GB1605396A - Improvements relating to control systems for missiles - Google Patents

Improvements relating to control systems for missiles Download PDF

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Publication number
GB1605396A
GB1605396A GB33465A GB33465A GB1605396A GB 1605396 A GB1605396 A GB 1605396A GB 33465 A GB33465 A GB 33465A GB 33465 A GB33465 A GB 33465A GB 1605396 A GB1605396 A GB 1605396A
Authority
GB
United Kingdom
Prior art keywords
spool
missile
rotatable
control surface
shaft
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
GB33465A
Inventor
Albert John Dunn
Oliver Samuel Carson
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
Application filed by Short Brothers and Harland Ltd filed Critical Short Brothers and Harland Ltd
Priority to GB33465A priority Critical patent/GB1605396A/en
Priority to AU67424/65A priority patent/AU658814B2/en
Priority to CA 947030 priority patent/CA1336084C/en
Anticipated expiration legal-status Critical
Publication of GB1605396A publication Critical patent/GB1605396A/en
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Description

(54) IMPROVEMENTS RELATING TO CONTROL "' SYSTEMS FOR MISSILES (71) We, SHORT BROTHERS & BR< HARLAND LIMITED, a Northern Ireland Company, of Airport Road, Belfast, Northern Ireland, do hereby declare the invention, for which we pray that a patent may be granted to us and the method by which it is to be performed to be particularly described in and by the following statement: The present invention relates to a control system for missiles.
In the complete specification of our copending British Application 7298/63 Specification No.
1605400, there is claimed a missile comprising a rotatable portion arranged for rotation relative to another portion of the missile, means for rotating said rotatable portion and bringing it to any one of a number of preselected positions in relation to a datum, and means on said rotatable portion for exerting a thrust thereon away from the axis of rotation to produce a steering effect on the missile.
According to the present invention, there is provided a missile comprising arotatable portion arranged for rotation about a predetermined axis relative to another portion of the missile, first and second control members on said rotatable portion for separate actuation by first and second actuator mechanisms moveable in response to the energisation of first and second electromagnetic coils forming part of the mechanisms and contained in the said other portion of the missile, said coils being mounted in space relation in the said other portion along the rotary axis of said rotatable portion and concentric with respect thereto, with the first coil nearer to the rotatable portion that the second coil, the first actuator mechanism comprising an axially movable sleeve coaxial with the rotary axis and extending at one end into the rotatable portion and at the other end carrying an armature disc mounted concentrically with respect to the sleeve and in cooperating relation with the first coil which upon energisation causes the disc and the sleeve to move axially, to effect actuation of the first control member and the second actuator mechanism comprising an axially moveable shaft coaxial with the rotary axis and slidable within the sleeve, said shaft extending beyond said sleeve at each, one end of the shaft extending into the rotatable portion of the missile and the other end carrying a further armature disc concentric with the shaft and arranged in cooperating relation with the second coil which upon energisation causes the further disc and the shaft to move axially along the rotary axis of the rotatable portion to effect actuation of the second control member.
The sleeve and its associated armature disc as well as the shaft and its associated disc maybe rotatable about the rotary axis of the rotatable portion of the missile, but in a preferred embodiment of the invention although capable of rotation the latter are not required to rotate with the rotatable portion, and a spool is provided on the end of the shaft and a further spool provided on the end of the sleeve, each spool being coaxial with the rotary axis of the rotatable portion and being engaged by a pin which lies in a peripheral groove in the spool and is constrained to follow the axial displacement of the spool whilst rotating with the rotatable portion.
In an embodiment of the invention hereinafter to be described, the spools are rotatably mounted on the ends of the shaft and sleeve so that they may turn with the rotatable portion and remain stationary with respect to their cooperating pins.
One embodiment of the invention will now be described by way of example with reference to the accompanying drawings in which: Fig. 1 is a side elevation of a missile according to the invention, Fig. 2 is a part-sectional side elevation of a forward portion of the missile shown in Fig. 1, drawn to a larger scale, Fig. 3 is a sectional end elevation taken on the line Ill-In in Fig. 2, and Fig. 4 is a sectional end elevation taken on the line IV-IV in Fig. 2.
