US3398916A - Device for correcting the trajectory of projectiles and the so-equipped projectiles - Google Patents
Device for correcting the trajectory of projectiles and the so-equipped projectiles Download PDFInfo
- Publication number
- US3398916A US3398916A US646899A US64689967A US3398916A US 3398916 A US3398916 A US 3398916A US 646899 A US646899 A US 646899A US 64689967 A US64689967 A US 64689967A US 3398916 A US3398916 A US 3398916A
- Authority
- US
- United States
- Prior art keywords
- projectile
- trajectory
- projectiles
- auxiliary
- speed
- 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
Links
Images
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
- F41G7/22—Homing guidance systems
- F41G7/222—Homing guidance systems for spin-stabilized 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
- F41G7/301—Details
- F41G7/305—Details for spin-stabilized missiles
-
- 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
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
Definitions
- a trajectory correcting device including an auxiliary projectile for a projectile rotating about its longitudinal axis along the trajectory thereof and comprising a remotely controllable detecting device.
- This invention relates to projectiles of the type comprising a remotely controllable detecting device, said projectile being rotated along its trajectory by its own characteristics or those of its launching means.
- the detecting device may be of any suitable type remotely controllable either by electromagnetic waves or by waves emitted from a source of coherent luminous waves (laser) or by infrared waves, e.g. those emitted by a motor exhaust and the like.
- laser coherent luminous waves
- infrared waves e.g. those emitted by a motor exhaust and the like.
- These waves may be emitted or reflected by the target or the shooter and generally they may reach the detecting device in any suitable manner.
- the object of the present invention is to cause the suitable intervening of a substantial lateral thrust capable of modifying almost instantaneously the trajectory of the projectile to bring it on the target.
- this solution is precarious 'due to, on one hand, the small value of the gas mass expelled with respect to the projectile mass and consequently the relatively small value of the resulting force system and, on the other hand, the way of applying said force.
- this lateral is applied in such manner that it results only in a torque causing the projectile to slant by rotating about its center of gravity, the resulting slant modifying progressively the trajectory owing to the aerodynamic characteristics of the projectile. Accordingly, the modification of the trajectory requires a relatively long time and the angular value of this modification may not be obtained with a suflicient accuracy.
- Another object of the invention is to make such device from a minimum number of constituting elements readily assembled, thereby allowing to reach relatively low cost prices with respect to the performances of the projectile.
- Still another object of the invention relates to a particular construction of such device offering a great resistance to lateral stresses when correcting the trajectory.
- the correcting device is characterized in that it comprises a make-up charge and an auxiliary projectile arranged in such manner that the resultant of the reaction forces created by the ejection of said auxiliary projectile is lateral, passes through or at close vicinity to the center of gravity of the projectile and is such that it may induce almost instantaneously a correction of the trajectory to bring the projectile on the target.
- the new trajectory of the main projectile is determined by the resultant of two orthogonal linear movements the first of which is caused by the propelling force of the main projectile, while the second movement results from the propelling force of the auxiliary projectile passing through or at close vicinity to the center of gravity of the said main projectile.
- auxiliary projectile will be injeoted substantially at the time of the detection and said time itself will correspond to such an angular position of the projectile that the speed vector of the auxiliary projectile is situated within or approximately within a plane including both the target and the longitudinal axis of the main projectile.
- the speed vector of the auxiliary projectile may be also situated within a plane slightly diiferent from that just described above to take account of surrounding factors such as, for instance, the time necessary for ejecting the auxiliary projectile, the shifting of the target and the like.
- the projectile provided with the device according to the invention will be correlatively conditioned by any suitable means providing for such constant speed.
- the projectile will be provided with a flight motor to define accurately the angular amplitude of the trajectory correction resulting from the combination of said speed with the transverse speed imparted by the lateral thrust.
- the flight motor will be such that the thrust with which it actuates the projectile, is approximately equal to the resistance to the advance of the projectile relatively to its initial speed.
