Pilot-oriented information is displayed on the screen of a cathode ray tube by electronically generated symbols superimposed on a simulated or real-world picture. The symbology uses as one datum a fixed airplane symbol and locates therefrom the airplane's degree of pitch, degree of roll, and the horizon. In addition, symbols are provided to indicate the relative position of the airplane with respect to ILS localizer and glide slope signals, pitch and roll commands obtained from an on-board flight director computer, a desired pitch reference, and actual as well as potential flight path angle. Deviation from a preset airspeed and radio or radar altitude are also shown. In all cases, the symbols are constructed by symbol generators from one or more basis rectangles, whose width is determined by a pulse of appropriate length during the CRT's horizontal scanning period, and whose height is determined by a similar pulse during the vertical scanning period. The location of each rectangle is determined by the delay between the start of the vertical or horizontal scanning period, and the start of the vertical or horizontal pulse. Modifications are described for generating rotating symbols. The outputs of the symbol generators are combined as a priority circuit and converted into a composite video signal by a video mixer.
The present invention utilizes a conventional aircraft landing and approach indicator in conjunction with a pilot controllable television camera and supporting aircraft computer for tracking an airdrop target and displaying the locus of payload ground impact points directly on the television image of the terrain being approached by the aircraft. The airdrop information is presented in such a manner which does not distract the pilot from the basic task of flying the aircraft by providing automatic calculation and continuous automatic updating of the airdrop information with respect to meteorological and aircraft flight path characteristics.
Driver-vehicle behavior display apparatus is provided wherein data representing a vehicle's performance capability envelope and a polar plot of forces imposed by a driver on a vehicle are superimposed in real time upon video information representing a driver's view of roadway being traversed. In addition, bar graph information corresponding to accelerator position and brake pressure may also be provided and superimposed upon such video information. The resulting video signal may be viewed directly, transmitted to a remote viewing station, or recorded in a conventional VCR.
Apparatus for providing an integrated display of flight instrument parameters on the screen of a single cathode ray tube is presented. The synthetically generated symbology is equivalent to that typically provided by ten conventional electromechanical instruments including an attitude-director indicator, horizontal situation indicator, pressure altimeter, radio altimeter, vertical speed indicator, radio magnetic indicator, Mach airspeed indicator, autopilot-flight director mode annunciator, load factor indicator and true air-speed indicator.
A cockpit-mounted cathode ray tube presents to the pilot a visual equivalent of the approach/landing during obscure visibility of an aircraft which contains a miniature illuminated runway that is being "approached" by a video camera that reproduces the position and position changes of the aircraft with respect to the real runway. Ground-based instrument landing system elements are used to air derive radio information to secure the operation of the device.
Flight path angle is displayed relative to the aircraft reference indicator in a unique display and aircraft control system particularly useful during approach operations. Flight path angle is computed as a function of vertical velocity of the aircraft and air speed. Angle of attack is displayed as an angle relative to the flight path angle and is derived by computing the difference between pitch and flight path angle. Thrust command is displayed vertically relative to the aircraft reference indicator while heading command is displayed laterally with respect to the aircraft reference indicator. In the approach mode, a pitch command computer produces a pitch command signal for controlling an aircraft's pitch to maintain a desired angle of attack, and hence, a desired air speed; a thrust command computer produces a thrust command signal for controlling the flight path angle to maintain an aircraft on a desired glide path for landing; and a desired heading command computer produces a heading command signal for controlling the aircraft's heading to maintain a desired course or heading depending upon mode selection. In addition in the approach mode, the unique display and control system provides the capability of substituting the flight path angle with a ground path angle input. This offers the advantage that the projection of the aircraft symbol relative to the horizon is really where the aircraft is going relative to the ground. A runway symbol is displayed in the approach mode only and is driven by the output of a navigation receiver.