Referring to the drawings, a missile 11 comprises a main body portion 12, a fixed nose portion 13 which is screwed on to the main body portion 12, and a rotatable nose portion 14 which is rotatably mounted on bearings 15 for rotation about the longitudinal axis of the missile. The rotatable nose ponion 14 includes a pair of elevator control surfaces 16 and 17 and a pair of aileron control surfaces 18 and 19. The control surface 16 is rotatably mounted in bearings 20 for rotation about an axis passing through the longitudinal axis of the missile and at right angles thereto and each of the other control surfaces 17, 18 and 19 are likewise rotatably mounted in the rotatable nose portion 14.The elevator control surfaces 16 and 17 have a common pivotal axis and are arranged to be pivoted about the axis by an actuator mechanism comprising a pair of solenoid coils 21 and 22 which are arranged coaxally on the longitudinal axis of the missile and are spaced apart so as to receive in the gap between them an armature disc 23 which is fixedly mounted on the rear end of a hollow shaft 24 lying on the longitudinal axis of the missile and extended forwardly into the rotatable nose portion 14 and terminating at the forward end in a spool 25 rotatably mounted thereon by bearings 26, and the solenoid coils 21 and 22 are so wound and adapted to be alternately energised that the armature disc 23 is pulled within the gap to the one or other or the coils and causes a longitudinal displacement of the shaft 24 and a corresponding displacement of the spool 25.
The aileron control surfaces 18 and 19 are likewise pivotal about a common lateral axis and are controlled by an actuator mechanism comprising a pair of solenoid coils 27 and 28 fixedly mounted in spaced relation in the fixed nose portion 13 and coaxial with the longitudinal axis of the missile and an armature disc 29 concentric with the coils and arranged in the gap between them. The disc 29 is fixedly on the end of a sleeve 30 within which the hollow shaft 24 is slideably and rotatably mounted, and the sleeve 30 is itself slideably and rotatably mounted in a supporting framework 31 of the fixed nose portion 13 and projects at its forward end into the rotatable nose portion 14, terminating in a spool 32 rotatably mounted on its forward end by bearings 33.The solenoid coils 27 and 28 are likewise so wound and energised alternately that the armature disc 29 is pulled within the gap to the one or the other of the coils and causes a longitudinal displacement of the sleeve 30 and a corresponding displacement of the spool 32.
Referring particularly to Fig. 3 the elevator control surface 16 is provided with an inwardly extending boss 34 which carries a curved pin 35 which engages in the peripheral groove in the spool 25, and elevator control surface 17 is likewise provided with a bush and curved pin the latter of which engages in the groove in the spool 25 on the same side as that of the pin 35 so that longitudinal displacement of the spool 25 results in a pivoting movement of the control surfaces 16 and 17 in the same sense.
Referring particularly to Fig. 4, the aileron control surface 18 is provided with an inwardly directed boss 36 carrying a curved pin 37 which is arranged to engage in the peripheral groove in the spool 32 and the aileron control surface 19 is likewise provided with a bush and curved pin the latter of which is arranged to engage in the groove in the spool 32 on the side opposite that engaged by the pin 37 so that displacement of the spool 32 along the longitudinal axis of the missile results in the pivoting movement of the control surfaces 18 and 19 in opposite senses.
The rotatable nose portion of the missile carries a free gyroscope 38 which is arranged to generate signals representative of the roll attitude of the nose portion ] 4, on a potentiometer 39 and these signals are fed along a signal carrying lead 40 which passes through the hollow shaft 24 to a slip ring assembly 41.
In the control system described and claimed in our copending British patent application No.
7298/63 (Specification No 1605400) signals for controlling the operation of the elevator and aileron control surfaces are transmitted from a ground station and received by a receiver mounted in the main body 12 of the missile, and these signals are employed to operate switches for alternately energising the coils 21, 22, 27 and 28 and the control is made such that the aileron control surfaces 18 and 19 are operated to being the rotatable nose portion to a predetermined roll attitude in space and the elevator control surfaces 16 and 17 operated to produce a lateral steering thrust on the missile.
What we claim is: 1. A missile comprising a rotatable portion arranged for rotation about a predetermined axis relative to another portion of the missile, first and second control members on said rotatable portion for separate actuation by first and second actuator mechanisms movable in response to the energisation of first and second electromagnetic coils forming part of the mechanisms and contained in the said other portion of the missile said coils being mounted in spaced relation in the said other portion along the rotary axis of the said rotatable portion and concentric with respect thereto, with the first coil nearer to the rotatable portion than the second coil, the first actuator mechanism comprising an axially movable sleeve co-axial with the rotary axis and extending at one end into the rotatable portion and at the other end carrying an armature disc mounted concentrically with respect to the sleeve and in cooperating relation with the first coil which upon energisation causes the disc and the sleeve to move axially to effect actuation of the first control member, and the second actuator mechanism comprising an axially movable shaft coaxial with the rotary axis and slidable within the sleeve, said shaft extending beyond said sleeve at each end, one end of the shaft extending into the rotatable portion of the missile and the other end carrying a further armature disc concentric with the shaft and arranged in cooperating relation with the second coil which upon energisation causes the further disc and the shaft to move axially to effect actuation of the second control member.
2. A missile according to claim 1, wherein the
**WARNING** end of DESC field may overlap start of CLMS **.

