US3162399A - Control means for guided missiles, aerodynes and the like - Google Patents

Control means for guided missiles, aerodynes and the like Download PDF

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Publication number
US3162399A
US3162399A US40894A US4089460A US3162399A US 3162399 A US3162399 A US 3162399A US 40894 A US40894 A US 40894A US 4089460 A US4089460 A US 4089460A US 3162399 A US3162399 A US 3162399A
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US
United States
Prior art keywords
lever
housing
planes
control lever
control
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US40894A
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English (en)
Inventor
Fleck William
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Short Brothers PLC
Original Assignee
Short Brothers and Harland Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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Publication of US3162399A publication Critical patent/US3162399A/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/24—Beam riding guidance systems

Definitions

  • Apparatus comprises a control lever mounted for angular movement in two planes at right angles to each other, a first magnetic circuit so arranged that changes in position of the control lever in one of said planes cause changes in the magnetic reluctance of said first circuit, a second magnetic circuit so arranged that changes in position of the control lever in the other of said planes cause changes in the magnetic reluctance of said second circuit, and first and second coil assemblies respectively associated with the first andsecond magnetic circuits and arranged to generate electric signals representative of the changes in magnetic reluctance, for controlling actuators of the pitch and yaw control surfaces.
  • the lever may take the form of a miniature joystick or control column, which" is mounted in a housing having a pistol-type grip so that it may be grasped in the hand with the thumb resting upon the free end of the lever, the movements of the lever being effected by appropriate movements of the thumb according to visual observations of missile and target.
  • FIG. 1 is a cross sectional side elevation of control apparatus according to the invention for use on a sighting arm of a particular form of a guidance control unit for a guided missile,
  • FIG. 2 is a cross sectional end elevation taken on the line II-II of FIG. 1 and,
  • FIG. 3 is a circuit diagram of the coil assemblies embodied in the apparatus shown in FIG. 1 and a demodulator for demodulating the signals generated therein.
  • control apparatus comprises a substantially cylindrical tubular housing 11, which is suitably supported on a sighting arm of a guidance control unit and which carries at one end a depending pistol-type grip 12 which, in conjunction with another grip on the sighting arm, is used by the missile controller to adjust the angular position of the sighting arm.
  • the housing 11 At its end remote from the pistol grip the housing 11 carries two end plates 32 and 33. In the centre of the plate 32 is fixed one end of a rod 14 which extends axially through the housing and terminates at a point adjacent the pistol grip in a thumb button 15.
  • the rod 14 possesses a certain degree of flexibility and is therefore capable of being moved angularly in any direction normal to its length by the movement of the controllers thumb pressed against the button 15.
  • the angular movement of rod 14 may be limited to give the required electrical outputs, as hereinbefore referred to, by means of four adjustable screws mounted on the thumb button 15.
  • the rod 14 constitutes the aforementioned miniature joystick lever.
  • the ingress of dust and moisture to the interior of the housing 11 is prevented by an india rubber or like sealing cap 16 through which the button 15 on the free end of the rod protrudes.
  • the coils 19 and 20 are mounted on the limbs of two oppositely directed U-shape stator cores 23 and 24 and the coils 21 and 22 are mounted on two further oppositely directed U-shaped stator cores 25 and 26.
  • the cores 23 and 24 lie in a vertical plane passing through the axis of rod 14 when the latter is in an undeflected position and the cores 25 and 26 lie in a plane also passing through said axis and at right angles to the first-mentioned plane.
  • the four stator cores 2326 carrying the coils 19-24 are mounted on a tube 30, which also carries the primary winding 18 and a plate 31 upon which are mounted circuit components of the circuit shown in FIGURE 3.
  • the tube 30 is fixedly mounted within the housing 11 and the remaining space in the housing filled with an epoxy resin such as sold by the Ciba Co., Inc. under the trademark Araldite.
  • the rod 14 is arranged to be co-axial with the tube 30 and fine adjustment of the fixed end of the rod to centralise the core 17 in relation to the stator cores is provided by connecting the end of the rod to the outer end plate 32 which is horizontally adjustable in relation to the inner plate 33 which is vertically adjustable in relation to the housing 11.
  • Vertical adjustment of the inner plate 33 can be etfected by the screwing of a set screw 34 which engages in a threaded bore in a projection 35 carried by the inner plate 33, the screw 34 being held in relation to the housing 11 by means of a locking screw 36 the reduced end of which engages in a reduced section of the shank of the screw 34.
  • a fixed pin 37 engages in a vertical slot 39 in the lower part of the plate 33 and Horizontal adjustment of the outer plate 32 is provided by means similar to that employed for adjustment of the plate 33, but these means are not shown in the drawing.
  • the end plates are protected by a cover 13 attached to housing 11 to form an airtight seal.
  • FIG. 3 this schematically shows an output circuit for the coils 19 and 20 for regulating pitch.
  • a similar output circuit (not shown) is connected to yaw control coils 21 and 22.
  • the coil 19 comprises two windings 191 and 192 and the coil 20 comprises two windings 201 and 203.
  • the two coil pairs 191, 192 and 201, 203 would be actually disposed in the same abovebelow relationship as coils 19 and 20 in FIGURES l and 2, and would have the same physical relation to primary winding 18 as illustrated in those figures.
  • the primary winding 18 which is also common to coils 21 and 22 is connected to a single phase A.C.
  • a full wave phase sensitive demodulator 42 which comprises four transistors 43 to 46 connected as shown to the windings 191, 192, 201 and 203 and to a pair of output terminals 47, 48.
  • Electrical connections to the AC. supply are made via a plug 49 (FIGURE 1) contained within a flange in the housing 11 and an electric cable which is fed through a tube 50 on the sighting the central position shown in FIGURE 1 or 2 increases the couplings from the primary winding 18 to the two FIGURE 3 windings 191 and 192 and decreases the couplings to the windings 201 and 293.
  • a DC. output voltage is generated across the output terminals 47, 48, the magnitude of which is a measure of the displacement of the armature 17 from its central position. Displacement of the armature 17 in the opposite sense produces a DC. voltage of opposite sign.
  • the DC. output signals so generated may be transmitted in known manner over a radio command link to control apparatus within the missile which in response to said signals effects a change in the position of the control surfaces as required by the remote controller.
  • the missile controller will determine from visual observations of the missile and the target, or of images thereof projected upon a radar screen, what directional control mane-ouvres are required to guide the missile to the target. Deflections in pitch will necessitate a movement of the thumb in the plane of one of the secondary winding assemblies, and deflections in yaw a movement in the plane of the other secondary winding assembly; combined movements in both planes may of course be eflected simultaneously. In either case the displacement of the core in relation to the secondary winding will make such alteration in the current induced therein as is required to produce the necessary adjustment of the apparatus governing the pitch (or yaw) control organ.
  • Apparatus for controlling pitch and yaw control surfaces of a missile or other moving body comprising a housing, a pistol-grip type handle to be grasped by an operator and fixedly secured to said housing, a control lever mounted within the housing for angular movement therein in two planes at right angles to each other, said lever being secured at one end so as to be angularly movable in said planes by transverse forces applied to the other end, a flexible diaphragm closing an opening in said housing at the said other end of said lever, a button secured to said other end of the lever and mounted in said flexible diaphragm for engagement by the thumb of the operator when said handle is gripped, to effect theaforesaid two-plane movement of said control lever without moving said housing, there being within said housing a first magnetic circuit including a pole piece extending in the direction of the control lever and terminating in the region of the control lever in a pole face at right angles to the direction of movement of the lever in one of the said two planes, whereby
  • Apparatus according to claim 1 comprising a further magnetic circuit associated with each plane and including a pole piece extending in the direction of the control lever and terminating in the region of the control lever in a pole face opposite the pole face of the other magnetic circuit associated with said plane, whereby a movement of the control lever in said plane produces a differential change in the reluctances of the two circuits, and a further coil assembly associated with each further magnetic circuit and connected with the associated one of the first and second coils to generate electric signals representative of the said diflerential change in reluctance.
  • Apparatus according to claim 2 comprising a full wave phase sensitive demodulator connected to receive the electrical output signals of the coil assemblies linking the magnetic circuits associated with each plane, and means for producing an alternating flux in the magnetic circuits.
  • control lever is sufliciently resilient as to permit deflection in said planes by force applied to the said other end by the button.
  • Apparatus according to claim 1 comprising means for adjusting the position of the said one end of the lever to bring the lever to a required undeflected position in relation to the magnetic circuits.
  • each magnetic circuit comprises a U-shaped stator core lying in the associated plane in which the lever is movable, the limbs of each stator core being directed to said lever and wherein the coil assemblies linking the magnetic circuits are mounted on the stator cores respectively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pinball Game Machines (AREA)
  • Mechanical Control Devices (AREA)
  • Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
US40894A 1959-07-28 1960-07-05 Control means for guided missiles, aerodynes and the like Expired - Lifetime US3162399A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB25887/59A GB889454A (en) 1959-07-28 1959-07-28 Improved control means for guided missiles and other moving bodies

