A non-nulling gas velocity measurement apparatus performs a non-nulling measurement of gas velocity parameters and includes: a non-nulling pitot probe; gas valves in fluid communication with a different entrant aperture of the non-nulling pitot probe via a different pressure channel; receives stagnant gas from the respective entrant aperture; receives a reference gas; receives a valve control signal; and produces a valve-selected gas based on the valve control signal, the valve-selected gas consisting essentially of the reference gas or the stagnant gas; and a plurality of differential pressure transducers, such that each differential pressure transducer: is separately and independently in fluid communication with a different gas valve, and that gas valve communicates the valve-selected gas to the differential pressure transducer; receives the valve-selected gas from the gas valve; and produces a differential pressure signal from comparison of the pressure of the valve-selected gas to a reference gas pressure.

A non-nulling gas velocity measurement apparatus performs a non-nulling measurement of gas velocity parameters and includes: a non-nulling pitot probe; gas valves in fluid communication with a different entrant aperture of the non-nulling pitot probe via a different pressure channel; receives stagnant gas from the respective entrant aperture; receives a reference gas; receives a valve control signal; and produces a valve-selected gas based on the valve control signal, the valve-selected gas consisting essentially of the reference gas or the stagnant gas; and a plurality of differential pressure transducers, such that each differential pressure transducer: is separately and independently in fluid communication with a different gas valve, and that gas valve communicates the valve-selected gas to the differential pressure transducer; receives the valve-selected gas from the gas valve; and produces a differential pressure signal from comparison of the pressure of the valve-selected gas to a reference gas pressure.

Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.

Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.

A dynamic pressure probe for a sensor device can determine the relative speed of an object and a medium surrounding that object, in particular for gathering flight data on a flying object. The dynamic pressure probe includes an outer body with a wall in which an inflow opening is formed and which encloses an inner space, as well as an inner body which is arranged at least partially in the inner space and which encloses a measuring space as a constituent part of the inner space. Medium is able to flow through the inflow opening and is able to be dammed in the measuring space. The inner body is able to be acted upon with a protective fluid, in particular a gas, on a side remote from the measuring space and includes passages through which protective fluid is able to flow into the measuring space.

An air data probe system can include a pitot static system configured to sense at least one total pressure value of a flow at one or more locations, at least one static pressure value of the flow at the one or more locations, and, directly or indirectly, at least one differential static pressure value of the flow at the one or more locations. The system can include an angle of slip (AOS) module configured to determine a local angle of slip (LAOS) value at each location based on the at least one total pressure value at each location, the at least one static pressure value at each location, and the at least one differential static pressure value at each location.

An air data probe system can include a pitot static system configured to sense at least one total pressure value of a flow at one or more locations, at least one static pressure value of the flow at the one or more locations, and, directly or indirectly, at least one differential static pressure value of the flow at the one or more locations. The system can include an angle of slip (AOS) module configured to determine a local angle of slip (LAOS) value at each location based on the at least one total pressure value at each location, the at least one static pressure value at each location, and the at least one differential static pressure value at each location.

A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality of first operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality of first operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

Systems/methods for measuring airstream parameters. The methods comprise: measuring a humidity and temperature by sensors of airstream sensor device(s) arranged symmetrically within a single cross-sectional plane of an air flow conveyance structure of an HVAC system; measuring, by absolute pressure sensor(s), a barometric pressure of an atmosphere outside of the air flow conveyance structure; receiving, by a transmitter, humidity measurement values and temperature measurement values from the sensors and barometric pressure value(s) from the absolute pressure sensor(s); computing a velocity weighted temperature value for the airstream based on the temperature measurement values; using the humidity measurement values, the velocity weighted temperature value, and the barometric pressure value to determine a psychrometric property associated with the airstream; and causing operations of the HVAC system, a building automation system or an application controller to be controlled based on the determined psychrometric property.