US3716696A - Projectile stream display apparatus - Google Patents

Projectile stream display apparatus Download PDF

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Publication number
US3716696A
US3716696A US00069536A US3716696DA US3716696A US 3716696 A US3716696 A US 3716696A US 00069536 A US00069536 A US 00069536A US 3716696D A US3716696D A US 3716696DA US 3716696 A US3716696 A US 3716696A
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vectors
aircraft
computer
signals
projectiles
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English (en)
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A Hayes
R Schultz
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Northrop Grumman Innovation Systems LLC
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Honeywell Inc
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Assigned to ALLIANT TECHSYSTEMS INC. reassignment ALLIANT TECHSYSTEMS INC. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: HONEYWELL INC. A CORP. OF DELAWARE
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/26—Teaching or practice apparatus for gun-aiming or gun-laying
    • F41G3/2616—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device
    • F41G3/2622—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device for simulating the firing of a gun or the trajectory of a projectile
    • F41G3/2644—Displaying the trajectory or the impact point of a simulated projectile in the gunner's sight
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/04—Aiming or laying means for dispersing fire from a battery ; for controlling spread of shots; for coordinating fire from spaced weapons
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/26—Teaching or practice apparatus for gun-aiming or gun-laying
    • F41G3/2616—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device
    • F41G3/2694—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device for simulating a target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G9/00—Systems for controlling missiles or projectiles, not provided for elsewhere
    • F41G9/002—Systems for controlling missiles or projectiles, not provided for elsewhere for guiding a craft to a correct firing position

Definitions

  • ABSTRACT [22] Fil d; S t, 4, 1970 Digital computer apparatus and computer controlled process for displaying the locus of the present posi- [21] Appl' 69536 tions of a plurality of projectiles, if discharged sequentially from a freely moving vehicle at known intervals V 52 us. Cl. ..235/6l.5 E beginning at a predetermined time in the Past, as Seen [51] Int. Cl.
  • FIG. 9 be 9:] FIG. IO $52 INVENTORS ARTHUR E HAYES ROBERT 1.. SCH Lrz ATTORNEY PATENTED 31975 3 7 i 6 696 shim 70F 9 FIG. I I
  • This invention relates to the field of visual display apparatus, and more particularly to apparatus for displaying to the pilot of a fighter aircraft what would be the apparent locus of the present positions of a plurality of projectiles if they had been fired at known recent intervals beginning at a predetermined time in the past.
  • the display may be projected on a combining glass through which the pilot observes target aircraft in evasive action, whereby he may so direct the flight of this aircraft that the target aircraft intersects the displayed projectile stream, at a proper range therealong, triggering his cannon at the appropriate instant to insure that real projectiles are present at the intersection.
  • the invention can equally well be used, however, in aeronautical laboratories, or in training equipment where a student pilot observes directly the face of the instrument producing the display, without the use of a combining glass, the target aircraft being simulated or computermodeled for the display, and the pursuit aircraft and autopilot being also simulated except for the controls.
  • Target and pursuit aircraft have now reached a stage of sophistication where a new sight is required.
  • a principal object of our invention is thus to provide an improved gunsight for aircraft use.
  • Another object is to provide such a display system which is continually corrected for changes in parameters of the movement of the pursuit aircraft, and in parameters of the flight of the projectiles.
  • a still further object of the invention is to provide a data processing method for deriving, from signals representative of aircraft motion, related signals for displaying said positions of said projectiles.
  • FIG. 1 is a block diagram of a display system according to our invention, together with means for adding to the display further inputs representative of the motion of a target aircraft where this is desired;
  • FIG. 2 is a labeled representation of the display actually observed
  • FIG. 3 is a block diagram of the system component identified as STREAM COMPUTER in FIG. 1;
  • FIGS. 4-10 inclusive show more details of portions of FIG. 3;
  • FIG. 1 l is a diagram illustrative of considerations underlying our invention.
  • FIG. 12 is a representation similar to FIG. 2 but modified to show how the locus of the earlier figure is traced.
  • FIG. 13 is a diagram illustrative of time relations in the invention.
  • block 21 identifies means for producing signals representative of parameters of the motion of a pursuit aircraft, and may comprise either the aircraft and autopilot themselves, or a computer model thereof, depending on whether the invention is to be used in actual flight or in laboratory or instruction work.
