US3548707A - Missile roll compensation device - Google Patents
Missile roll compensation device Download PDFInfo
- Publication number
- US3548707A US3548707A US882254A US3548707DA US3548707A US 3548707 A US3548707 A US 3548707A US 882254 A US882254 A US 882254A US 3548707D A US3548707D A US 3548707DA US 3548707 A US3548707 A US 3548707A
- Authority
- US
- United States
- Prior art keywords
- missile
- roll
- launcher
- compensation device
- roll compensation
- 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
- 239000007789 gas Substances 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000003467 diminishing effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/048—Means for imparting spin to the rocket before launching
Definitions
- This invention relates to the field of missile launchers.
- the missile In firing missiles from a rifled gun tube launcher, the missile develops a roll far in excess of that which the missile can functionally overcome during the flight of the missile to a target.
- This roll is developed by escape of pressurized gases of combustion through the rifling grooves of tube launcher. The gases engage the skin of the missile and by friction impart rotation to the missile in the direction of the rifling helix. Contact with the gases escaping in the grooves occurs along the entire cylindrical length of the missile.
- the gyrostabilizer of the missile is inadequate to cope with the rate of rotation imparted to the missiles by the escaping gases.
- This invention provides a solution to the problem by the inclusion of a counter roll compensating apparatus located between the missile and the missile cap.
- the apparatus will impart an 8 to l2 roll to the missile in the direction opposite to compensated roll developed due to the gun tube rifling during the rest of the missile travel in the tube.
- the now compensated missile roll will be within the limits that can be functionally controlled by the gyrostabilizer.
- the use of the invention will eliminate fatigue cracking of the gun tube launcher.
- FIG. 1 shows the apparatus on a missile in a rifled gun tube.
- FIG. 2 shows the helical groove located in the missile cap.
- Reference numeral 1 indicates a rifled gun tube launcher having rifling grooves 3 therein.
- the launcher includes a device 5 for closing the breech of the launcher.
- a missile aft shroud 7 is shown having a protuberance 9 on the outer surface thereof.
- a missile cap 11 encloses the shroud and includes a helical groove 13 for engagement with said protuberance for imparting a counterroll correction to the missile when fired.
- the missile cap also includes a flange 15 for engaging a shoulder 17 of the gun tube launcher. When device 5 is closed, member 19 will cause the cap to be secured to shoulder 17.
- protuberance 9 is in engagement with groove 13 and follows the groove to its end.
- the cooperation between the protuberance and the groove will impart to the missile an 8 to 12 roll.
- This imparted roll will offset the rotation imparted to the missile by the frictional contact of the combustion gases escaping forwardly through the rifling grooves. Therefore the compensating apparatus al lows the missile to exit the rifled gun tube launcher with a roll that is functionally controlled during the flight of the missile to its target.
- groove and protuberance While only one groove and protuberance is shown, a plurality of grooves and protuberances may be used if desired.
- a roll-compensating apparatus comprising a rifled gun tube launcher having a device for closing the breech of the launcher, a missile engaging the lands of the rifling whereby the gases of combustion escape forwardly through the rifling grooves and by frictional engagement with the skin of the missile impart a rotation to the missile in the direction of the rifling helix, a shroud located on the aft end of the missile including a protuberance and a cap disposed for secured engagement between the breech device and the launcher tube,
Description
United States Patent 72] Inventor James G. Hughes Madison, Ala. [21 Appl. No. 882,254 [22] Filed Dec. 4, 1969 Continuation-impart of Ser. No. 787,411, Dec. 27, 1968, abandoned [45] Patented Dec. 22, 1970 [73] Assignee the United States 01' America as represented by the Secretary of the Army [54] MISSILE ROLL COMPENSATION DEVICE 1 Claim, 2 Drawing Figs.
[52] US. Cl 89/l.8; 102/343, 102/38; 89/1816 [51] hit. F411'3/04 [50] Field of Search 89/1 1.8, 1.813, 1.816; 102/38. 34.3
[56] References Cited UNITED STATES PATENTS 2,884,859 5/1959 Alexander et a1 102/38 Primary Examiner-Samuel W. Engle Attorneys-Harry M. Saragovitz, Edward J. Kelly, Herbert Her] and Charles R. Carter ABSTRACT: A missile roll-compensating apparatus for imparting a roll correction to a missile fired from a rifled gun tube launcher having a device for closing the breech of the launcher. This apparatus imparts the roll correction at the initial phase of missile launching and the correction is applied in a direction opposite to the spin developed by the missile during the remainder of the missiles travel in the rifled launcher. The apparatus includes a missile cap telescoped over the aft shroud of a missile. A helical groove is located in one of these members and a protuberance is located on the other member for engagement with the helical groove, thus materially diminishing the roll of the missile as it leaves the tube.
