US3233545A - Practice projectiles - Google Patents

Practice projectiles Download PDF

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Publication number
US3233545A
US3233545A US261950A US26195063A US3233545A US 3233545 A US3233545 A US 3233545A US 261950 A US261950 A US 261950A US 26195063 A US26195063 A US 26195063A US 3233545 A US3233545 A US 3233545A
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US
United States
Prior art keywords
projectile
end portion
parachute
hollow
forwardly
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
US261950A
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English (en)
Inventor
Heller Rudolf
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.)
Rheinmetall Air Defence AG
Original Assignee
Oerlikon Contraves AG
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Filing date
Publication date
Application filed by Oerlikon Contraves AG filed Critical Oerlikon Contraves AG
Application granted granted Critical
Publication of US3233545A publication Critical patent/US3233545A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/56—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of parachute or paraglider type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/22—Load suspension
    • B64D17/34—Load suspension adapted to control direction or rate of descent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/006—Guided missiles training or simulation devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B8/00—Practice or training ammunition
    • F42B8/12—Projectiles or missiles
    • F42B8/24—Rockets

Definitions

  • Such projectiles are quite expensive. When used for practice purposes they are identical with the real projectile except that they do not include the explosive charge which is carried by the real projectile. However, they do include such structures as the signal receiving equipment, the flight controlling fins, and the structure for translating the signals which are received into corresponding controls of these stabilizing fins so as to move the latter to give the projectile the desired direction of flight.
  • Such projectiles normally travel at a speed of from 60 to 150 kilometers per hour, and when travelling at such speed these projectiles are seriously injured when they fall to the ground and more often than not it is not worthwhile to repair them. As a result practicing with these projectiles is extremely expensive.
  • One of the objects of the present invention is to provide a practice projectile of the above type which will not be injured when it falls to the ground so that it can be used again and again and thus the great cost involved in the use of such practice projectiles as outlined above is avoided.
  • Another object of the present invention is to provide a projectile of the above type with a structure which will reliably cause a parachute connected to the projectile to become operative when the projectile falls toward the ground so as to prevent injury to the projectile.
  • the present invention includes a projectile, a projectile body portion to the front end of which a hollow end portion of the projectile is removably connected, this hollow front end portion forming the front end of the projectile and in accordance with the present invention a parachute is housed within the hollow front end portion of the projectile, this parachute being connected to the body portion.
  • the body portion of the projectile carries a means constructed in accordance with the present invention for removing the hollow front end portion of the projectile from the body portion of the latter while the projectile is in flight so as to release the parachute to the open air so that the parachute can expand and retard the falling of the projectile so as to prevent injury to the latter and thus enable the projectile to be used again.
  • FIG. 1 is a sectional elevational view of that part of a projectile which includes the structure of the invention.
  • FIGS. 2a-2f illustrate various stages in the operation of a projectile which includes the structure of the invention.
  • the projectile includes an elongated body portion 10 having a front end at which this body portion 10 is provided with a transverse wall 11.
  • the transverse wall 11 is formed with a central opening and fixedly carries a cylinder 12 which may be formed integrally with the wall, the central opening of the wall 11 forming the front end of the cylinder 12, as illustrated in FIG. 1.
  • the cylinder 12 is also open at its rear end where it is provided with outer threads.
  • a piston 13 is slidable within the cylinder 12 through the opening in the front wall 11. It will be noted that piston 13 is provided at its rear end with an outwardly directed annular flange adapted to engage the shoulder in the interior of the cylinder 12 just behind the wall 11 so that forward movement of the piston 13 is limited in this way.
  • a closure member 14 is removably connected to the cylinder 12 by being threaded onto the rear end of the latter, and this closure member 14 closes the rear end of the cylinder 12.
  • the closure member 14 carries at its inner face which is directed toward the interior of the cylinder 12 an explosive charge 15 in the form of any suitable cartridge carrying an explosive which will explode upon being ignited.
  • a detonator cap 17 is carried by the closure member 14 and is actuated through the electrical lead 18 which ignites the detonator cap to cause the charge 15 to become ignited.
  • the closure 14 carries a simple fuse 16 which may be ignited by the operator before the projectile is put into flight so that eventually when enough time goes by the fuse 16 will have burnt suificiently to cause the charge 15 to be ignited in this way.
