US3691520A - Maneuvering command display for aircraft - Google Patents

Maneuvering command display for aircraft Download PDF

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Publication number
US3691520A
US3691520A US140340A US3691520DA US3691520A US 3691520 A US3691520 A US 3691520A US 140340 A US140340 A US 140340A US 3691520D A US3691520D A US 3691520DA US 3691520 A US3691520 A US 3691520A
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bars
display
bar
vertical axis
aircraft
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US140340A
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English (en)
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Knut Lennart Nordstrom
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Definitions

  • This invention relates to apparatus for displaying maneuvering commands to the pilot of an aircraft, and is concerned more specifically with maneuvering command display means that can be readily perceived and interpreted with the use of only peripheral vision.
  • two cylinders have counter-directed helical patterns, and one is mounted concentrically within the other and is visible therethrough. Upon rotation of the respective cylinders to signify a required maneuver, their helical patterns cooperate to define a square pattern which appears to move up, down, right or left, or in vector directions therebetween, to signify the direction of maneuver required.
  • a further object of this invention is to provide maneuver command display means of the character described whereby commands can be given for composite maneuvers, such as simultaneous change of vertical and lateral direction, by means of a pattern of command symbols that is simple enough to be readily perceptible with peripheral vision.
  • FIG. 1 is a perspective view of a mechanically operating maneuvering command display device mounted in the cockpit of an airplane, as seen by the pilot of the airplane;
  • FIG. 2 is a view generally similar to FIG. I but illustrating a modifiedembodiment of the invention comprising an electronically operated maneuvering command display device wherein maneuvering command signals are displayed on a transparent screen in the pilots normal forward field of vision;
  • FIGS. 3a-3e illustrate various maneuver command display patterns obtainable with the device illustrated in FIG. 1;
  • FIGS. 4a-4e are views similar to FIGS. 3a-3e, respectively, but showing the corresponding displays on a modified embodiment of the device;
  • FIGS. 5a-5e are likewise views similar to FIGS. 3a-3e, respectively, but showing the displays as they would appear on the embodiment of the device illustrated in FIG. 2;
  • FIG. 6 is a schematic block diagram of the units in a maneuver command signal system comprising a display device like that illustrated in FIG. 1;
  • FIG. 7 is a view generally similar to FIG. 6 but illustrating a display device like that of FIG. 2 together with its associated equipment;
  • FIG. 8 is an enlarged front view of the command signal display device shown in FIG. 1;
  • FIG. 9 is a perspective view of the display device shown in FIG. 8, illustrating more or less diagrammatically the drive means and motion transmitting means by which its display symbols are actuated;
  • FIGS. 10 and 11 illustrate displays of maneuver command and flight situation information on a form of the device shown in FIG. 2.
  • the numeral designates generally an aircraft instrument panel above which there is a windshield 6 through which the pilot can look forwardly out of the aircraft.
  • the maneuvering command display device of this invention which is designated generally by 7, is mounted in such a location as to be in or closely adjacent to the pilots normal forward line of vision, so that the display that the device provides is within the pilots peripheral vision both when he is looking forwardly through the windshield and when he is looking at instruments on the panel.
  • the mechanically actuated display device of the embodiment of the invention illustrated in FIG. 1 is mounted at the top center of the instrument panel.
  • the electronic embodiment of the display device illustrated in FIG. 2 comprises a transparent projection screen 12' that projects up from the center of the instrument panel so as to be in the pilots range of vision through the windshield.
  • the primary flight instruments most frequently referred to, and which are designated by 8, are preferably arranged adjacent to the face of the display device 7. As illustrated, a radar screen or attitude indicator is mounted in the location 9 just below the display device.
  • the display device is connected with the output of a computer that receives inputs from various flight and navigation devices 11, such as gyros for measuring the attitude angles of the aircraft, airspeed, altitude and angle of attack sensors, radio navigation systems, instrument landing systems and the like.
  • the inputs to the computer thus correspond in part to a predetermined situation to which the aircraft is to be maneuvered, and in part to the currently existing situation of the aircraft, and the output of the computer that is fed to the display device comprises signals that correspond to the computed maneuvering of the aircraft required to bring it from its existing situation to the predetermined situation.
  • the computer output signals are translated by the display device into a display pattern of bars that signify to the pilot by their arrangement and movement the maneuvers that he must accomplish to bring the aircraft to the predetermined situation and to maintain it there.
  • the pilot sees before him a screen or background 12 having a shape in outline that is symmetrical to a vertical axis 14 and preferably also to a horizontal axis 15, and on which moveable bars 16 and 17 are superimposed.
  • the screen is black and the bars are white, for maximum contrast and to facilitate observation with peripheral vision.
  • Each of the bars 16 and 17 is mounted for pivotal motion about one of its ends, to swing across the face of the screen, and the pivoted ends of the bars are at or near the intersection of the axes l4 and 15.
  • the two bars 16 have their pivot axes on the horizontal axis 15, and they extend symmetrically to opposite sides of the vertical axis 14.
