A method for measuring HVAC efficiency is disclosed which may be used to test various heat transfer or passive elements within a HVAC system to determine whether any element, such as a cooling coil, heating coil, filter or mixer, is operating at an acceptable efficiency when compared to design specifications or previously established standards. The method may also be used to easily determine volumetric flow rate of air through the system at various points.

A method of controlling a vehicle having an active aerodynamic feature includes sensing a static pressure adjacent to the active aerodynamic feature. An estimated aero force from measured pressure is calculated from the sensed static pressure adjacent the aerodynamic feature. The estimated aero force from measured pressure is compared to an estimated aero force from current vehicle operating conditions, to determine a deviation therebetween. A control signal including the deviation is sent to a vehicle control system, so that the vehicle control system may control a system of the vehicle based on the deviation.

A method of controlling a vehicle having an active aerodynamic feature includes sensing a static pressure adjacent to the active aerodynamic feature. An estimated aero force from measured pressure is calculated from the sensed static pressure adjacent the aerodynamic feature. The estimated aero force from measured pressure is compared to an estimated aero force from current vehicle operating conditions, to determine a deviation therebetween. A control signal including the deviation is sent to a vehicle control system, so that the vehicle control system may control a system of the vehicle based on the deviation.

A wind tunnel balance, with a tunnel wall adaptor configured to fasten the wind tunnel balance to a wall of a wind tunnel, an actuator housing connected to the tunnel wall adaptor, a plurality of force sensors arranged between the actuator housing and the tunnel wall adaptor and which are configured to detect forces acting on the actuator housing, a pivot coupling, by means of which an airfoil model of an aircraft can be pivotably coupled to the actuator housing, and a plurality of piezoelectric actuators arranged in the actuator housing and which are configured to controllably deflect an airfoil model mounted on the pivot coupling in three spatial directions.

An in-vehicle apparatus includes a load weight information obtainer, a load information obtainer, an aerodynamic analyzer, a specific power consumption calculator, and a route information retriever. The load weight information obtainer acquires a load weight of a load placed on a roof rail or a roof carrier of the vehicle. The load information obtainer acquires load information including a size and a shape of the load from image data on the load. The aerodynamic analyzer executes an aerodynamic analysis based on the load information. The specific power consumption calculator calculates a specific power consumption based on the load weight and a result of the aerodynamic analysis. The route information retriever retrieves route information including a charging timing in travel from a departure point to a destination based on a current amount of charge and a result of calculating by the specific power consumption calculator.

An in-vehicle apparatus includes a load weight information obtainer, a load information obtainer, an aerodynamic analyzer, a specific power consumption calculator, and a route information retriever. The load weight information obtainer acquires a load weight of a load placed on a roof rail or a roof carrier of the vehicle. The load information obtainer acquires load information including a size and a shape of the load from image data on the load. The aerodynamic analyzer executes an aerodynamic analysis based on the load information. The specific power consumption calculator calculates a specific power consumption based on the load weight and a result of the aerodynamic analysis. The route information retriever retrieves route information including a charging timing in travel from a departure point to a destination based on a current amount of charge and a result of calculating by the specific power consumption calculator.

A wheel bearing assembly is provided. The wheel bearing assembly includes a wheel releasably coupled to a vehicle to perform an aerodynamic testing of the vehicle. The wheel bearing assembly further includes a shaft adaptor coupled between a bearing of the wheel and other components of the vehicle. The shaft adaptor rotates the wheel independent of the control of other components of the vehicle.

A wheel bearing assembly is provided. The wheel bearing assembly includes a wheel releasably coupled to a vehicle to perform an aerodynamic testing of the vehicle. The wheel bearing assembly further includes a shaft adaptor coupled between a bearing of the wheel and other components of the vehicle. The shaft adaptor rotates the wheel independent of the control of other components of the vehicle.

A system and method for sampling a flight envelope of an air vehicle under test. The method includes obtaining engineering models of the vehicle to identify how the vehicle behaves, obtaining empirical models through test data, and obtaining historical models of similar legacy aircraft. The method further includes ensembling the models into an integrated model and assessing the ensemble uncertainty at any particular test point, for a variety of aircraft conditions, to determine model reliability. The method includes determining the optimal order of test points based on local model uncertainty, testing the air vehicle at a point, revising the integrated model with that data and reassessing the uncertainty, and determining if a stop testing condition has been met, in which case the testing series is closed. The last calibrated integrated model could then be used to generate trusted data for any remaining required test using a certification by analysis method.

A system and method for sampling a flight envelope of an air vehicle under test. The method includes obtaining engineering models of the vehicle to identify how the vehicle behaves, obtaining empirical models through test data, and obtaining historical models of similar legacy aircraft. The method further includes ensembling the models into an integrated model and assessing the ensemble uncertainty at any particular test point, for a variety of aircraft conditions, to determine model reliability. The method includes determining the optimal order of test points based on local model uncertainty, testing the air vehicle at a point, revising the integrated model with that data and reassessing the uncertainty, and determining if a stop testing condition has been met, in which case the testing series is closed. The last calibrated integrated model could then be used to generate trusted data for any remaining required test using a certification by analysis method.