  • the autopilot includes an air data computer and an inertial package, and from it a first cable 22 supplies air data computer signals, and a second cable 23 supplies inertial package signals, the signals going to a projectile stream computer 24 having a plurality of means 25 for setting appropriate constants.
  • a display 26 preferably in the form of a cathode ray oscilloscope is to present data obtained in computer 24 as a line plotted on Cartesian coordinates representative of the angular displacements of various points, measured at the pilots eye, from a zero or nominal direction, angles in train being represented by X-coordinates and angles in elevation being represented by Y- coordinates.
  • the computed coordinates for each of projectiles are supplied by computer 24 on a cable 27 to a storage device 28 from which they are from time to time supplied on a cable 30 to display 26.
  • members 24 and 28 may conveniently comprise functional portions of a single conventional general purpose computer appropriately programmed to perform computations as detailed below, and to store and read out data in a scheduled fashion.
  • Block 31 is representative of the human pilot, student, or experimental operator of the system: he observes the display as suggested at 32 and operates controls such as the throttle 33 and control stick 34 of the actual or modeled aircraft to produce desired real or simulated aircraft motion, in accordance with which the projectile stream must change appropriately.
  • FIG. 2 shows the appearance of a typical display as presented by our apparatus.
  • a cathode ray tube 35 may be viewed directly or reflected in a combining glass. If desired a suitable optical system focused at infinity may be used to avoid parallax, as is well known in gunsights.
  • a line 36 extending from one to another of a series of points, each point being representative of the instantaneous location of a particular one of a series of hypothetical projectiles fired at intervals of 0.1 second beginning at an instant 2 seconds in the past: for convenience the several projectiles are identified by n numbers between 1 and 20, the projectile identified by n 1 being that fired 0.1 second ago and the projectile identified by n 20 being that fired 2 seconds ago.
  • any projectile fired more than 2 seconds ago no longer appears in the display, so that the n numbers are not associated exclusively with particular projectiles, but rather with projectiles having particular times of discharge relative to the continually advancing presentf
  • the n numbers are not associated exclusively with particular projectiles, but rather with projectiles having particular times of discharge relative to the continually advancing presentf
  • the display presents a boresight" cross 37, three range markers in the form of bars 40, 41, and 42, and a radar pipper" 43.
  • the center of cross 37 has coordinates X Y and its size is predetermined.
  • the centers of the range bars have coordinates X Y X Y and X Y and their predetermined lengths are proportional to the angular dimensions, at the pilot's eye, of a target of known size at ranges of 1,000 feet, 2,000 feet, and 3,000 feet, respectively. If desired an adjustment may be provided for selecting different known target sizes: alternatively the range markers may be circles of proper diameters centered at the identified points.
  • the center of radar pipper 43 has the coordinates X Y it preferably comprises a hollow square of predetermined size, but may take any other desired configuration.
  • storage device 28 receives signals for determining the positions and sizes of bars 40, 41, and 42 on a cable 46 from a subordinate range bar computer 47 and signals determining the position and size of the radar pipper 43 on a cable 50 from a subordinate radar pipper computer 51, and supplies these signals on cables 48 and 49 respectively to display 26.
  • computers 47 and 51 receive signals from stream computer 24 on a cable 52.
  • Computer 51 receives a signal at 53 representative of the output of a real or modeled range radar 54. In actual flight there is often insufficient time for a range radar to lock on to the target, and in this case, pipper 43 may not be used.
  • a block 55 is shown representing the target which is being observed in terms of its coordinates X Y relative to the display: the target may be a visually observed one, in flight use of the apparatus, or its coordinates, size, and attitude may be supplied to display 26 on a cable 56 from the same model which supplies radar range 54.
  • FIG. 11 is'simplified compared with FIG. 2, for purposes of illustration, by the assumption that the aircraft is in straight flight andhas followed in the last 2 seconds a course a determined by the line 20, 10', 0: the present location of the aircraft is at 0'. If projectiles had been fired at 0.l second intervals, that fired 0.1 second ago would be at position 1, that fired 0.2 second ago would be at position 2, and so on: the actual trajectory for projectile 10 is shown by curve 60, and that for projectile 20 is shown by curve 61.