Publications (1)

Publication Number Publication Date
US3162399A true US3162399A (en) 1964-12-22

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ID=10234984

Family Applications (1)

Application Number Title Priority Date Filing Date
US40894A Expired - Lifetime US3162399A (en) 1959-07-28 1960-07-05 Control means for guided missiles, aerodynes and the like

Country Status (5)

Country Link
US (1) US3162399A (enrdf_load_stackoverflow)
CH (1) CH381099A (enrdf_load_stackoverflow)
DE (1) DE1240974B (enrdf_load_stackoverflow)
GB (1) GB889454A (enrdf_load_stackoverflow)
NL (1) NL254095A (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3661346A (en) * 1967-05-23 1972-05-09 Bolkow Gmbh Device for producing missile guiding signals

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2888635A (en) * 1957-06-26 1959-05-26 Mandrel Industries Stick force transducer
US2903663A (en) * 1955-05-03 1959-09-08 Contraves Italiana Spa Stick actuated inductive controller element
US2919404A (en) * 1954-06-15 1959-12-29 Honeywell Regulator Co Bridge demodulator phase detecting circuit

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1020475A (fr) * 1950-06-19 1953-02-06 Electronique & Automatisme Sa Perfectionnements apportés aux servo-mécanismes de recopie
DE938655C (de) * 1953-03-31 1956-02-02 Trix Vereinigte Spielwaren Fab Netzanschlussgeraet fuer mit Gleichstrom betriebene Spieltriebfahrzeuge
US2839733A (en) * 1954-05-13 1958-06-17 Gen Electric Tracer head
DE1098411B (de) * 1958-07-25 1961-01-26 Vickers Armstrongs Aircraft Handgeraet zum Lenken drahtgelenkter Geschosse

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2919404A (en) * 1954-06-15 1959-12-29 Honeywell Regulator Co Bridge demodulator phase detecting circuit
US2903663A (en) * 1955-05-03 1959-09-08 Contraves Italiana Spa Stick actuated inductive controller element
US2888635A (en) * 1957-06-26 1959-05-26 Mandrel Industries Stick force transducer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3661346A (en) * 1967-05-23 1972-05-09 Bolkow Gmbh Device for producing missile guiding signals

Also Published As

Publication number Publication date
CH381099A (de) 1964-08-14
DE1240974B (de) 1967-05-24
NL254095A (enrdf_load_stackoverflow)
GB889454A (en) 1962-02-14

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