MISSILE ROLL COMPENSATION DEVICE This is a continuation-in-part of Pat. application Ser. No. 787,411, filed Dec. 27, 1968, now abandoned.
BACKGROUND OF THE INVENTION This invention relates to the field of missile launchers. In firing missiles from a rifled gun tube launcher, the missile develops a roll far in excess of that which the missile can functionally overcome during the flight of the missile to a target. This roll is developed by escape of pressurized gases of combustion through the rifling grooves of tube launcher. The gases engage the skin of the missile and by friction impart rotation to the missile in the direction of the rifling helix. Contact with the gases escaping in the grooves occurs along the entire cylindrical length of the missile. The gyrostabilizer of the missile is inadequate to cope with the rate of rotation imparted to the missiles by the escaping gases.
SUMMARY OF THE INVENTION This invention provides a solution to the problem by the inclusion of a counter roll compensating apparatus located between the missile and the missile cap. The apparatus will impart an 8 to l2 roll to the missile in the direction opposite to compensated roll developed due to the gun tube rifling during the rest of the missile travel in the tube. At the time the missile exits the tube launcher, the now compensated missile roll will be within the limits that can be functionally controlled by the gyrostabilizer. The use of the invention will eliminate fatigue cracking of the gun tube launcher.
This invention may be better understood from the following detailed description taken in conjunction with the accompanying drawing.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 shows the apparatus on a missile in a rifled gun tube. FIG. 2 shows the helical groove located in the missile cap.
Reference numeral 1 indicates a rifled gun tube launcher having rifling grooves 3 therein. The launcher includes a device 5 for closing the breech of the launcher. A missile aft shroud 7 is shown having a protuberance 9 on the outer surface thereof. A missile cap 11 encloses the shroud and includes a helical groove 13 for engagement with said protuberance for imparting a counterroll correction to the missile when fired. The missile cap also includes a flange 15 for engaging a shoulder 17 of the gun tube launcher. When device 5 is closed, member 19 will cause the cap to be secured to shoulder 17.
As the missile in initially launched, protuberance 9 is in engagement with groove 13 and follows the groove to its end. The cooperation between the protuberance and the groove will impart to the missile an 8 to 12 roll. This imparted roll will offset the rotation imparted to the missile by the frictional contact of the combustion gases escaping forwardly through the rifling grooves. Therefore the compensating apparatus al lows the missile to exit the rifled gun tube launcher with a roll that is functionally controlled during the flight of the missile to its target.
While only one groove and protuberance is shown, a plurality of grooves and protuberances may be used if desired.
lclaim:
1. A roll-compensating apparatus comprising a rifled gun tube launcher having a device for closing the breech of the launcher, a missile engaging the lands of the rifling whereby the gases of combustion escape forwardly through the rifling grooves and by frictional engagement with the skin of the missile impart a rotation to the missile in the direction of the rifling helix, a shroud located on the aft end of the missile including a protuberance and a cap disposed for secured engagement between the breech device and the launcher tube,
counter rotation to the missile when fired.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US88225469A | 1969-12-04 | 1969-12-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3548707A true US3548707A (en) | 1970-12-22 |
Family
ID=25380212
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US882254A Expired - Lifetime US3548707A (en) | 1969-12-04 | 1969-12-04 | Missile roll compensation device |
Country Status (1)
Country | Link |
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US (1) | US3548707A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4452124A (en) * | 1983-03-10 | 1984-06-05 | Ford Aerospace & Communications Corporation | Stabilizing tab for missile launcher |
US4646618A (en) * | 1982-04-05 | 1987-03-03 | Dynamit Nobel Aktiengesellschaft | Launching tube for missiles |
-
1969
- 1969-12-04 US US882254A patent/US3548707A/en not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4646618A (en) * | 1982-04-05 | 1987-03-03 | Dynamit Nobel Aktiengesellschaft | Launching tube for missiles |
US4452124A (en) * | 1983-03-10 | 1984-06-05 | Ford Aerospace & Communications Corporation | Stabilizing tab for missile launcher |
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