Claims (10)

  1. **WARNING** start of CLMS field may overlap end of DESC **.
    thereto and each of the other control surfaces 17, 18 and 19 are likewise rotatably mounted in the rotatable nose portion 14. The elevator control surfaces 16 and 17 have a common pivotal axis and are arranged to be pivoted about the axis by an actuator mechanism comprising a pair of solenoid coils 21 and 22 which are arranged coaxally on the longitudinal axis of the missile and are spaced apart so as to receive in the gap between them an armature disc 23 which is fixedly mounted on the rear end of a hollow shaft 24 lying on the longitudinal axis of the missile and extended forwardly into the rotatable nose portion 14 and terminating at the forward end in a spool 25 rotatably mounted thereon by bearings 26, and the solenoid coils 21 and 22 are so wound and adapted to be alternately energised that the armature disc 23 is pulled within the gap to the one or other or the coils and causes a longitudinal displacement of the shaft 24 and a corresponding displacement of the spool 25.
    The aileron control surfaces 18 and 19 are likewise pivotal about a common lateral axis and are controlled by an actuator mechanism comprising a pair of solenoid coils 27 and 28 fixedly mounted in spaced relation in the fixed nose portion 13 and coaxial with the longitudinal axis of the missile and an armature disc 29 concentric with the coils and arranged in the gap between them. The disc 29 is fixedly on the end of a sleeve 30 within which the hollow shaft 24 is slideably and rotatably mounted, and the sleeve 30 is itself slideably and rotatably mounted in a supporting framework 31 of the fixed nose portion 13 and projects at its forward end into the rotatable nose portion 14, terminating in a spool 32 rotatably mounted on its forward end by bearings 33.The solenoid coils 27 and 28 are likewise so wound and energised alternately that the armature disc 29 is pulled within the gap to the one or the other of the coils and causes a longitudinal displacement of the sleeve 30 and a corresponding displacement of the spool 32.
    Referring particularly to Fig. 3 the elevator control surface 16 is provided with an inwardly extending boss 34 which carries a curved pin 35 which engages in the peripheral groove in the spool 25, and elevator control surface 17 is likewise provided with a bush and curved pin the latter of which engages in the groove in the spool 25 on the same side as that of the pin 35 so that longitudinal displacement of the spool 25 results in a pivoting movement of the control surfaces 16 and 17 in the same sense.
    Referring particularly to Fig. 4, the aileron control surface 18 is provided with an inwardly directed boss 36 carrying a curved pin 37 which is arranged to engage in the peripheral groove in the spool 32 and the aileron control surface 19 is likewise provided with a bush and curved pin the latter of which is arranged to engage in the groove in the spool 32 on the side opposite that engaged by the pin 37 so that displacement of the spool 32 along the longitudinal axis of the missile results in the pivoting movement of the control surfaces 18 and 19 in opposite senses.
    The rotatable nose portion of the missile carries a free gyroscope 38 which is arranged to generate signals representative of the roll attitude of the nose portion ] 4, on a potentiometer 39 and these signals are fed along a signal carrying lead 40 which passes through the hollow shaft 24 to a slip ring assembly 41.
    In the control system described and claimed in our copending British patent application No.
    7298/63 (Specification No 1605400) signals for controlling the operation of the elevator and aileron control surfaces are transmitted from a ground station and received by a receiver mounted in the main body 12 of the missile, and these signals are employed to operate switches for alternately energising the coils 21, 22, 27 and 28 and the control is made such that the aileron control surfaces 18 and 19 are operated to being the rotatable nose portion to a predetermined roll attitude in space and the elevator control surfaces 16 and 17 operated to produce a lateral steering thrust on the missile.
    What we claim is: 1. A missile comprising a rotatable portion arranged for rotation about a predetermined axis relative to another portion of the missile, first and second control members on said rotatable portion for separate actuation by first and second actuator mechanisms movable in response to the energisation of first and second electromagnetic coils forming part of the mechanisms and contained in the said other portion of the missile said coils being mounted in spaced relation in the said other portion along the rotary axis of the said rotatable portion and concentric with respect thereto, with the first coil nearer to the rotatable portion than the second coil, the first actuator mechanism comprising an axially movable sleeve co-axial with the rotary axis and extending at one end into the rotatable portion and at the other end carrying an armature disc mounted concentrically with respect to the sleeve and in cooperating relation with the first coil which upon energisation causes the disc and the sleeve to move axially to effect actuation of the first control member, and the second actuator mechanism comprising an axially movable shaft coaxial with the rotary axis and slidable within the sleeve, said shaft extending beyond said sleeve at each end, one end of the shaft extending into the rotatable portion of the missile and the other end carrying a further armature disc concentric with the shaft and arranged in cooperating relation with the second coil which upon energisation causes the further disc and the shaft to move axially to effect actuation of the second control member.
  2. 2. A missile according to claim 1, wherein the
    sleeve and the associated armature disc as well as the shaft and its associated armature disc are rotatable about the rotary axis of the rotatable portion of the missile.
  3. 3. A missile according to claim 1 or 2, wherein a spool is provided on the end of the shaft and a further spool on the end of the sleeve each spool being co-axial with the rotary axis of the rotatable portion and being engaged by a pin which is carried by the associated control member, said pin being engaged in a peripheral groove in the spool and being constrained thereby to follow the axial displacement of the spool whilst rotating with the rotatable portion.
  4. 4. A missile according to claim 3, wherein the spools are rotatably mounted on the ends of the shaft and sleeve.
  5. 5. A missile according to claim 3 or 4 wherein said first and second members are first and second aerodynamic control surfaces pivotally mounted on the rotatable portion of the missile for pivotal movement about lateral axes and wherein the pin engaging one of the spools is carried by a supporting shaft for one of the control surfaces in such a manner that axial displacement of the spool causes a pivotal turning movement of the control surface, and wherein the pin engaging the other spool is carried by a supporting shaft for the other control surface in such a manner that axial displacement of the other spool causes a pivotal turning movement of the said other control surface.
  6. 6. A missile according to claim 5, wherein the second control surface serves as an elevator in cooperation with a fourth control surface arranged on the rotatable portion for pivotal movement about the same lateral axis as the second control surface, and wherein the forth surface carries a pin which engages in the groove in the spool engaged by the pin actuating the second control surface, on the same side of the spool as the pin actuating the second control surface, the arrangement being such that axial displacement of the spool causes a pivotal turning movement of the second and forth control surfaces in the same sense.
  7. 7. A missile according to claim 6, wherein the first control surface serves as an aileron in cooperation with a third control surface arranged on the rotatable portion for pivotal movement about the same lateral axis as the first control surface, and wherein the third control surface is arranged to carry a pin which engages in the groove in the spool engaged by the pin actuating the first control surface, on the side of the spool opposite to that engaged by the pin actuating the first control surface, the arrangement being such that an axial displacement of the spool causes pivotal turning movement of the first and third control surfaces in opposite senses.
  8. 8. A missile according to any of the preceding claims, wherein said shaft is hollow and wherein an electrical lead is arranged to pass through the hollow shaft for conducting electrical current between the rotatable portion and the other portion of the missile.
  9. 9. A missile according to claim 8, wherein said rotatable portion includes a space-stabilised gyroscope adapted to generate an electrical signal representative of the roll attitude of the rotatable portion with respect to a datum attitude, and wherein said signal is conducted to the said other portion of the missile by said electrical lead.
  10. 10. A missile substantially as hereinbefore described with reference to the accompanying drawings.
GB33465A 1965-01-04 1965-01-04 Improvements relating to control systems for missiles Expired - Lifetime GB1605396A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB33465A GB1605396A (en) 1965-01-04 1965-01-04 Improvements relating to control systems for missiles
AU67424/65A AU658814B2 (en) 1965-01-04 1965-12-02 Improvements relating to control systems for missiles
CA 947030 CA1336084C (en) 1965-01-04 1965-12-06 Missile control system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB33465A GB1605396A (en) 1965-01-04 1965-01-04 Improvements relating to control systems for missiles