- trajectory correcting device for a projectile and a so equipped projectile will be described hereafter in their essential elements with reference to the enclosed drawings wherein:
- FIGURE 1 shows very diagrammatically a longitudinal section of a projectile and the correcting device according to the invention
- FIGURE 2 shows a section taken on the line IIII of FIGURE 1;
- FIGURE 3 shows diagrammatically the correcting process resulting from the device and the projectile according to the invention.
- the chamber 6 houses the charge, generally a hollow charge represented at 9.
- Chamber 7 houses a suitable device providing for the flight speed of the projectile.
- this device comprises a flight motor represented in 10.
- the cross-piece 8 has a blind hole 11 the longitudinal axis of which merges with the said axis A-A.
- Said blind hole houses at least a priming element or device 12, a charge 13, an auxiliary projectile, namely a plug 14 and a lid 15.
- the highly resistant body is preferably reinforced by any suitable means in the plane of the lateral thrust.
- the tubular element will have an increasing thickness from its ends or at a distance from its ends 1617 and in the direction of the cross-piece 8. Similarly, the bottom of the said blind hole 11 will be conditioned or shaped to present a great resistance. W
- the head 3 will comprise a detecting device 18 which will be selected in accordance with the used detecting way, i.e. the nature of the waves of the emitter.
- the head 3 will be generally provided with a conventional protecting cap 19 having a spherical, ogival or similar shape. According to conditions, a transparent or opaque material will be selected but, in any case, said material will be permeable to the waves having to reach or operate the detecting device represented in 18.
- the fins 4 will be also shaped and conditioned in any suitable manner.
- the detecting device or the projectile provided therewith will operate substantially as follows: the projectile 1 is brought as accurately as possible to bear on a point adjacent to the target. At a point of the trajectory of the projectile 1, the detecting device 18 is remotely energized by a known means, e.g. by directing directly a train or a beam of waves thereto or by reflecting said waves, e.g. from the target or in any other manner. At that time, as diagrammatically represented in FIGURE 3, the projectile 1 is subjected simultaneously to the flight speed before the lateral thrust represented by the vector V1 and at a complementary speed indicated by vector W2 and resulting from the relative speed of the auxiliary projectile 14 indicated by vector W1. Accordingly, the projectile 1 is then subjected to a resulting speed indicated by vector V2 which must be tangential to a trajectory represented in t passing through the target 0 or at close vicinity of the latter.
- a known means e.g. by directing directly a train or a beam of waves thereto or by reflecting said
- the detecting device 18 will be necessarily energized, i.e. that also the charge 13 for propelling the auxiliary projectile 14 will be fired when the vector W1 representing the speed of the auxiliary projectile lies within or approximately within a plane including both the longitudinal axis BB of the projectile 1 and the target 0.
- the projectile according to the invention provides a very great shooting accuracy.
- the principal parameters having an influence upon the precision may be predetermined with sufficient accuracy, provided of course that the launching arm has been correctly aimed.
- the angle at which the detecting device 8 may see the target is known and the value of said angle makes possible to a determination of the angular value of the correction being given to the trajectory of the projectile, the speed of the latter being constant and known.
- this correction may be reproduced with sufiicient accuracy since the resultant of the reaction forces acting upon the center of gravity G of the projectile at the time of the ejection of the auxiliary projectile is known within sufiicient limits, said center of gravity G being shifted in a very short time.
- the thrust of the flight motor is selected to be equal or practically equal to the resistance to advance of the projectile relatively to its initial speed. Of course, this makes it possible to maintain the angle of lateral correction (angle of lateral thrust) constant for every flight state.
- this invention covers any detection projectile using the foregoing characteristics as well as the projectile parts specially conditioned therefor.