  • a vector 7, is defined to extend from the present position of the aircraft (actually of the pilots eye) to the present position of projectile n.
  • a second vector b is defined to extend from the position of the aircraft at the time projectile n was fired to the present position of projectile n.
  • a third vector 71 is defined to extend from the position of the aircraft at the time projectile n was fired to the present position of the aircraft.
  • Vectorsf b Y and 5 are identified on the figure: vector Ti is the line 10' 0' and vector Ti is the line 20' 0'.
  • the line 62 is the locus of the present positions of projectiles 1-20 on their respective trajectories, and is not, in itself, the trajectory of anything.
  • FIG. 3 shows projectile stream computer 24 in more detailed block diagram form.
  • the computer is shown functionally: its inherent store, retrieve, and manipulate functions are those of any general purpose computer, and this conventional detail is omitted to keep the specification within reasonable bounds.
  • computer 24 was a commercial Sigma 5 unit supplied by Scientific Data Systems, Inc., El Segunda, Calif., but any general purpose computer may be used.
  • Theoutput of the computer is a series of 20 values of X on line 63 and a series of corresponding values of Y on line 64: lines 63 and 64 comprise cable 27 in FIG. 1.
  • the values are supplied from a display conversion unit 65 of conventional nature in accordance with a series of 20 vector inputs 2,, each of which is supplied on a cable 66 from an R-Vector computer 67 in terrqspf its components aligned with three orthogonal axes i,j, and ii.
  • a vector i is associated with each projectile computed.
  • the unit vector i is taken along the longitudinal axis of the aircraft, and is positive in the forward direction: rotation about this line as an axis is identified by the roll" angle 0,, positive for rotation according to the ight hand rule.
  • the unit vector j is normal to, the vector i and parallel to the chord of the wings of the aircraft, and is positive to the right, looking forward in the air craft: rotation about this line as an axis is identified by the pitch angle 6 positive according to the right hand rule.
  • the unit vector is normal to vectors i and j and hence in straight and level flight is vertical and is then positive in the downward direction: rotation about this axis is identified as the yaw angle positive according to the right hand rule.
  • Angles 0,, 0 and 0 are sometimes referred to in the literature of aerodynamics as 1), 0, and I, and directions along the unit vectors are sometimes identified by lower case subscripts x, y, and
  • each vector? is expressed in terms of the following identity n nz mj nz
  • the X-coordinate of each projectile is computed from the equation ARCTAN (nu/ (2) and the Y-coordinate of each projectile is computed from the equation nz/ n.r)]
  • the arc tangent is computed by solution of a series:
  • ARCTAN X X (Y /3) (X 4) (Xl7) 4
  • the R-Vectors are computed according to the equation 7,, b, ?i,, (s) as shown in FIG. 8. Values of ii are supplied to computer 67 on a cable 70 from an A-Vector computer 71, FIG. 3, and values I2, are supplied to computer 67 on a cable 72 from a B-Vector computer 73.
  • Computers 71 and 73 operate recursively: each value of ii for example is computed on the basis of a previous value of E Thus, a new value of Ti is computed using the previous value of Z and replaces the previous value of "5 then a new value of '6 is computed using the previous value of E and replaces the previous value of 3, and so on.
  • Non-recursive computation is of course required for 21], and special means are provided for giving an initial set of values, as will be explained below. It is again remarked that each computation is actually made in terms of orthogonal components, and involves the steps of retrieval from storage, manipulation, and return to storage of constant quantities, variable input quantities, and computed quantities.
  • equation (5) is n.1" n.r)( m( rm).; nz' nzfl from which the values r r,,,,, and r are evident by inspection.
  • computer 73 uses the initial values of ,b and i to solve the equation for a new 3 pro ce edin then to find 7; and 5, and so on u r 1til it finds b and Thereafter, new values of b and b l are computed using the equations
  • computer 71 requires as inputs quantities identified as B, T, "v,,, and E, as well as a set of initial values (i )
  • computer 73 requires quantities identified as B, T, K ,V,,,, V,,,, and g, as well as a set of initial values [5,, and P5,. The sources of these quantities will presently be explained.
