US3043197A - Means for controlling guided missiles - Google Patents

Means for controlling guided missiles Download PDF

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Publication number
US3043197A
US3043197A US823606A US82360659A US3043197A US 3043197 A US3043197 A US 3043197A US 823606 A US823606 A US 823606A US 82360659 A US82360659 A US 82360659A US 3043197 A US3043197 A US 3043197A
Authority
US
United States
Prior art keywords
missile
control unit
thumb
potentiometer
housing
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
US823606A
Other languages
English (en)
Inventor
John W Piper
Fryer William Harry
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.)
Vickers Armstrongs Aircraft Ltd
Original Assignee
Vickers Armstrongs Aircraft 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
Application filed by Vickers Armstrongs Aircraft Ltd filed Critical Vickers Armstrongs Aircraft Ltd
Application granted granted Critical
Publication of US3043197A publication Critical patent/US3043197A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F41G7/32—Command link guidance systems for wire-guided missiles
    • 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
    • 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

Definitions

  • the invention has for its object to provide improved means for controlling electrically guided missiles, principally (though not necessarily exclusively) missiles which are capable of being launched and operated by an infantryman.
  • the invention provides a control unit having two handle grips disposed one in front of the other, by which the control unit may be aligned on the target, an electrical trigger-switch or firing button adapted to be connected by trailing wires to a lunching apparatus for the missile, and a pivotally mounted thumb housing adapted to receive one of the operators thumbs and to constrain the thumb to move about axes which, when signals derived from the movements of potentiometer wipers connected to said thumb housing are transmitted to the missile, will impart to the missile guidance control movements with reference to the horizontal and vertical planes.
  • the control unit is also preferably provided with a monocular prismatic or other visual aid by which the operator may be assisted when attacking distant targets.
  • FIG. 1 is a side elevation of the control unit
  • FIGS. 2, 3 and 4 are diagrams illustrating the manner in which the missile is controlled, FIG. 2 being a plan and FIGS. 3 and 4 side elevations respectively showing the missile before and after launching; and
  • FIGS. 5 and 5a are fragmentary side and rear elevations, respectively, partially broken away and showing the potentiometer'wiper connections to the thumb housing and to the horizontal axis lever of the control unit.
  • control unit comprises a stock upon the underside of which are provided two downwardly depending handle grips 11'and 12, respectively spaced fore-and-aft, so that the stock 10 may be'aligned in a given direction by grasping the handle grips 11, 12 in the two hands held one in front of the other.
  • a springloaded trigger switch 13 Conveniently adjacent to the handle grip 11 is a springloaded trigger switch 13, protected by a guard 14, and
  • a cup-shaped housing 16 Adjacent the handle grip 12 is a cup-shaped housing 16 into which the operators thumb is placed. Said housing 16 is mounted on the stock upon a lever 17 with capability of pivotal motion thereon about a horizontal axis at 171, said lever being mounted at 172 end the stock with'capability of pivotal motion about an axis in the longitudinal vertical plane.
  • the axis 172 coincides substantially with the axis of the carpal joint of the thumb, whilst the axis 171 coincides substantially with the axis of the terminal joint thereof; thus, when the stock is heldwith the handle grips 11, 12 in an upright position, the
  • thumb is constrained by the housing 16 to move only in the direction determined by said two axes 171, 172.
  • the control unit incorporates two electric potentiometers Ph and Pv respectively housed in the casings 18, 19.
  • the wiper 22 of the potentiometer Ph contained in the casing 18 is connected to the spindle 20 on which the lever 17 is mounted, so that when operated this potentiometer Ph transmits to the missile signals imparting guidance in the horizontal plane.
  • the wiper 23 of the potentiometer Pv housed in the casing 19 is operated by the movement of the housing 16 about the axis 171, so that when operated this potentiometer Pv transmits to the missiles signals imparting guidance in the vertical plane.
  • Electric batteries for the two potentiometers Ph and Pv are housed within the handle grip 12, suitable connections being made with the end contacts of the potentiometers.
  • the electric guidance circuits relating to said potentiometers, and the firing circuit connected with the trigger switch 13, are accommodated in the leads included in a trailing-cable 21 which is attached to the handle 12.
  • the handle grip is used to accommodate a passive resistance-capacitance network, serving as a ground filter.
  • Simple self-centering springs may be provided in association with the thumb housing, in order to provide feel simulation in operating the controls.
  • FIGS. 2 and 3 show a (missile A mounted on a launching standB and connected by the cable 21 to the stock 10 of the control unit held in the hands of a prone infantryman C represented as sighting the control unit upon a target D.
  • the guided course of the missile A after firing is indicated by the dotted line (FIG. 2).
  • FIG. 4 shows the missile A, after discharge, connected by a trailing cable E to the launching stand, said cable E enclosing the guidance control circuit connections from the control unit.
  • a manually operated device for controlling the flight .path of a missile with the natural movements of an operators thumb
  • said device comprising a stock member having a depending handle grip, a horizontal axis control lever disposed rearwardly of said grip, pivot means mounting said horizontal axis control lever on the device for pivotal movement from side to side of said stock member, a cup-shaped housing disposed adjacent the free end of said horizontal axis control lever and formed for receiving the thumb of an operator of the device, second pivot means mounting said housing at its rearward end to the free end of said horizontal axis control lever for pivotal movement upwardly and downwardly, potentiometer means for connection to said missile for varying electric impulses transmitted thereto for controlling horizontal and vertical movements thereof, said potentiomfirst potentiometer mounted adjacent said horizontal axis control lever and being connected thereto for movement thereby and a second potentiometer mounted adjacent said cup-shaped housing and being connected thereto for movement thereby, said potentiometers registering movements of said lever and said cup-shaped housing.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Mechanical Control Devices (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US823606A 1958-07-25 1959-06-29 Means for controlling guided missiles Expired - Lifetime US3043197A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24091/58A GB853682A (en) 1958-07-25 1958-07-25 Improved means for controlling guided missiles

