A display generation system that is able to generate display signals for an underlay image with at least one embedded safety pattern and display images for an overlay image. The display generation system and method are able to determine whether there are any anomalies or graphical errors when an overlay display generated by the system or generated by some other system is displayed simultaneously with the underlay image with the embedded safety pattern. The display generation system uses the embedded safety pattern to detect the occurrence of anomalies in the simultaneous display and uses information from its own generated overlay image to detect graphical errors in the simultaneous display. Flight display systems for aircraft can use the display generation system and method of the present invention to display an underlay image depicting geographical scenery in the vicinity of the aircraft while on the ground, during takeoff or in flight. The underlay image is displayed simultaneously with an overlay image depicting standard graphics of a flight display system.

Display generation system

A method of measuring aircraft fuel quantity and density in a fuel container using an ultrasonic transducer; a stillwell liquid fuel; a computer control, an indicator and an altitude sensor. The computer control includes a central processing unit connected to each of the ultrasonic transducers. The altitude sensor is connected to the central processing unit. The indicator means is connected to the central processing unit. The stillwell is supported by the container. Each ultrasonic transducer is supported within the stillwell by the container. The liquid fuel is supported within the container. An ultrasonic signal is transmitted from the transducer within the stillwell. The reflected ulrasonic signal is received by the transducer within the stillwell. The round-trip time period from sending to reciving the signal is measured. The quantity of fuel in the container is determined from the round-trip time period and stored data on the container volume in the central processing unit.

Ultrasonic fuel quantity gauging system

A universal sensor interface system that utilizes a common hardware and software interface to drive many types of sensors. A variety of stimulation signals are generated that are transmitted to a plurality of sensors. The stimulation signals cause the sensors to generate response signals in the form of parametric measurements, which are then converted into a common format. The sensor response signals are processed and output as usable inputs to a data consuming apparatus. A method of automatically determining the sensor configuration in an aircraft sensor system is also provided. During operation the host computer system or digital signal processor is programmed to analyze sensor response signals to detect sensor faults, help predict sensor failures, and determine if there has been a sensor error. The universal sensor interface system is also capable of notifying a system operator of wiring problems with a particular sensor or if a particular sensor is malfunctioning.

Universal sensor interface system and method

A method and system for measuring the mass quantity and volume of fuel in an aircraft fuel tank is disclosed. A pressure assembly (124) is disposed proximate the lowest portion of each fuel tank on an aircraft (60), with respect to a wing tank (100). The pressure sensor assembly includes a temperature probe (126) having a plurality of temperature sensors (128) mounted therein at spaced apart elevations within the fuel tank. Also included is an attitude sensor (150) in which are provided a roll sensor (156) and a pitch sensor (160) for respectively determining the roll and pitch angles of the fuel surface with respect to a vertical reference axis on the aircraft. The reference axis is aligned with an acceleration-sensitive axis of an accelerometer (164), which is operative to determine the acceleration acting upon fuel within the wing tank, and using the roll and pitch angles, the acceleration normal to the upper surface of the fuel. Wing bending sensors (82) are installed in each wing to determine the deflection of the wing as a result of loading the wing tanks with fuel and as a result of in-flight aerodynamic forces on the wing. The signals from each of these sensors are input to a microprocessor (178), which determines the height of fuel in each tank, corrects for variations in density due to temperature stratification, determines the volume and mass of fuel as a function of fuel height, correcting for the attitude of the fuel tank and for acceleration applied to the mass of fuel during measurement of its pressure at the bottom of each fuel tank.

System and method for measuring liquid mass quantity

A supersonic aircraft comprises a wing, a fuselage, a plurality of fuel tanks contained within the wing and/or fuselage, and a fuel transfer system communicatively coupled to the plurality of fuel tanks and capable of transferring fuel among the plurality of fuel tanks. The aircraft further comprises at least one sensor capable of indicating a flight parameter and a controller. The controller is coupled to the one or more sensors and to the fuel transfer system. The controller can transfer fuel among the plurality of fuel tanks and adjust the aircraft center of gravity to reduce trim drag and increase aircraft range.

Aircraft with active center of gravity control

A true mass fuel gaging system for aircraft utilizing multiplexing of tank unit measurements in or adjacent a fuel tank for improved accuracy and fault isolation. The system provides dual equipment channels for redundancy throughout all data processing portions of the system and also uses extensive built-in testing (BIT) routines so that upon detection of a fault an alternative channel can be switched into use. Detected fault locations are displayed in the cockpit with the fuel quantity displays. The system also provides displays of center of gravity measurements derived from fuel mass and location.

Multiplexed junction probe for fuel gaging system and system containing same

A standardized, modular, fuel quantity gaging system suitable for use with aircraft having a plurality of fuel tanks. The system utilizes a standard electronic module, preferably located on the front spar of the center wing box, to house a redundant, centralized, microprocessor-based electronic assembly. This assembly processes the tank-generated fuel quantity signals and produces a digital data stream which is distributed to display units in the cockpit and at the refueling control panel. The digital signals are transmitted over two 2-wire data busses from the standard electronic module to the cockpit and to the refueling panel. One of these buses is active, the other being held in standby, for use as needed. The two busses are part of separate data processing channels extending between the fuel quantity signal multiplexers in the standard electronic module and the indicators in the cockpit and at the refueling panel. The indicators are basically display only units which receive, decode and display the digital fuel quantity information as it appears on the active data bus. This arrangement permits a high degree of interchangeable modularity among its various components, leading to minimized maintenance and spares provisioning cost. Components can be replaced without any need for recalibration or adjustment of any kind. The system includes equipment for detecting and indicating faults, thus providing improved reliability.

Martin Horowitz

Papers

Multiplexed junction probe for fuel gaging system and system containing same

Multiplexed true mass gaging system

Sonde a jonction multiplexee pour systeme de jaugeage de carburant, et systeme le contenant