  • the first signal AV is the translation of the aircraft in inertial space
  • the second signal A6 is the rotation of the aircraft in inertial space: the axes of rotation and of translation coincide puter, in which it is stored as a function of Mach and are as previously defined.
  • a pression H matrix computation is performed which involves the evaluation of the elements of a matrix B defined by the i is to be interpreted as the arithmetic value of the rate o f c hange of vector R
  • the coefficient 0.020402 is quation, W W.
  • A01 A6g A032 (130 M); I A63) (A01A03 7 T 4 2 4 1 2 2 4 2 D D D D i 5L Hf p: 2 4 2 1 4 4 4 2 4. 2
  • the matrix quantity [3 is supplied at 80, 81, and 82,
  • FIG. 3 to computer 71, at 80, 81, and 83 to computer 73, and at 80, 84, to a Gravity Filter 85.
  • K P n/ (20a) The central air data computer 86 of the aircraft, or is pp to computer 97 at 130 and 131 and I0 its equivalent in the model, supplies five signals. Two of puter 73 at 130 and these relate to the ambient air mass; p is the air density Initial condition computer 97 receives another input 124 together make up cable 22 of FIG. 1.
  • the output of computer 1 14, a drag factor K derived from the equation and T is the air temperature.
  • V a, and B signals from air data computer 86 to the equatlons 4 are supplied to an air speed computer 87 at 88, 90, 91 T A (2.2) respectively.
  • a second necessary signal is V, which is the value of 1 one sample old, and is readily available in the computer 52:, memory.
  • the quantity 7, is supplied at 92, 93, and 94 l T+1 go (24) to computer 71, at 92, 93, and 95 to filter 85, and at 92 and 96 to an Initial Condition Computer 97, which also receives at 98 and 99 a vector quantity 7,, representative of the muzzle velocity of the projectiles to be used: I this quantity is also supplied to computer 73 at 98 and The determination of rates of change of vector quantities, and their arithmetic values, is not new in computer technology, and may be performed for example according to the following equations A 100.
  • computer 9 proceeds to determine the values of ,6 ⁇ to 5;, and of b, to ,b,,, according to the following equations 73, at 127 and 126.
  • the initial values ,5 are supplied at 134 to A-l/ector computer 71, and the initial values b and ],b,,[ are supplied at 135 to B-Vector computer 73.
  • the initial vector 5, is supplied to gravity filter 73 at 136.
  • Air speed computer 97 supplies the quantity 7, to computer 73 at 137 and 140, and to filter 85 at 137 and 141.
  • filter 85 also receives A V inputs at 76 from inertial sensor package 75. It computes the actual vector of gravity, g, according to the equation where L is the filter gain and 5,, is the previous value of starting with g ⁇ . This computation is thus also recursive. The quantity is supplied by filter 85 to computer 73 at 142.
  • FIG. 9 gives more details of range bar computer 47, which performs a triplicate function, once each for standard ranges R 1,000 feet, R 2,000 feet, and R 3,000 feet: other values for standard ranges may be obtained by adjustments 143, 144, and 145. The function will be described once for the range R 3,000 feet.
  • Values of F1. are supplied to computer 47 at 52, and the computer first determines a value F, of Ff, such that for example WM RC 2 l inl' (32) See FIG. 11, where a range of 3,000 feet from the aircraft is shown to lie on an are 148 (actually a sphere) passing between ri and u here FI, terminates at point 19 and rj terminates at point 18.
  • the interpolation constant R is first computed according to the equation
  • the desired coordinates are then computed according to equations and stored at 28 through cable 46.
  • the process is repeated for R 2,000 feet and R, l,000 feet. These coefficients define the centers of range bars 40, 41, and 42, FIG. 2.
  • FIG. 10 gives more details of the range pipper computer 51.
  • This computer may be provided with a size adjustment 149, and operates like computer 47 except that a single computation is necessary, based on the input R representative of radar range, and the coordinates X Y which are supplied at 50 for storage at 28 represent the center of range pipper 43, FIG. 2.
  • boresight selector 45 The purpose of boresight selector 45 will now be considered. Reference was earlier made to the iron sight, a sight fixed to the aircraft which the pilot attempts to bring to bear on his target. In the use of such a sight it is obvious that the pilot must not only lead his target in azimuth, to allow for the time of flight of the projectile, but must also allow for the departure of the projectile, under the force of gravity, from endless flight along the cannon boresight.