  • the pivot axis of the bar 17 is on the vertical axis, and it extends generally upwardly from the horizontal axis.
  • the positions of the two bars 16 denote pitching (climb-dive) maneuvers, while the positions of the bar 17 denote lateral (left-right) maneuvers.
  • FIGS. 3a-3e depict various maneuvering commands signified by the bars 16 and 17 in the device illustrated in FIG. 1, wherein the pivot axes of the bars 16 are spaced to opposite sides of the vertical axis, and the generally upright bar 17 has its pivot axis on the intersection of the axes 14 and 15.
  • the bars 16 are aligned with one another on the horizontal axis 15, and the upright bar 17 is aligned with the vertical axis 14, all as illustrated in FIGS. 3a and 4a, so that the pattern defined by the bars has the form of an inverted T.
  • FIGS. 3b and 4b illustrate a command for an upward movement (e.g., from level flight to climb, or from dive toward level flight)
  • FIGS. 3c and 4c illustrate displays that command a downward movement (e.g., from level flight to dive or from climb toward level flight).
  • the position of the bar 17 in FIGS. 3b, 3c, 4b and 4c, aligned with the vertical axis denotes that the heading is satisfactory, that is, that no lateral change in flight direction is to be made.
  • FIGS. 3d and 4d signify that pitching motion is satisfactory but that a turn to the left is to be made.
  • FIGS. 3e and 4e illustrate patterns which command composite maneuvers, signifying, in each case, that the aircraft is to be given an upward change of pitch direction and is to be turned to the right.
  • the bold and simple patterns produced by the display device are readily observed with peripheral vision and can be interpreted without the need for closer inspection of the display. Furthermore, the swinging movements of the bars as they assume various patterns draw attention to the need for maneuvering control motions and facilitate perception of the patterns. Since the patterns formed by the bars are well defined, the axes l4 and 15 need not actually be delineated on the panel or screen 12 that the bars overlie. Note that all displays are self-explanatory if the pilot is merely instructed to fly toward the needles.
  • the mechanism by which the bars are actuated comprises a moving coil 19 that is connected with the bars 16 through a known type of wishbone and bell crank linkage 20 by which it actuates them in unison; and a moving coil 21 that is connected through a parallelogram linkage 22 with the bar 17.
  • the moving coils 19 and 21 are of course connected with the computer to receive output signals from it.
  • the mechanical maneuvering command display apparatus can be arranged to provide attitude information in addition to command signals, by means of a horizon bar 23.
  • the horizon bar In straight and level flight the horizon bar is on the horizontal axis 15, and, in the manner of the classical artificial horizon, it remains parallel with the actual horizon, tilting relative to the axis as the airplane rolls and moving bodily up and down relative to said axis with changes in the pitch attitude of the aircraft.
  • the tilting axis of the horizon bar 23 is of course at its center and remains on the vertical axis 14 in all positions of its vertical displacement.
  • Tilting motion of the horizon bar is effected by means of a rotor coil 25 which is connected with the center of the bar through a shaft 26 and which can of course be slaved to an attitude gyro (not shown).
  • Vertical motion of the horizon bar is effected by means of another rotor coil 27, suitably linked to the shaft 26 and which can likewise be slaved to the attitude gyro.
  • the altitude display symbol can comprise a pair of vertical bars 29, spaced a short distance to each side of the vertical axis 14 and which move vertically, in unison, during changes in altitude within the critical range.
  • the altitude display bars are actuated by a rotor coil 30 which is connected with them through suitable motion transmission means 31 and which can be slaved to an altitude sensor (not'shown) that can be either an aneroid or (preferably) a radar altimeter.
  • an altitude sensor not'shown
  • the altitude display bars will be in an inoperative position.
  • the altitude bars will signify the prevailing altitude by their vertical position.
  • the altitude bars can function according to any desired scheme of movement that is reasonably self-explanatory. For example, they can be concealed at a level beneath the visible part of the background screen 12 when altitude of the aircraft exceeds the critical value, and within the critical range they can signify the altitude of the aircraft by the distance H between their bottoms and the horizontal axis 15. As an aid to interpretation of the altitude display, the bars can be so dimensioned that their size represents some significant unit on the altitude display scale, as for example each bar can have a length that corresponds to 200 ft. on its altitude scale.
  • the bars 16' and 17 comprising the display symbols are delineated by light projected onto the transparent screen 12 and generated electronically.
  • various inputs are fed to a computer 10.
  • the output side of the computer is connected with a maneuvering command symbol generator 33, which in turn controls a cathode ray tube 34.
  • the command display symbols appear on the screen of the cathode ray tube, and are projected onto the transparent display screen 12' by means of a mirror 35 and collimating optics 36.
  • the bars 16' and 17' are discontinuous, that is, each has the appearance of a line of dashes 38.
  • the maneuvering command display patterns will then appear as shown in FIGS. 5a-5e, which respectively denote the same maneuver commands as FIGS. 3a-3e and 4a-4e.
  • speed commands can be incorporated in the maneuvering command display pattern by providing for movement of the clashes that comprise the direction command bars 16' and 17'.
  • the dashes defining the bars can be caused to move along them in directions towards their pivot ends (i.e., convergently along the several bars), thereby creating an impression that the pattern is moving forward, and giving the pilot the feeling that he is falling behind the pattern so that his more or less automatic response will be to increase his velocity.
