Disclosed is an apparatus for testing a water rocket and a method for use thereof, the apparatus comprising a housing, a load cell assembly, a launcher assembly, a rocket assembly, and a base piston. The load cell assembly, the launcher assembly, the rocket assembly, and base piston all situated within the housing. A hose running from the exterior of the housing to the launcher assembly and/or the rocket assembly, whereby water or air may be supplied to the launcher assembly or the rocket assembly. The supply of air and/or water pressurizes the rocket assembly and the launcher assembly, which may then be released to cause the rocket to exert a force in a direction opposite to the direction of the release of water and air. 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.

A method for measuring a thrust margin of a turbomachine, in which data are acquired including the thrust margin which is determined as a function of a specified thrust and a measured thrust, the measured thrust being determined on a measuring bench which includes a bench equipment and on which the turbomachine is, wherein a time evolution of the thrust margin is modelled by at least one linear or affine function which is calculated for at least one determined time interval of the thrust margin, at least one bias of the bench equipment is calculated relative to at least one linear or affine function having been calculated, the thrust margin is corrected by subtracting from it at least one bias of the bench equipment in at least one determined time interval.

The instant invention describes devices and methods of measuring the differential air pressure at numerous representative points across the surface of the sail or sails and providing visual feedback of areas of ideal laminar flow and areas of less than optimal airflow with a calculation of thrust and providing an indication the maximal differential airflow and thrust. The invention utilizes an array of sensors that detect minute variations in barometric pressure and other data on each side of the sail surface. These sensors are connected together to form a network or net across the sail. This connection can be physical, using wires, or it may be wireless, using for example, but certainly not being limited to, Bluetooth LE 5.0 or other wireless topologies or technologies. This can be extended over multiple sails and monitor not only the sail but the interaction of the sails. Finally it can utilize a combination of wired and wireless connections to fit individual situations and can couple with existing terrestrial and satellite ship networks.

Systems and methods for operating a rotorcraft engine are described herein. Measurements indicative of at least one of current temperature and current pressure at an inlet of the engine are obtained from at least one sensor while the rotorcraft is in flight. At least one current inlet loss is determined from the measurements. Current available engine power of the rotorcraft engine is determined based on the at least one current inlet losses. A visual indication of the current available engine power is produced via a flight display.

A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from a central axis extending through the propeller and a propeller drive shaft, is provided. The method includes obtaining measurements representative of strain in the propeller drive shaft using multiple primary strain sensors, each primary strain sensor providing respective measurements representative of strain. The primary strain sensors are located around a circumference of the drive shaft of the propeller, and each strain sensor is located such that it crosses a plane defined by the radial direction of a blade and the central axis, the plane being bounded by the central axis. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.

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.

An electrical signal is received via a boom where a rotor is attached to the boom and the received electrical signal is received while the rotor outputs a thrust. It is decided whether to decrease the thrust which is output by the rotor, including by analyzing the received electrical signal. In response to deciding to decrease the thrust which is output by the rotor, the thrust which is output by the rotor is decreased.

An aircraft powerplant and a method for measuring thrust are described herein. A gas turbine engine has a turbine section for extracting energy from combustion gases and has a shaft mounted to the turbine section for converting the energy into rotary motion. A load cell is coupled to an end of the shaft and positioned to rotate with the shaft. The load cell is configured for generating a measurement indicative of propeller thrust. A propeller is coupled to the load cell and is configured for converting the rotary motion from the shaft and the load cell into the propeller thrust. The propeller thrust can be measured from the load cell as the propeller rotates.

An electrical signal is received via a boom where a rotor is attached to the boom and the received electrical signal is received while the rotor outputs a thrust. It is decided whether to decrease the thrust which is output by the rotor, including by analyzing the received electrical signal. In response to deciding to decrease the thrust which is output by the rotor, the thrust which is output by the rotor is decreased.

A system for total pressure measurement of a propulsive stream through a turbine engine, the system incorporates a track circumferentially mounted on a fan exhaust nozzle proximate a trailing edge. A carriage is mounted in the track and adapted for translation through a range of azimuthal angles relative to an engine centerline. A pressure measurement rake extends from the carriage and has a probe mount protruding radially inward into a fan flow duct with a plurality of pressure probes mounted to a leading edge of the probe mount.