Abstract: A horizontal speed indicator for a rotary-wing aircraft includes first and second sensors for determining, respectively, the heading and the horizontal speed of the aircraft. The indicator processes the signals delivered by the first and second sensors, and displays the processed signals on a screen, which includes a compass rose which can rotate when the aircraft alters its heading, and a scale which represents the horizontal speed of the aircraft. The scale includes cross wires and concentric circles, and is capable of moving with respect to the compass rose.

Abstract: The present invention provides a device for indicating an operating point of an aircraft comprising a sensor to measure air speed and a sensor to measure vertical acceleration. The device also comprises a processor in communicative connection with each of the airspeed sensor and the vertical acceleration sensor. The processor is also in communicative connection with a display. The display presents an operating envelope diagram of the aircraft. The display also displays the current operating point of the aircraft relative to the operating envelope diagram. The present invention also provides a method for indicating an operating point of an aircraft in which the operating envelope diagram and the measured operating point of the aircraft are displayed upon the same display.

Abstract: A direction gauge enables easy recognition of an indicated direction by constructing an arrow-shaped indication segment made up of an unshared segment and a pair of adjacent shared segments. The combination of shared and unshared segments forms an indication segment having a sharp outward-directed tip and a blunt base. The sharp outward directed tip is the outer end of the unshared segment. The blunt base is a combination of the inner end of the unshared segment together with the two adjacent shared segments. The indication segment provides a good indication of direction even if the indicia on the remainder of the display cannot be seen because of darkness.

Abstract: A sea marker for emergency flights of ship-based planes onto a ship is disclosed which comprises a float, a tube containing a pyrotechnical charge and also a percussion igniter. The tube consists of a material which does not burn away, and is provided with a light charge consisting of about 30 to 60% by weight of sodium nitrate, about 3 to 18% by weight of polyolefin resin and about 30 to 60% by weight of magnesium.

Abstract: Masthead device for sailboats that indicates apparent wind direction composed of a rotating wind vane and a protractor arm encompassing multiple reference marks. These marks can be adjusted with greater compass accuracy to allow several settings in each quadrant creating a series of reference points enabling one to more accurately determine the apparent wind angle from a center point, and thus optimize sail trim, heading and boat speed.

Abstract: Disclosed is a method of visualizing laminar to turbulent boundary layer transition, shock location, and laminar separation bubbles around a test surface. A liquid crystal coating is formulated using an unencapsulated liquid crystal operable in a temperature bandwidth compatible with the temperature environment around the test surface. The liquid crystal coating is applied to the test surface, which is preferably pre-treated by painting with a flat black paint to achieve a deep matte coating, after which the surface is subjected to a liquid or gas flow. Color change in the liquid crystal coating is produced in response to differences in relative shear stress within the boundary layer around the test surface.

Abstract: An easily manipulable hand operable device for use in visualization of relative orientations for steering operations to a final azimuth orientation in homing of a fluid craft having an axis of symmetry and guidance system in making an approach in the homing. Three coaxial indicator discs are used.

Abstract: A compass having a color coded compass card for enhanced reading of the compass. The compass card is divided into four quadrants each of which is further subdivided into equal sectors differently colored within each quadrant; the color sequence of the sectors within each quadrant is repeated in each quadrant. The color sequencing enables an efficient method of navigating a sailing dinghy around an olympic course.

Abstract: This Takeoff and Abort Instrument system, mounted on the pilot's instrument panel, will indicate to the pilot, as soon as the throttles are advance to the takeoff position and brakes are released if all engines are producing the designed takeoff thrust. During the takeoff run an ABORT indication will be visible to the pilot anytime the net aircraft linear acceleration degrades below that amount required to make a safe takeoff. This instrument assembly is comprised of two major components: A. A flexible transparent tube formed into a right triangle with the shortest leg being mounted vertically on the instrument face; this leg becomes a sight gauge up which a colored non-freezing liquid rises directly in proportion to the aircraft's linear acceleration. The longest leg connects the base of the sight gauge to a reservoir located forward of and level with the base of the sight gauge.

Abstract: A Mach/airspeed indicator instrument has two pressure capsules each of which have a finger projecting from one face which is displaced by deflection of the capsule. Each finger is coupled to a respective arm that extends radially from respective shafts, so that displacement of a finger causes rotation of the respective shaft about its axis. Rotation of one shaft causes rotation of a Mach scale plate whereas rotation of the other shaft causes rotation of a pointer around an airspeed scale. The rear end of the Mach shaft is rotatably mounted at one end of a radially-extending lever that is in turn pivotally mounted close to its other end. The airspeed shaft is coupled with the Mach shaft by means of a link that extends between a plate fixed to the airspeed shaft and the lever. Rotation of the airspeed shaft thereby causes rotation of the lever and lateral displacement the Mach shaft about a pivot point at the end of the finger.