Publications (1)

Publication Number Publication Date
GB1605396A true GB1605396A (en) 1995-04-26

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ID=9702571

Family Applications (1)

Application Number Title Priority Date Filing Date
GB33465A Expired - Lifetime GB1605396A (en) 1965-01-04 1965-01-04 Improvements relating to control systems for missiles

Country Status (3)

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AU (1) AU658814B2 (en)
CA (1) CA1336084C (en)
GB (1) GB1605396A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2762080A1 (en) * 1997-04-15 1998-10-16 Tda Armements Sas MICRO-GOVERNOR DEVICE FOR CORRECTION OF ROTATION-STABILIZED AMMUNITION TRAJECTORY
JP2010078221A (en) * 2008-09-25 2010-04-08 Technical Research & Development Institute Ministry Of Defence Missile

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2762080A1 (en) * 1997-04-15 1998-10-16 Tda Armements Sas MICRO-GOVERNOR DEVICE FOR CORRECTION OF ROTATION-STABILIZED AMMUNITION TRAJECTORY
EP0872704A1 (en) * 1997-04-15 1998-10-21 Tda Armements S.A.S. Device for the micro-control of fins for correcting the trajectory of a spin-stabilised projectile
JP2010078221A (en) * 2008-09-25 2010-04-08 Technical Research & Development Institute Ministry Of Defence Missile

Also Published As

Publication number Publication date
AU658814B2 (en) 1995-05-04
AU6742465A (en) 1995-03-30
CA1336084C (en) 1995-06-27

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