  • the body portion 10 of the projectile includes an annular ring 19 threaded onto the wall 11 in the manner shown in FIG. 1 and having a forwardly extending cylindrical wall portion 19.
  • the annular member 19 is provided with a plurality of hooks 19" for a purpose pointed out below.
  • the projectile includes also a hollow front end portion or housing 21 shown in FIG. 1, this hollow front end portion or housing 21 shown in FIG. 1, this hollow front end portion 21 forming the front end of the projectile and being removably connected with the body portion 10 thereof.
  • the hollow front end portion 21 slips at its rear end onto the cylindrical portion 19 of the ring 19, and the rear end portion of the member 21 as well as the front end por tion of the part 19' re provided with aligned openings.
  • a plurality of shear pins 22 are located in these aligned openings, these shear pins being made of a relatively soft material so that the pins can be-sheared fairly easily when the front end portion 21 of the projectile is forcefully moved forwardly with respect to the body portion of the projectile.
  • a separating member 23 is located against a shoulder of the ring 19 at the inner surface of the wall 19 thereof, and this separating member 23 has a forwardly directed cylindrical portion engaging the rear end of the hollow front end portion 21.
  • the separating member 23 is located forwardly of the transverse wall 11 and is formed with a plurality of openings 23
  • a parachute Z8 is located within the hollow front end portion 21 of the projectile forwardly of the separating member 23 and the cords 26 of the parachute respectively extend through the openings 23' and are respectively hooked onto the hooks 19" of the ring 19.
  • FIGS. 2a-2f illustrate the use of the projectile.
  • the operator A manipulates a suitable control device B which acts through the leads C on the projectile I), this projectile during flight remaining electrically connected with the control device B through the leads C in a well known manner.
  • the operator A directs the projectile toward a suitable practice target and such a target is shown at B in FIG. 2.).
  • FIGS. and 2d illustrates the front end portion 21 when it is located at a substantial distance beyond the body portion 19 with the cords 26 extending between body portion ill and front end portion 21 but the parachute 23 still is located in the latter.
  • the housing 21, in which the parachute 28 is located is thrown forwardly from the body portion 10 while the parachute 28 remains in the hollow housing 21, and in fact the parachute 28 remains in the housing 21 until all of the cords 26 become taut, as illustrated in FIG. 20?, and it is only thereafter that the front end portion or housing 21 becomes separated from the parachute.
  • PEG. 20 illustrates the projectile with the front end portion 21 completely separated from the parachute.
  • the parachute 23 is acted upon by the stream of air so that it curves rearwardly in the manner shown in FIG.
  • the device instead of igniting the charge 15 at the will of the operator, it is possible to provide the device with a suitable timer which automatically ignites the charge 15 after passage of a predetermined period of time, or the fuse 16 may be ignited when the projectile is launched, this fuse 16 having such a length that a certain period of time is required for the fuse 16 to burn sufficiently to cause the charge 15 to become ignited.
  • the fuse 16 by its length talces over the function of the timer, and the fuse 16 may be ignited to guarantee ignition of the charge 15 in the event that the operator does not actuate the detonator 17 within a definite period of time.
  • the practice field in which the projectile moves may be provided with auxiliary devices operated by radio waves, for example, which automatically set off the charge 15 when the projectile reaches a predetermined area of the practice field.
  • the automatic signal transmitted in this way to the projectile while it is in flight so as to set off the charge 15 also can be set to actuate the projectile controls so as to automatically direct the projectile upwardly just before the charge 15 is ignited so that the projectile will have the proper attitude for the best operation of the parachute 28.
  • a hollow front end portion forming the front of the projectile; an elongated projectile unit constituting all except the front of the projectile, means removably fixing said projectile unit to said hollow front end portion at the rear end of the latter, said projectile unit extending rearwardly from said front end portion, the interior of said hollow front end portion communicating with said projectile unit; a parachute located in said front end and having elongated cords connected with said projectile unit; and means between said front end portion and said projectile unit and cooperating with said hollow front end portion and driving the latter forwardly from the projectile unit while the projectile is in flight to place said cords in a taut condition before the hollow front end portion releases the parachute which then opens to retard the falling of the projectile unit to prevent injury to the latter so that it may be used again.
