan's rotational speed.

Disclosed are a method, a device, equipment and a medium for dynamic positioning of a semi-submersible offshore platform. The method includes: acquiring a real-time position of the platform; if the real-time position is different from a preset position, detecting an external force torque by a first torque detector; calculating a first target thrust produced by each of propellers, controlling the propellers to produce forces according to a first target thrust torque, and detecting an actual thrust torque; obtaining a fault condition of each of the propellers if the actual thrust torque is different from the first target thrust torque, indicating that the propellers have faults; recalculating a thrust of each of the propellers, a second target thrust torque, according to the fault condition, the external force torque and the preset formula set; and controlling each of the propellers to generate the thrust according to a corresponding second target thrust torque.

A take-off apparatus and method for unmanned aerial vehicle without landing gear includes an unmanned aerial vehicle, a carrier, a lock/release mechanism, a lift or airspeed sensing module, a signal processing module and a release motion sensing module. The lock/release mechanism locks the unmanned aerial vehicle onto the carrier and controllably releases the unmanned aerial vehicle from the carrier. The lift or airspeed sensing module senses an overall lift or airspeed of the unmanned aerial vehicle. When the lift or speed value of the unmanned aerial vehicle is greater than a predetermined threshold, it drives the lock/release mechanism into an unlocked state so that the unmanned aerial vehicle is released from the carrier and takes off more accurately and successfully.

The invention relates to a drive system for an, in particular electrically driven, aircraft. The drive system is provided with thrust measuring means which measure a currently effective thrust of the thrust generator of the aircraft. The measurement values obtained in this way are supplied to a controller of the drive system, which uses the measured thrust, along with other parameters, to control the drive system such that a selectable parameter, e.g. the thrust or an efficiency of the drive system, can be is optimised.

A method determines a thrust force of an aircraft engine that is attached to an aircraft by a force transferring element having a strain gauge for determining its strain state and a temperature sensor for measuring a surface temperature of the force transferring element adjacent to the strain gauge. The method includes: determining the surface temperature; determining a strain of the force transferring element; determining the strain state of the force transferring element based on the determined strain and compensating for temperature effects by taking into account the surface temperature, the compensation of the temperature effects taking into account both static and transient influences; and calculating the thrust force of the aircraft engine from the determined strain state.