- a projectile comprising an elongated tubular body, a hollow head carried by one end of said body, a detecting device within said head, a central cross piece located within said body between the ends thereof and dividing the interior of the body into a front chamber and a rear chamber, said cross piece having a blind hole the longitudinal axis of which extends at right angles to the longitudinal axis of said body, a charge within said front chamber, a flight motor within said rear chamber for maintaining constant the speed of the projectile, a priming element in said hole, an auxiliary charge in said hole controlled by said detecting device, and an auxiliary projectile in said hole substantially in the center of gravity of the projectile, whereby resultant reaction forces caused by the lateral ejection of said auxiliary projectile pass through said center of gravity.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE683586 | 1966-07-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3398916A true US3398916A (en) | 1968-08-27 |
Family
ID=3849029
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US646899A Expired - Lifetime US3398916A (en) | 1966-07-04 | 1967-06-19 | Device for correcting the trajectory of projectiles and the so-equipped projectiles |
Country Status (9)
Country | Link |
---|---|
US (1) | US3398916A (xx) |
AT (1) | AT278594B (xx) |
BE (1) | BE683586A (xx) |
CH (1) | CH469242A (xx) |
ES (1) | ES342471A1 (xx) |
GB (1) | GB1193304A (xx) |
IL (1) | IL28154A (xx) |
NL (1) | NL6708669A (xx) |
SE (1) | SE348829B (xx) |
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2091901A2 (xx) * | 1970-04-10 | 1971-01-21 | Etu Realisa Electronique | |
FR2167608A1 (xx) * | 1972-01-03 | 1973-08-24 | Ship Systems Inc | |
US4160415A (en) * | 1978-05-05 | 1979-07-10 | The United States Of America As Represented By The Secretary Of The Army | Target activated projectile |
US4374495A (en) * | 1977-09-17 | 1983-02-22 | Thomanek Franz R | Warhead for antitank missiles featuring a shaped charge |
WO1983003894A1 (en) * | 1982-04-21 | 1983-11-10 | Hughes Aircraft Company | Terminally guided weapon delivery system |
DE3911576A1 (de) * | 1989-04-08 | 1990-10-11 | Rheinmetall Gmbh | Fluegelstabilisiertes geschoss |
US5261629A (en) * | 1989-04-08 | 1993-11-16 | Rheinmetall Gmbh | Fin stabilized projectile |
US5880396A (en) * | 1992-03-27 | 1999-03-09 | Zacharias; Athanassios | Process for guiding a flying object and flying objects |
WO2000052414A1 (en) * | 1999-03-03 | 2000-09-08 | Linick James M | Impulse motor to improve trajectory correctable munitions |
WO2001090682A1 (en) * | 2000-05-25 | 2001-11-29 | Metal Storm Limited | Directional control of missiles |
US6502785B1 (en) * | 1999-11-17 | 2003-01-07 | Lockheed Martin Corporation | Three axis flap control system |
US6722609B2 (en) * | 1998-02-13 | 2004-04-20 | James M. Linick | Impulse motor and apparatus to improve trajectory correctable munitions including cannon launched munitions, glide bombs, missiles, rockets and the like |
US20050269456A1 (en) * | 2003-08-29 | 2005-12-08 | Smiths Aerospace, Inc. | Stabilization of a drogue body |
AU2002210130B2 (en) * | 2000-05-25 | 2006-06-08 | Metal Storm Limited | Directional control of missiles |