Abstract: This invention sets forth a wind tracking device particularly useful on sailing vessels for determining the best sailing direction relative to the wind. The reference card is provided with color panels which cooperate with lines on the dome to indicate best direction. Further, the card has circular lines about the axis which cooperate with a dot on the axis of the dome to indicate a 360.degree. level condition around a horizontal plane.

Abstract: A glide path instrument for an aircraft to display to a pilot that the aircraft is descending on a predetermined inclined glide path. The instrument includes a rectangular casing mountable in stationary position in the aircraft and carrying a freely pivotable frame which has sighting elements at opposite ends spaced different vertical distances from the plane of the frame. The frame carries a pendulum-like structure including depending legs supporting free swinging weights. The sighting elements align in a single sight plane with a runway reference point when the aircraft is at the predetermined glide angle. A lamp in the casing illuminates the sighting elements.

Abstract: An indicator instrument for aircraft may be operated in either of two modes. In an HSI mode, first indicia reflect heading, second indicia reflect selected course, and third indicia reflect course deviation. In a CDI mode, the first indicia reflect selected course, the second indicia assume a fixed position, and the third indicia reflect course deviation. A compass validity signal automatically triggers the changeover from HSI mode to CDI mode.

Abstract: A direction indicating device has an azimuth card which is positioned upon a compass. The card is provided with a number of indicia marks corresponding to specific geographic locations. An adjustable straight-line cursor is positioned to be aligned with an indicia marking corresponding to the geographic location at which the device is being used and with the pivot point of the compass magnetic needle such that when the compass magnetic needle is pointing to magnetic North, the straight-line cursor will indicate the true direction of the predetermined locale from that specific geographic location.

Abstract: A flight director type of aircraft control or guidance display and mechanism for pilot reference which provides a composite integrated display of roll, pitch and heading with a sensing relationship approximating what the pilot sees through the windshield in the real world environment. The visual cue relationship is retained when the display is viewed during flight in obscure visibility with resulting elimination of vertigo and disorientation. The display is remote from its sensors of aircraft control and guidance and may be positioned in a head erect location in the instrument panel. The electro-mechanical display of roll, pitch and heading embodies a roll symbol which is positioned in front of a rotating dial displaying heading that enables control coordination during turns. An associated horizon bar remains parallel to the display base while rising and falling past the roll symbol to indicate a glide or climb respectively.

Abstract: An omnidirectional airspeed indicator has a plate with a window and a fixed horizontal bar across the window. A drum with graduations and numerical indications of speed and forward and rearward direction and with a safe flight envelope indication and safe engagement and disengagement indication rotates within the window so that the horizontal bar points to the forward and rearward speeds. A vertical bar moves between a drum and the window to indicate lateral speeds. Vectoral sum of speed is presented in digits at the top of the window. A rearward flight warning light is mounted beneath the window and a high speed warning flag appears in the window when maximum safe speeds are approached. Triangles at the lateral edges of the window cause the vertical bar to appear as a broken line when maximum lateral indications are approached or exceeded. Rate of climb is indicated by a pointer beside the window. A selector switch lights air density in the digital display.

Abstract: 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 provides the pilot with an integrated display of substantially all aircraft attitude and flight path command and control parameters including attitude and magnetic heading, barometric and radiometric attitude, vertical spread, critical take-off speeds, true airspeed and Mach airspeed, flight path angle, flight director path control commands, and mode annunciation for the flight director and automatic pilot systems.

Abstract: An indicator for indicating the optimum angular position of a sail which is adapted to be rotated in various positions relative to a wind, and wherein the position of the sail may be represented by a polar curve comprising a laminar zone, a drop-off zone, a transition zone and a checking zone. The indicator comprises display means for displaying the optimum angular position of the sail relative to the wind as well as evaluation means for determining the position of the sail which corresponds to value between the end of the laminar zone and the beginning of the checking zone as a function of the direction of the wind. Means for indicating the direction of the wind to the evaluation means and driving means for driving the display means to display the optimum sail position are also included.

Abstract: An aircraft-speed indicating instrument has an index which is movable against a scale to provide a reading of airspeed, and a digital indicator which is selectively operable to provide a digital reading of either Mach number or the airspeed. The index and the digital indicator are driven by respective control systems supplied with a multiplexed electrical signal containing information representative of both Mach number and airspeed. Each control system includes gating means which is operable to pass only those parts of the multiplexed signal necessary for the associated control means to provde the desired reading.

Abstract: A directional gyro for aircraft having on its stationary face plate, color zones referable separately to portions of the 360.degree. movable directional scale; each color zone indicating a particular entry procedure (direct, parallel, or tear drop) for the preselected radial.

Abstract: A method and a device for facilitating the determination of wind direction and the position of a sailing vessel on a racing course. One and the same geographical bearing determined by the wind direction can be read on both tacks. The same graduation number may be watched on both tacks and this number refers to the wind direction.