  • the dashes that define the several bars are caused to move in the direction away from the pivoted ends of the bars, creating the impression that the pattern is expanding or coming nearer.
  • the dashes When forward velocity is correct for the predetermined situation, the dashes will of course remain stationary along the bars that they define, giving the pilot the feeling that he is maintaining a desired fixed distance from the pattern.
  • the magnitude of a required speed change can be denoted by the rate of movement of the dashes along the bars.
  • FIGS. 10 and 11 illustrate supplemental modifications that can be made to the embodiment of the invention illustrated in FIGS. 2 and 7, whereby quantitative information concerning the prevailing flight situation can be displayed as a supplement to the maneuvering command display.
  • FIG. 10 illustrates a supplemental situation display for the navigation phase of a flight.
  • the horizontal axis 15 of the display is fixed in relation to the wings of the aircraft, as is the vertical axis 14.
  • a heading scale 39 is generated and displayed above the heading command bar 17', along a line which remains parallel to the horizon, and the heading along that scale is designated by a pointer 41 that remains on a line normal to the horizontal scale and through the intersection of the axes 14 and 15.
  • An altitude scale 42 is displayed to the right of the maneuvering command symbol, along a line which remains in true vertical.
  • the prevailing altitude is designated by a pointer 43 adjacent to the altitude scale, on a true horizontal line through the intersection of the reference axes 14 and 15.
  • the flight path angle is read by reference to the point 45 at which the reference axes l4 and intersect, which point is identifiable not only by reference to the bars 16' and 17' but also by reason of the fact that it is defined by perpendiculars to the heading scale and altitude scale lines through the pointers 41 and 43.
  • the flight path angle value lines 44 remain truly horizontal.
  • FIG. 1 1 illustrates a flight situation display mode that is particularly suitable for the landing approach phase of a flight.
  • the reference axes l4 and 15 are fixed with respect to the ground, so that the horizontal axis 15 remains in true horizontal.
  • the true horizon is indicated on the display by a generated line 47 that coincides with the actual horizon 48 as seen in the pilots field of view, as illustrated in FIG. 2.
  • the heading scale 39 is in this case delineated along the generated horizon line 47.
  • the generated horizon line also serves as an index cooperating with an altitude scale 42 to the right of the command display, to provide an indication of altitude. in this case the flight path angle scale is omitted.
  • this invention provides a display by which maneuvering commands are so presented to the pilot of an aircraft that he can readily perceive them with only peripheral visibn, are denoted by maneuvering command symbols which are so simple as to be almost self-explanatory, so that the pilot can follow them almost automatically, and can be accompanied by a simple display of the existing flight situation.
  • B. means delineating a pair of straight bars, each having an end on said horizontal axis and adjacent to said vertical axis, said bars being swingable in unison about their said ends between a position in which the bars are aligned with one another along the horizontal axis to signify satisfactory vertical movement and positions in which the bars are symmetrically oblique to the horizontal axis to signify required changes in vertical movement in the direction in which the bars are inclined and of a magnitude corresponding to the amount of their inclination;
  • C. means defining a third straight bar having one of its ends on said vertical axis and adjacent to the horizontal axis, said third bar being swingable about its said end between a position aligned with the vertical axis, signifying a satisfactory heading
  • said display field means comprising a panel having I a dark substantially flat surface
  • each of said bars comprising a rigid element of light color mounted in front of said surface to swing thereacross.
  • said display field means comprising a transparent projection screen
  • each of said bars comprising means for generating and projecting onto said screen a row of luminous dashes.
  • F. means for causing the dashes of the rows that define said bars to move lengthwise therealong in a direction corresponding to the sign of a required change in forward velocity and at a rate corresponding to the magnitude of such required change.
  • a display device by which maneuvering commands are displayed to a pilot of an aircraft, in following which he brings the aircraft to a predetermined situation, and which display device is of the type having a defined display screen, means defining generally upright bar-like indicator means having one end that remains on a vertical axis of symmetry on said screen and which swings about its said end to denote required changes in heading by its inclination to said vertical axis of symmetry, and other bar-like indicator means swingable up and down to denote required changes in vertical flight path, said display device being characterized by:
  • said upright bar-like indicator means having its said one end substantially at a midpoint on the screen and extending generally upwardly therefrom;
  • said other bar-like indicator means comprising a pair of generally horizontal bar-like indicator elements
  • said bar-like indicator elements being swingable in unison about their said ends, symmetrically to said vertical axis of symmetry, between a position of horizontal alignment signifying no required change in vertical flight path and positions in which they are inclined to said horizontal line and signify a required change in vertical flight path in the direction of their inclination.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Traffic Control Systems (AREA)
  • Devices For Indicating Variable Information By Combining Individual Elements (AREA)
  • Instrument Panels (AREA)
  • Navigation (AREA)
US140340A 1970-05-11 1971-05-05 Maneuvering command display for aircraft Expired - Lifetime US3691520A (en)

