Abstract: A test bench for generating aerodynamic loads on an actuator to be tested includes a force actuator configured to generate at least one dynamic load, the test bench being configured to transmit the dynamic load produced by the force actuator to the actuator to be tested, and a controller for controlling the dynamic load generated by the force actuator depending on a pressure, measured by a pressure sensor, inside one of the chambers of the force actuator.

Abstract: A device for simulating an ingestion of chunks of ice by an engine, including: a main tank forming a cavity for a fuel, and connected to an inlet of the engine by a pipe; an injection system including an injection member arranged in the pipe; a secondary tank forming a cavity for a fuel, which tank is connected to the injection system by a selector member; and a reservoir connected firstly to a reserve of water and secondly to the injection system via the selector member. The selector member is configured to place the injection system selectively in communication with the secondary tank or with the reservoir to inject a determined quantity of water into the engine.

Abstract: A system and methods for reducing pressure in an enclosed volume is disclosed. A first quantity of steam is inserted into a condensation chamber, and the first quantity of steam is substantially condensed in the condensation chamber. A first quantity of air is extracted from an enclosed volume into the condensation chamber.

Abstract: An engine simulator for wind tunnel models exhibits a turbine with an inlet for a pressurized fluid and an outlet for a relieved fluid, a flow-type body arranged downstream from the turbine, a jacket that at least partially envelops the flow-type body with the formation of a gap, and at least two electrodes. A downstream end of the flow-type body is provided with a heater coating comprised of a matrix material that contains a conductivity additive and is connected with the electrodes for applying an electrical voltage. This may make it possible to prevent ice formation on the trailing edge of the flow-type body.

Abstract: Blow-out testing devices which include a box-like housing defining two contiguous inner chambers communicating directly with one another through an inner aperture which is closable by applying a blow-out panel thereupon are provided. In such devices at least one of the two chambers is provided with a hermetically closable door. Both chambers are pressurized and sealed. Opening the door, an instant pressure drop is caused in one of the two chambers. The pressure within the other chamber causes the panel to break. Methods for blow-out testing are also provided.

Abstract: A method and apparatus for generating a flow of heated air in an airfoil model of an inlet of an aircraft engine. Heated air is sent into a duct system associated with the airfoil model of the inlet of the aircraft engine. The heated air is circulated within the airfoil model of the inlet of the aircraft engine using the duct system in a manner that simulates air flowing in the inlet of the aircraft engine.

Abstract: A method and apparatus for an icing simulation system. The icing simulation system comprises a wind tunnel, a nozzle system, and a controller. The nozzle system is configured to spray drops of water within the wind tunnel. The controller is configured to control a number of properties of the water in the nozzle system such that the nozzle system sprays the drops of the water with different sizes for a desired type of icing condition.

Abstract: A liquid based ice protection test system for testing an aircraft part having a first heating element comprises a tub configured for retaining a low temperature bath. The system also includes a first support member for suspending the aircraft part in the tub and a first temperature sensing device for sensing temperatures from one or more locations of a skin of the aircraft part.

Abstract: A method and apparatus for an icing simulation system. The icing simulation system comprises a wind tunnel, a nozzle system, and a controller. The nozzle system is configured to spray drops of water within the wind tunnel. The controller is configured to control a number of properties of the water in the nozzle system such that the nozzle system sprays the drops of the water with different sizes for a desired type of icing condition.

Abstract: Methods and systems for optimizing the design of aerodynamic surfaces are provided. They include in the design process of an aerodynamic surface of a body which moves through a flow field, the following: preparation of a CFD simulation of said body; resolution of the CFD calculation for specific conditions of the flow field and for obtaining flow lines of the flow on said surface; calculation of at least one geometrical variable of the surface, such as, for example, the normal curvature, according to the direction of said flow lines; and simultaneous visualization of the surface of said body and of at least one geometric variable. Additionally, at least one variable of the aerodynamic flow, such as, for example, a pressure gradient, may be calculated and visualized.

Abstract: A wind tunnel test model (1) includes a half model portion (3) that simulates a fuselage portion of an airframe with a single wing and a supporting apparatus (5) that supports the half model portion rotatably about a central axis. The supporting apparatus has a horizontal cross-sectional shape that is approximately the same as or similar to that of the fuselage portion (7) and extends rearward of the fuselage portion, includes, toward its rear end, a fixing portion (11) that fixes the half model portion to a wind tunnel test apparatus side, and includes, within a housing, a torsional rigidity imparting unit.

Abstract: An aircraft model for testing in a wind tunnel of width W including a fuselage, a truncated wing whose length L1 is less than the length L of a full scaled wing and additional components in the rear of the aircraft as, in particular, a horizontal tail plane, that produces the same downwash that arrives to the additional components as in a full scaled model. The shape of the truncated wing may be designed for having a similar lift distribution to the lift distribution of a full scaled wing along at least the maximum length L2 in the Y-axis of any component in the rear of the aircraft. The invention also relates to a method for designing the truncated wing.

Abstract: Blow-out testing devices which include a box-like housing defining two contiguous inner chambers communicating directly with one another through an inner aperture which is closable by applying a blow-out panel thereupon are provided. In such devices at least one of the two chambers is provided with a hermetically closable door. Both chambers are pressurized and sealed. Opening the door, an instant pressure drop is caused in one of the two chambers. The pressure within the other chamber causes the panel to break. Methods for blow-out testing are also provided.

Abstract: An apparatus for pivotally fastening an aerodynamic surface. The apparatus includes a bearing block. A clamping block is connected to the bearing block and includes at least two elongate holes. A pivotally mounted strip member is coupled to the aerodynamic surface and to the clamping block. At least one fastening device is insertable into each of the at least two elongate holes for locking the clamping block relative to the bearing block. The aerodynamic surface is lockable in at least one angular position.