US20060226293A1 (en) * | 2005-02-25 | 2006-10-12 | Smiths Aerospace Llc | Optical tracking system for refueling |
US7377468B2 (en) * | 2003-08-29 | 2008-05-27 | Smiths Aerospace Llc | Active stabilization of a refueling drogue |
US8084725B1 (en) * | 2008-05-01 | 2011-12-27 | Raytheon Company | Methods and apparatus for fast action impulse thruster |
RU2443968C2 (ru) * | 2009-03-19 | 2012-02-27 | Николай Евгеньевич Староверов | Противовертолетная и противостелсовая ракета |
US10615547B2 (en) | 2016-09-08 | 2020-04-07 | Raytheon Company | Electrical device with shunt, and receptacle |
US10662898B2 (en) | 2016-09-08 | 2020-05-26 | Raytheon Company | Integrated thruster |
CN112199635A (zh) * | 2020-10-17 | 2021-01-08 | 中国人民解放军63876部队 | 一种火箭橇运动弹道计算修正方法 |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USRE32094E (en) * | 1979-11-09 | 1986-03-25 | Avco Corporation | Overflying munitions device and system |
GB2370342B (en) * | 1981-11-05 | 2002-11-20 | Emi Ltd | Terminally - corrected sub-munitions |
GB2251834B (en) * | 1983-02-22 | 1992-12-16 | George Alexander Tarrant | Guided missiles |
DE3345529C1 (de) * | 1983-12-16 | 1999-09-02 | Diehl Stiftung & Co | Zielsuchende Munition mit vor ihrer Gefechtsladung-Einlage angeordnetem Sensor-Wandler |
GB2250804B (en) * | 1990-11-07 | 1994-06-01 | Colebrand Ltd | Protective device for a sensing head |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2029491A (en) * | 1934-08-25 | 1936-02-04 | Technicraft Engineering Corp | Gun type formation tester |
US2258281A (en) * | 1938-05-20 | 1941-10-07 | Commercial Ingredients Corp | Aerial torpedo |
US3107617A (en) * | 1962-04-11 | 1963-10-22 | William F Loeper | Ring decoy launching mechanism |
US3141411A (en) * | 1957-06-19 | 1964-07-21 | Eltro G M B H & Co Ges Fur Str | Target finder for missiles |
-
1966
- 1966-07-04 BE BE683586D patent/BE683586A/xx unknown
-
1967
- 1967-06-18 IL IL28154A patent/IL28154A/en unknown
- 1967-06-19 CH CH863667A patent/CH469242A/fr unknown
- 1967-06-19 US US646899A patent/US3398916A/en not_active Expired - Lifetime
- 1967-06-19 AT AT569667A patent/AT278594B/de not_active IP Right Cessation
- 1967-06-19 SE SE08649/67A patent/SE348829B/xx unknown
- 1967-06-21 NL NL6708669A patent/NL6708669A/xx unknown
- 1967-06-21 GB GB28551/67A patent/GB1193304A/en not_active Expired
- 1967-06-30 ES ES342471A patent/ES342471A1/es not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2029491A (en) * | 1934-08-25 | 1936-02-04 | Technicraft Engineering Corp | Gun type formation tester |
US2258281A (en) * | 1938-05-20 | 1941-10-07 | Commercial Ingredients Corp | Aerial torpedo |
US3141411A (en) * | 1957-06-19 | 1964-07-21 | Eltro G M B H & Co Ges Fur Str | Target finder for missiles |
US3107617A (en) * | 1962-04-11 | 1963-10-22 | William F Loeper | Ring decoy launching mechanism |
Cited By (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2091901A2 (xx) * | 1970-04-10 | 1971-01-21 | Etu Realisa Electronique | |
FR2167608A1 (xx) * | 1972-01-03 | 1973-08-24 | Ship Systems Inc | |
US4374495A (en) * | 1977-09-17 | 1983-02-22 | Thomanek Franz R | Warhead for antitank missiles featuring a shaped charge |
US4160415A (en) * | 1978-05-05 | 1979-07-10 | The United States Of America As Represented By The Secretary Of The Army | Target activated projectile |