  • a hollow front end port-ion forming the front end of the projectile and an elongated projectile unit forming the remainder of the projectile and extending rearwardly from said hollow front end portion; means rem-ovably connecting said projectile unit to said hollow front end portion; a parachute located in said hollow front end portion and connected with said projectile unit through elongated cords of the parachute; an explosive charge carried by said projectile unit; means operatively connected to said charge for igniting the same while the projectile is in flight; and means interposed between said charge and said hollow front end portion for applying the force of the ignited charge to said hollow front end portion for driving the latter forwardly from said projectile unit to place the cords of the parachute in a taut condition and then to release the parachute from the hollow front end portion, the parachute then opening and retarding the falling of the projectile unit to prevent injury to the latter so that it may be used again.
  • an elongated projectile body portion having a front end and provided at said front end with a wall extending transversely across the projectile; .a piston carried by said wall for movement forwardly beyond the wall; an explosive charge removably carried by said wall behind said piston for moving the piston forwardly with respect to said wall when said charge is ignited; means operatively connected to said charge for igniting the same when the projectile is in flight; a hollow front end portion forming the front end of the projectile; means removably connecting said front end portion to said body portion of the projectile at the front end of said body portion, said hollow front end port-ion being located forwardly of and spaced from said wall; and a separating member located forwardly of said wall between the latter and said hollow front end portion and engaging said front hollow end portion, said separating member being located in the path of movement of said piston so that the piston will drive said separating member forwardly to separate said hollow front end portion from said body portion of said projectile, said separating member being
  • a projectile body portion having a front end and provided at said front end with a transverse wall; a piston carried by said wall for movement forwardly with respect to the latter; an explosive charge removably carried by said wall behind said piston for moving the piston forwardly when said charge is ignited; means operatively connected to said charge for igniting the same when the projectile is in flight; a hollow front end portion forming the front end of the projectile and engaging and extending forwardly from said body portion; a plurality of shear pins connecting said hollow front end portion and said body portion so that when said pins are sheared the hollow front end portion will be separated from said body portion; a separating member located between said wall and hollow front end portion and engaging the front end portion, said separating member being located in the path of movement of said piston when the latter is moved upon ignition of said charge so that said separating member will drive said hollow front end portion forwardly with respect to said body portion to shear said pins and separate said hollow front end portion from said body portion,
  • a projectile body portion having a front end and provided at said front end with a transverse wall extending transversely across the body portion, said transverse wall being formed with a central opening and said transverse wall having connected therewith a cylinder extending rearwa-rdly from said transverse wall and axially aligned with said opening so that the opening forms the front end of said cylinder, said cylinder having an open rear end also; a piston slidable in said cylinder for movement forwardly beyond said wall; a closure member removably connected with said cylinder at the rear end of the cylinder for closing said rear end; an explosive charge carried by said closure member in the interior of said cylinder when said closure member closes said cylinder, so that when said charge is ignited said piston will be driven forwardly; ignition means carried by said closure member and operatively connected to said charge for igniting said charge while the projectile is in flight; a separating member carried by said body portion forwardly of said wall thereof in the path of movement of said
  • a hollow front end portion forming the front of the projectile; an elongated projectile unit constituting all except the front of the projectile and fixed removably to said hollow front end portion at the rear end of the latter and extending rearwardly therefrom, the interior of said hollow front end portion communicating with said projectile unit; a parachute located in said front end portion; cords connecting said parachute only to said projectile unit;
  • a projectile unit having a front end portion and constituting almost the entire projectile; a hollow housing constituting the remainder of said projectile and having an open rear end; means removably connecting said rear end of the housing to said front end portion of said projectile unit so that said housing is coaxial-1y arranged with the projectile unit and projects forwardly therefrom; a separating member located in said front end portion of said projectile unit and engaging said rear end of said housing, said separating member being formed with openings passing therethrough; a folded parachute located in said hollow housing and having cords extending through said openings in said separating member and being connected to said projectile unit; means including an explosive charge carried in said front end portion of said projectile unit rearwardly of said separating member for exerting, when said charge is exploded, a blow in axial forward direction directly on said separating member so that the separating member will be driven forwardly to separate said housing from said front end portion of said projectile unit; and means operatively connected to said charge for explo