Abstract: This invention is a display system to assist a human operator in manually ntrolling a ship. This system may be operated in a conventional autopilot mode, where the system controls the ship completely; in a conventional hand electric mode, where the helsman manually controls the ship unaided by the system; and in a third mode, where the autopilot provides the helmsman all the information needed to steer the ship properly while the helmsman maintains direct manual control over the ship. In addition to the usual displays such as a rudder angle indicator and a compass repeater, the system provides a display which shows both the actual angle of the helm wheel and optimum angle for the helm wheel calculated by the autopilot.

Abstract: A command bar gives pitch and roll commands to an aircraft pilot. The command bar is carried on a magnet assembly which is supported to pivot on a pair of perpendicular edges that correspond to the pitch and roll axes. A permanent bar magnet included in the assembly has its opposite ends received within bobbins on which coils are wound. The coils are arranged in a plurality of separate tiers located above and below the ends of the magnet. Fields are generated by the coils to selectively deflect the magnet in a manner to effect pitch and roll movement of the command bar.

Abstract: A navigational instrument known as a buoy reminder which includes a base adapted to support an indicator for lateral reciprocal movement thereon. The reminder has two depictions of nun and can buoys which are in a specific relation. The reminder also comprises a means to exhibit a nun buoy at a first site when it is in a certain position and a can buoy at a second site when it is in a second position.

Abstract: An omnidirectional cockpit display has perpendicular bars independently moving across a plate for providing indications of speed in lateral, forward and rearward directions. A zero point is centered between lateral edges of the plate and is displaced vertically from the center of the plate to provide greater speed indications in a forward direction than in a rearward direction. A safe flight envelope is indicated on the plate, extending around the zero point in lateral and rearward directions and extending toward the edges of the plate in the forward flight direction. Indicator scales are mounted along edges of the plate, and pointers move along the scales to indicate vector sum of component speeds, and density altitude. Other scales and pointers indicate ground speed in orthogonal directions, while the crossbars indicate air speed in those directions. Other peripheral scales and pointers indicate directional control position, collective thrust control position, rate of climb and rate of closure.

Abstract: Power required curves for ratios of helicopter weight to air density ratio form a background over which move perpendicular bars representing air speed and engine torque. The intersection of the relatively movable bars indicates which power required curve the helicopter is operating on. An area to the right and above that curve represents power margin available for maneuvering. A knob positions a mask over a portion of the background to indicate the actual maximum power limitation of the helicopter. A maximum power setting is varied according to ambient pressure and temperature. A minimum speed warning is produced by comparing air speed and engine torque. A rapid descent automatically raises the minimum speed warning.

Abstract: An altimeter has a pointer which rotates clockwise once round a dial for each thousand unit (feet or meters) increase in altitude, the zero of the dial being in the nine o'clock position.Two digital displays are situated one above and one below the horizontal through the dial zero. When the pointer lies in the upper segment of the dial a reading is shown on the upper display and when the pointer lies in the lower segment of the dial a reading is shown on the lower display. When the pointer is in the region of the zero position (for example within 100 feet of the zero position) a reading is shown on both displays. The upper display then reads thousands corresponding to a pointer position above zero and the lower display reads thousands corresponding to a pointer position below zero (whether the pointer is above or below zero).

Abstract: A command driving mechanism for command bars which are rotatable about the longitudinal axis of and transversely displaceable with respect to the horizontal reference line of a flight director indicator includes a command plate, the plane of which is parallel to the front face of the indicator. The perpendicular axis of the command plate is coaxial with the longitudinal axis of the indicator and rotatable thereon in accordance with roll commands. Command bar struts are pivotally supported at diametrically opposed peripheral portions of the command plate and connected through a wire bail which is driven by a helical cam in accordance with pitch commands.

Abstract: An altimeter has a rotatably-mounted index that is driven to rotate through one complete revolution around a scale for each change of 1,000 feet in altitude sensed by two evacuated manometric capsules the number of revolutions of the index is indicated by numerical markings visible through an arcuate window which breaks into the scale against a `zero` arrowhead at the top-center of the scale. The markings are distributed around the opaque circumferential-margin of a transparent disc that is mounted coaxially with the index and is driven in the counter direction to the index through step-down gearing. Successive ones of the numerical markings are rotated to the zero arrowhead to indicate the number of units of 1,000 feet appropriate to the altitude measurement, upon successive revolutions of the index.

Abstract: An indicator for a flight director instrument particularly for use in rotary wing aircraft includes a command cue having a shape resembling that of an associated aircraft control element or stick and includes cooperating indicia representative of the direction to move the control stick so as to center the cue and thereby satisfy the command. This novel indicator arrangement engenders an instinctive pilot response to move the associated control stick to satisfy the flight director command.