  • the boresight cross of the present display corresponds to an iron sight.” It is coordinated with the harmonization point," a point on the real or modeled boresight of the cannon, if properly aligned, 2,250 feet from the muzzle.
  • a target in line with the boresight cross is on the pilots line of slight passing through the harmonization point.
  • the apparatus is arranged so that even if there is failure of stream computer 24 or its adjuncts, selector 45 continuously provides the coordinates of the boresight sighting so that the pilot is not completely deprived of sighing aids.
  • the location, on the face of the cathode ray tube, of the center of this cross can be adjusted, in orthogonal directions aligned with the X- and Y-coordinates, by location set adjustments 147 and 150, and the lengths of its cross arms may be varied if desired by a further adjustment 151.
  • FIG. 13 is a time diagram illustrative of this facet of the invention. From this diagram it will be seen that new values of R p, T and V are supplied to the computer every l00 milliseconds, while new values of a, [3,, AV, and A6 are provided every 20 milliseconds, if these values change.
  • the computer determines the coordinates for 20 projectiles and those for the range bars and radar pipper, which requires less than milliseconds, waits until the end of I00 milliseconds, when new input values, if any, are supplied, and repeats the computations. As newly computed values for the various coordinates are stored they replace previous values, so that no coordinate in the computer is based on data older than I00 milliseconds.
  • display unit 26 per se is simply one of nondestructively reading out the coordinates of one point after another, in a predetermined sequence, and deflecting the beam of the CRT to the locations of these points successively, blanking the beam where it is not desired that a visible trace appear.
  • This can be acill complished by the same general purpose computer on a time sharing basis, in a conventional fashion, as follows. Although each individual computing step takes only a few microseconds, many such steps have to be performed in sequence in each lOO millisecond interval, and the computer is normally engaged in these computations until near the end of the 100 millisecond period.
  • an interrupt pulse is supplied: the computer completes whatever computing step it was engaged in, and remembers" where it was, then retrieves from storage the next coordinates and brightness data according to a preset program and supplies thm to the display, and then returns to computation, rembering also where in the display program it was. If, at the instant when read-out of the coordinates of a particular point to the display is called for, the new values of these coordinates have not yet been computed, the previous values will be used again. This continues until all 29 points have been retrieved, pauses, and then repeats, every 20 milliseconds.
  • FIG. 13 shows the lower row of time markings: as mentioned above, we choose to display only the even numbered projectiles, to reduce required computer capacity and display speed requirements.
  • the beam is deflected to a starting point and is blanked. After 0.5;.ts the beam is deflected to point 1 and intensified. It is deflected in sequence to points 2, 3, 4, 5, 6, and 7 and then blanked while it is deflected to point 8, and so on. The points are followed in numerical order, deflections during which the beam is blanked being indicated by dashed lines. Note that from point 17 the beam is not deflected to X Y but rather to point 18: the length of each range bar having been previously set, the computer automatically subtracts and adds one-half of this length to X R A and thus arrives at points 18 and 19 directly.
  • the persistence of the oscilloscope screen is lOng enough that little loss of visual intensity occurs in the 14.5 milliseconds required to trace the pattern of 29 points (including zero) but is also short enough that no trouble is encountered from blurring of the visual image due to change in coordinates of a projectile between one sweep of the pattern and the next, or due to the fact that point 14 for example may be a newly computed point while point is based on an old computation.
  • the same general purpose computer which determines the various coordinates may also be used to model the aircraft-and-autopilot and the target-andradar.
  • all information useable by the investigator or student pilot is on the oscilloscope screen and no combining glass is necessary.
  • the invention here presented pertains to the production of the display representing the projectiles, with the range bars and so forth, as distinguished from apparatus combining the display with a visual target.
  • Apparatus according to claim 1 together with means for impressing on the display at least one further indicium definitive of a point therealong at a predetermined range from the vehicle.
  • a computer to compute the further coordinates in said Cartesian system of the point defining the direction of the head of an interpolation vector extending from the present position of the aircraft for a known distance and terminating on said locus.