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
US261950A 1958-09-29 1963-02-27 Practice projectiles Expired - Lifetime US3233545A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH6445558A CH374910A (de) 1958-09-29 1958-09-29 Rakete mit Bergungsfallschirm

Publications (1)

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US3233545A true US3233545A (en) 1966-02-08

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US261950A Expired - Lifetime US3233545A (en) 1958-09-29 1963-02-27 Practice projectiles

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US (1) US3233545A (ko)
BE (1) BE582772A (ko)
CH (1) CH374910A (ko)
DE (1) DE1097320B (ko)
FR (1) FR1244485A (ko)
GB (1) GB899496A (ko)
NL (1) NL242530A (ko)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014037189A1 (de) * 2012-09-06 2014-03-13 Rheinmetall Waffe Munition Gmbh, Patente AUS EINER TRAGBAREN, RÜCKSTOßFREIEN WAFFE VERSCHIEßBARER LEUCHTMUNITIONSKÖRPER
US10458765B2 (en) 2016-04-06 2019-10-29 Bae Systems Bofors Ab Parachute device for divisible shell
CN112319866A (zh) * 2020-07-16 2021-02-05 西安航天化学动力有限公司 一种民用火箭的活塞式回收装置

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785557A (en) * 1972-12-21 1974-01-15 Colspan Environmental Syst Inc Cloud seeding system
US5347931A (en) * 1992-11-12 1994-09-20 Thiokol Corporation Combustible flare ignition system
US5386781A (en) * 1992-11-12 1995-02-07 Thiokol Corporation Parachute deployment system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1011002A (en) * 1911-05-17 1911-12-05 Krupp Ag Search-light projectile.
US1434784A (en) * 1922-06-20 1922-11-07 V M L Ex Ltd Shell
US1774535A (en) * 1929-06-19 1930-09-02 Wiley Samuel Aerial bomb or flare
US2606495A (en) * 1947-09-30 1952-08-12 Kilgore Inc Pyrotechnic device
US2841084A (en) * 1954-08-30 1958-07-01 Orville H Carlisle Toy rocket
US2945442A (en) * 1958-01-02 1960-07-19 Barnet R Adelman Explosive separation device
US3068792A (en) * 1959-03-06 1962-12-18 Herbert D Brown Rocket-like aerial toy

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1011002A (en) * 1911-05-17 1911-12-05 Krupp Ag Search-light projectile.
US1434784A (en) * 1922-06-20 1922-11-07 V M L Ex Ltd Shell
US1774535A (en) * 1929-06-19 1930-09-02 Wiley Samuel Aerial bomb or flare
US2606495A (en) * 1947-09-30 1952-08-12 Kilgore Inc Pyrotechnic device
US2841084A (en) * 1954-08-30 1958-07-01 Orville H Carlisle Toy rocket
US2945442A (en) * 1958-01-02 1960-07-19 Barnet R Adelman Explosive separation device
US3068792A (en) * 1959-03-06 1962-12-18 Herbert D Brown Rocket-like aerial toy

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014037189A1 (de) * 2012-09-06 2014-03-13 Rheinmetall Waffe Munition Gmbh, Patente AUS EINER TRAGBAREN, RÜCKSTOßFREIEN WAFFE VERSCHIEßBARER LEUCHTMUNITIONSKÖRPER
US10458765B2 (en) 2016-04-06 2019-10-29 Bae Systems Bofors Ab Parachute device for divisible shell
CN112319866A (zh) * 2020-07-16 2021-02-05 西安航天化学动力有限公司 一种民用火箭的活塞式回收装置

Also Published As

Publication number Publication date
GB899496A (en) 1962-06-27
NL242530A (ko)
BE582772A (fr) 1960-01-18
DE1097320B (de) 1961-01-12
CH374910A (de) 1964-01-31
FR1244485A (fr) 1960-09-19

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