WO1983003894A1 (en) * | 1982-04-21 | 1983-11-10 | Hughes Aircraft Company | Terminally guided weapon delivery system |
DE3911576A1 (de) * | 1989-04-08 | 1990-10-11 | Rheinmetall Gmbh | Fluegelstabilisiertes geschoss |
US5261629A (en) * | 1989-04-08 | 1993-11-16 | Rheinmetall Gmbh | Fin stabilized projectile |
US5880396A (en) * | 1992-03-27 | 1999-03-09 | Zacharias; Athanassios | Process for guiding a flying object and flying objects |
US6722609B2 (en) * | 1998-02-13 | 2004-04-20 | James M. Linick | Impulse motor and apparatus to improve trajectory correctable munitions including cannon launched munitions, glide bombs, missiles, rockets and the like |
WO2000052414A1 (en) * | 1999-03-03 | 2000-09-08 | Linick James M | Impulse motor to improve trajectory correctable munitions |
US6502785B1 (en) * | 1999-11-17 | 2003-01-07 | Lockheed Martin Corporation | Three axis flap control system |
AU2002210130B2 (en) * | 2000-05-25 | 2006-06-08 | Metal Storm Limited | Directional control of missiles |
WO2001090682A1 (en) * | 2000-05-25 | 2001-11-29 | Metal Storm Limited | Directional control of missiles |
US6889935B2 (en) | 2000-05-25 | 2005-05-10 | Metal Storm Limited | Directional control of missiles |
US7377468B2 (en) * | 2003-08-29 | 2008-05-27 | Smiths Aerospace Llc | Active stabilization of a refueling drogue |
US20050269456A1 (en) * | 2003-08-29 | 2005-12-08 | Smiths Aerospace, Inc. | Stabilization of a drogue body |
US7275718B2 (en) | 2003-08-29 | 2007-10-02 | Smiths Aerospace Llc | Active control of a drogue body |
US7681839B2 (en) | 2005-02-25 | 2010-03-23 | Smiths Aerospace Llc | Optical tracking system for refueling |
US20080075467A1 (en) * | 2005-02-25 | 2008-03-27 | Smiths Aerospace Llc | Optical tracking system for airborne objects |
US20080067290A1 (en) * | 2005-02-25 | 2008-03-20 | Mickley Joseph G | Optical tracking system for airborne objects |
US20060226293A1 (en) * | 2005-02-25 | 2006-10-12 | Smiths Aerospace Llc | Optical tracking system for refueling |
US7686252B2 (en) * | 2005-02-25 | 2010-03-30 | Smiths Aerospace, Llc | Optical tracking system for airborne objects |
US20100163679A1 (en) * | 2005-02-25 | 2010-07-01 | Mickley Joseph G | Optical tracking system for airborne objects |
US8104716B2 (en) | 2005-02-25 | 2012-01-31 | Ge Aviation Systems Llc | Optical tracking system for airborne objects |
US8084725B1 (en) * | 2008-05-01 | 2011-12-27 | Raytheon Company | Methods and apparatus for fast action impulse thruster |
RU2443968C2 (ru) * | 2009-03-19 | 2012-02-27 | Николай Евгеньевич Староверов | Противовертолетная и противостелсовая ракета |
US10615547B2 (en) | 2016-09-08 | 2020-04-07 | Raytheon Company | Electrical device with shunt, and receptacle |
US10662898B2 (en) | 2016-09-08 | 2020-05-26 | Raytheon Company | Integrated thruster |
CN112199635A (zh) * | 2020-10-17 | 2021-01-08 | 中国人民解放军63876部队 | 一种火箭橇运动弹道计算修正方法 |
CN112199635B (zh) * | 2020-10-17 | 2024-03-29 | 中国人民解放军63876部队 | 一种火箭橇运动弹道计算修正方法 |
Also Published As
Publication number | Publication date |
---|---|
SE348829B (xx) | 1972-09-11 |
AT278594B (de) | 1970-02-10 |
DE1578139B1 (de) | 1971-12-23 |
IL28154A (en) | 1972-08-30 |
BE683586A (xx) | 1966-12-16 |
ES342471A1 (es) | 1968-07-16 |
NL6708669A (xx) | 1968-01-05 |
GB1193304A (en) | 1970-05-28 |
CH469242A (fr) | 1969-02-28 |
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