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SE06389/70A SE335248B (de) 1970-05-11 1970-05-11

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US3691520A true US3691520A (en) 1972-09-12

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US (1) US3691520A (de)
AT (1) AT319056B (de)
BE (1) BE766877A (de)
CH (1) CH522206A (de)
DE (1) DE2122830C3 (de)
FR (1) FR2097776A5 (de)
GB (1) GB1347030A (de)
SE (1) SE335248B (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158885A (en) * 1977-11-09 1979-06-19 The Boeing Company Guidance-light display apparatus and method for in-flight link-up of two aircraft
US4368517A (en) * 1978-03-16 1983-01-11 Bunker Ramo Corporation Aircraft landing display system
US4484191A (en) * 1982-06-14 1984-11-20 Vavra George S Tactile signaling systems for aircraft
US4825194A (en) * 1987-05-27 1989-04-25 Honeywell Inc. Single cue flight director indicator
DE4109016A1 (de) * 1991-03-20 1992-09-24 Dornier Luftfahrt Anzeigeinstrument fuer luftfahrzeuge zur darstellung der fluglage, insbesondere der roll- und nicklage bzw. des flugbahnwinkels
US5382954A (en) * 1993-05-27 1995-01-17 Honeywell Inc. Resolution advisory display instrument for TCAS guidance
FR2733597A1 (fr) * 1995-04-28 1996-10-31 Smiths Industries Plc Instrument de bord destine a controler la vitesse de tangage d'un avion lors du decollage
US20010031640A1 (en) * 2000-03-13 2001-10-18 Michael Waller Access to information networks by mobile devices

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1526396A (en) * 1974-10-03 1978-09-27 Smiths Industries Ltd Display systems
US6405975B1 (en) * 1995-12-19 2002-06-18 The Boeing Company Airplane ground maneuvering camera system
DE29721708U1 (de) * 1997-12-09 1998-01-29 Handeck Claus G Führerstand für Land-, Luft-, Wasser- oder Raumfahrzeuge

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2613350A (en) * 1948-03-16 1952-10-07 Sperry Corp Flight indicating system for dirigible craft

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2613350A (en) * 1948-03-16 1952-10-07 Sperry Corp Flight indicating system for dirigible craft

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158885A (en) * 1977-11-09 1979-06-19 The Boeing Company Guidance-light display apparatus and method for in-flight link-up of two aircraft
US4368517A (en) * 1978-03-16 1983-01-11 Bunker Ramo Corporation Aircraft landing display system
US4484191A (en) * 1982-06-14 1984-11-20 Vavra George S Tactile signaling systems for aircraft
US4825194A (en) * 1987-05-27 1989-04-25 Honeywell Inc. Single cue flight director indicator
DE4109016A1 (de) * 1991-03-20 1992-09-24 Dornier Luftfahrt Anzeigeinstrument fuer luftfahrzeuge zur darstellung der fluglage, insbesondere der roll- und nicklage bzw. des flugbahnwinkels
US5382954A (en) * 1993-05-27 1995-01-17 Honeywell Inc. Resolution advisory display instrument for TCAS guidance
FR2733597A1 (fr) * 1995-04-28 1996-10-31 Smiths Industries Plc Instrument de bord destine a controler la vitesse de tangage d'un avion lors du decollage
US20010031640A1 (en) * 2000-03-13 2001-10-18 Michael Waller Access to information networks by mobile devices

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Publication number Publication date
DE2122830A1 (de) 1971-11-25
GB1347030A (en) 1974-02-13
AT319056B (de) 1974-12-10
CH522206A (de) 1972-06-15
FR2097776A5 (de) 1972-03-03
BE766877A (fr) 1971-10-01
DE2122830C3 (de) 1974-02-07
DE2122830B2 (de) 1973-07-05
SE335248B (de) 1971-05-17

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