Publications (1)

Publication Number Publication Date
US3043197A true US3043197A (en) 1962-07-10

Family

ID=10206225

Family Applications (1)

Application Number Title Priority Date Filing Date
US823606A Expired - Lifetime US3043197A (en) 1958-07-25 1959-06-29 Means for controlling guided missiles

Country Status (6)

Country Link
US (1) US3043197A (da)
BE (1) BE580967A (da)
CH (1) CH385035A (da)
FR (1) FR1230873A (da)
GB (1) GB853682A (da)
NL (2) NL113561C (da)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3198072A (en) * 1959-09-24 1965-08-03 Bolkow Entwicklungen Kg Portable missile carrier and launcher
US3233548A (en) * 1963-11-12 1966-02-08 Canrad Prec Ind Inc Dirigible aerial torpedo
US3366346A (en) * 1965-07-19 1968-01-30 Army Usa Remote missile command system
US3661346A (en) * 1967-05-23 1972-05-09 Bolkow Gmbh Device for producing missile guiding signals
US3868883A (en) * 1964-02-20 1975-03-04 Mc Donnell Douglas Corp Guidance system
US3974984A (en) * 1961-03-24 1976-08-17 British Aircraft Corporation Control of guided missiles
US4298914A (en) * 1978-06-23 1981-11-03 Long Alvin L Electric firing device
US5620152A (en) * 1995-01-27 1997-04-15 British Aerospace Public Limited Company Tethered missile system

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1249274A (en) * 1915-01-12 1917-12-04 Chandler Dev Corp Means for fire control for dirigible devices.
US1313100A (en) * 1919-08-12 Torpedo-controlling apparatus
US2149666A (en) * 1937-05-07 1939-03-07 William H Hammer Electrical toy airplane
US2435217A (en) * 1945-05-02 1948-02-03 Jr Cleves H Howell Firearm and stock structure therefor
US2558109A (en) * 1945-03-09 1951-06-26 Stanzel Victor Single-line control for miniature aircraft
US2725669A (en) * 1953-02-16 1955-12-06 Robert W Vincent Control box for model aeroplanes

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1313100A (en) * 1919-08-12 Torpedo-controlling apparatus
US1249274A (en) * 1915-01-12 1917-12-04 Chandler Dev Corp Means for fire control for dirigible devices.
US2149666A (en) * 1937-05-07 1939-03-07 William H Hammer Electrical toy airplane
US2558109A (en) * 1945-03-09 1951-06-26 Stanzel Victor Single-line control for miniature aircraft
US2435217A (en) * 1945-05-02 1948-02-03 Jr Cleves H Howell Firearm and stock structure therefor
US2725669A (en) * 1953-02-16 1955-12-06 Robert W Vincent Control box for model aeroplanes

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3198072A (en) * 1959-09-24 1965-08-03 Bolkow Entwicklungen Kg Portable missile carrier and launcher
US3974984A (en) * 1961-03-24 1976-08-17 British Aircraft Corporation Control of guided missiles
US3233548A (en) * 1963-11-12 1966-02-08 Canrad Prec Ind Inc Dirigible aerial torpedo
US3868883A (en) * 1964-02-20 1975-03-04 Mc Donnell Douglas Corp Guidance system
US3366346A (en) * 1965-07-19 1968-01-30 Army Usa Remote missile command system
US3661346A (en) * 1967-05-23 1972-05-09 Bolkow Gmbh Device for producing missile guiding signals
US4298914A (en) * 1978-06-23 1981-11-03 Long Alvin L Electric firing device
US5620152A (en) * 1995-01-27 1997-04-15 British Aerospace Public Limited Company Tethered missile system

Also Published As

Publication number Publication date
NL241643A (da)
GB853682A (en) 1960-11-09
NL113561C (da)
BE580967A (da)
FR1230873A (fr) 1960-09-20
CH385035A (de) 1965-02-26

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