  • Apparatus according to claim 4 together with means for adding to the display an indicium characterized in accordance with said known distance and located in accordance with said further coordinates.
  • the first vectors are determined by vector quantities representative of the rotation of the craft in inertial space, A0, and the displacement of the cannon muzzle from the observers viewing point, d, and by scalar quantities representative of the interval between projectile firings,
  • computer means programmed for iteratively determining the present apparent positions of a plurality of projectiles, if discharged sequentially from a moving vehicle at known intervals beginning at a predetermined time in the past, as seen from a particular point in the vehicle;
  • the method of displaying data represented by a sequence of vectors radiating from a common origin in directions having a major component aligned with a particular direction, as seen from a point on the side of said origin opposite to said general direction, which comprises, in combination:
  • Display apparatus comprising means programmed to compute a family of vectors extending from successive points along the path of a moving vehicle, at which points successive missiles are fired therefrom at predetermined intervals in the past, to the present locations of the missiles;

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
US00069536A 1970-09-04 1970-09-04 Projectile stream display apparatus Expired - Lifetime US3716696A (en)

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US (1) US3716696A (enrdf_load_stackoverflow)
AU (1) AU3253571A (enrdf_load_stackoverflow)
BE (1) BE772157A (enrdf_load_stackoverflow)
CA (1) CA966931A (enrdf_load_stackoverflow)
CH (1) CH537565A (enrdf_load_stackoverflow)
DE (1) DE2143873A1 (enrdf_load_stackoverflow)
FR (1) FR2107236A5 (enrdf_load_stackoverflow)
GB (1) GB1313260A (enrdf_load_stackoverflow)
IL (1) IL37746A (enrdf_load_stackoverflow)
NL (1) NL7112175A (enrdf_load_stackoverflow)
NO (1) NO130741C (enrdf_load_stackoverflow)
SE (1) SE368459B (enrdf_load_stackoverflow)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0009984A1 (en) * 1978-10-10 1980-04-16 General Electric Company System for controlling the dispersion pattern of a gun
EP0042004A4 (en) * 1979-12-20 1982-04-29 Gen Electric SHOOTING SIMULATION SYSTEM.
AU571850B2 (en) * 1982-09-30 1988-04-28 General Electric Company Aircraft gunnery boresight correction
US20190154402A1 (en) * 2016-04-25 2019-05-23 Bae Systems Plc System integration

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4698489A (en) * 1982-09-30 1987-10-06 General Electric Company Aircraft automatic boresight correction
FR2541448A1 (fr) * 1983-02-18 1984-08-24 Thomson Csf Systeme de controle du vol d'un aeronef utilisable comme simulateur de tir
AU669341B2 (en) * 1992-11-09 1996-06-06 Electronic Data Systems Corporation Improvements in weapons systems
CN105300184B (zh) * 2015-10-30 2017-12-15 北京艾克利特光电科技有限公司 一种可对目标物进行三维定位及显示的光电瞄准器

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0009984A1 (en) * 1978-10-10 1980-04-16 General Electric Company System for controlling the dispersion pattern of a gun
EP0042004A4 (en) * 1979-12-20 1982-04-29 Gen Electric SHOOTING SIMULATION SYSTEM.
AU571850B2 (en) * 1982-09-30 1988-04-28 General Electric Company Aircraft gunnery boresight correction
US20190154402A1 (en) * 2016-04-25 2019-05-23 Bae Systems Plc System integration
US10557686B2 (en) * 2016-04-25 2020-02-11 Bae Systems Plc System integration

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IL37746A (en) 1974-12-31
NL7112175A (enrdf_load_stackoverflow) 1972-03-07
GB1313260A (en) 1973-04-11
CA966931A (en) 1975-04-29
SE368459B (enrdf_load_stackoverflow) 1974-07-01
AU3253571A (en) 1973-02-22
CH537565A (de) 1973-05-31
NO130741C (enrdf_load_stackoverflow) 1975-01-29
DE2143873A1 (de) 1972-03-09
FR2107236A5 (enrdf_load_stackoverflow) 1972-05-05
BE772157A (fr) 1972-01-17
IL37746A0 (en) 1972-02-29
NO130741B (enrdf_load_stackoverflow) 1974-10-21

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