Abstract: A device and method for simulating rotation of a wheel on a vehicle having a rotatable wheel rotation sensor. A motor is coupled to a rotatable portion of the rotation sensor, and is operated to rotate the rotatable portion of the rotation sensor according to a pulse train simulating a wheel skid.

Abstract: The present invention relates to a turbofan propulsion simulator means, in particular for a turbofan of an aircraft or spacecraft, wherein the turbofan propulsion simulator means comprises a modular configuration, wherein the turbofan propulsion simulator means comprises a module, wherein the module is a turbine means to drive the turbofan of the turbofan propulsion simulator means, wherein the turbine means can be coupled with at least two fan means, characterized in that, the at least two fan means to be connected with the turbofan propulsion simulator means comprises almost or essentially the same mass and/or almost or essentially the same barycentre.

Abstract: In-flight testing methods and kits for in-flight testing of proposed aerodynamic structures are disclosed. The methods and kits involve a testing station carried on a pre-existing fully engineered and tested host aircraft. Interchangeable but differently configured aerodynamic structures may be carried upon the host aircraft, and existing systems of the host aircraft may be utilized to conduct the testing, avoiding time and cost associated with constructing fully operational demonstrator aircraft for testing purposes.

Abstract: A test facility provides high temperature, high pressure and high mass flow fluid to a test object to form a relatively large thermal gradient on the object. Energy in the fluid is recuperated to drive system components, such as a heat exchanger and a turbocharger compressor. A test chamber housing the test object can be arranged to conform to a contour of the test object. A control system permits independent variation of pressure, temperature, cooling fluid and fluid velocity, as well as mechanical loading on the test object. Noncontact, optical inspection measurement techniques can be employed to measure test chamber and/or test object parameters. The test object can be configured to direct cooling airflow to permit various temperature or pressure gradients to be implemented. The test facility is relatively inexpensive to operate and provides a significant cost advantage over testing conducted in a full gas turbine engine.

Abstract: A method of testing a steerable wheel assembly incorporating a shock absorber strut, comprising providing a combined linear and rotary actuator, engaging a lower end of the assembly with the actuator so that the line of linear action of the actuator is aligned with the line of compression of the strut, operating the actuator to compress the strut, and operating the actuator in a rotary sense to apply a steering torque to the assembly. A linear actuator is engageable with the assembly via a load coupling to load the strut. The load coupling comprising a first part on the actuator adapted to engage a second part on the assembly, the two parts being adapted to provide a self-aligning action as the actuator engages the assembly. Preferably, one of the two parts comprises a tapered recess formation, and the other two parts comprises a tapered projecting formation engageable in the tapered recess formation.

Abstract: A liquid based ice protection test method tests an aircraft part that includes at least a first heating element mounted on an inside surface of an aircraft skin. The method includes bringing the aircraft skin into contact with a low temperature bath and taking one or more temperature readings of the aircraft skin. A liquid based deicing test system includes a container that holds a low temperature bath, a fixture to suspend the aircraft part within the container, and a temperature sensing device for reading temperatures on an outside surface of the aircraft part. A liquid based ice protection test method includes sealing off ends of an aircraft part, attaching at least one temperature sensing device on the aircraft part and at least partially submerging it in a low temperature bath, and obtaining temperature information from the temperature sensing device.

Abstract: In-flight testing methods and kits for in-flight testing of proposed aerodynamic structures are disclosed. The methods and kits involve a testing station carried on a pre-existing fully engineered and tested host aircraft. Interchangeable but differently configured aerodynamic structures may be carried upon the host aircraft, and existing systems of the host aircraft may be utilized to conduct the testing, avoiding time and cost associated with constructing fully operational demonstrator aircraft for testing purposes.

Abstract: A method of and apparatus for determining and controlling the inertial attitude of a spinning artificial satellite without using a suite of inertial gyroscopes. The method and apparatus operate by tracking three astronomical objects near the Earth's ecliptic pole and the satellite's and/or star tracker's spin axis and processing the track information.

Abstract: A method for modeling the acoustic signature produced by an aircraft of interest flying at a particular supersonic Mach number/altitude operating point of interest. The method includes operating a sub-scale aircraft that is a sub-scale version of the aircraft of interest at a supersonic Mach number and at an altitude that are respectively different from the Mach number and the altitude associated with the operating point of interest. The Mach number and altitude at which the sub-scale aircraft is operated is selected such that peak overpressure generated by the sub-scale aircraft and time to rise to peak overpressure are the same as peak overpressure and time to rise to peak overpressure caused by operating the aircraft of interest at the operating point of interest.

Abstract: A method of testing a steerable wheel assembly incorporating a shock absorber strut, comprising providing a combined linear and rotary actuator, engaging a lower end of the assembly with the actuator so that the line of linear action of the actuator is aligned with the line of compression of the strut, operating the actuator to compress the strut, and operating the actuator in a rotary sense to apply a steering torque to the assembly. A linear actuator is engageable with the assembly via a load coupling to load the strut. The load coupling comprising a first part on the actuator adapted to engage a second part on the assembly, the two parts being adapted to provide a self-aligning action as the actuator engages the assembly. Preferably, one of the two parts comprises a tapered recess formation, and the other two parts comprises a tapered projecting formation engageable in the tapered recess formation.

Abstract: The invention relates to methods of measuring an aircraft under simulated flight-loads while the aircraft is not in-flight. While the aircraft is under the simulated flight-loads, positions of one or more portions of the aircraft may be measured in order to determine how the aircraft is performing under such loads. The aircraft may be readjusted and/or redesigned based on the measurements in order to reduce drag on the aircraft.