US2998752A - Missile launching ramp - Google Patents
Missile launching ramp Download PDFInfo
- Publication number
- US2998752A US2998752A US275500A US27550052A US2998752A US 2998752 A US2998752 A US 2998752A US 275500 A US275500 A US 275500A US 27550052 A US27550052 A US 27550052A US 2998752 A US2998752 A US 2998752A
- Authority
- US
- United States
- Prior art keywords
- missile
- ramp
- launching
- tracks
- shoes
- 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
- 238000010276 construction Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- 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
Definitions
- This invention relates to a launching ramp for winged missiles, and in particular to the track arrangement thereof which permits a missile to leave the ramp at relatively low speed without tip-01f.
- Another object of the invention is to provide a launching ramp for missiles which is most compact and affords a stabilizing effect to the missile for a satisfactory take-01f.
- a missile launching ramp with three tracks, engaging shoes attached to the missile. Two of the tracks are laterally spaced and disposed on top of the ramp structure, and the third track is positioned in the center of this structure and below the aforementioned tracks.
- the front ends of the upper tracks and the front end of the lower track are staggered longitudinally such a distance that in launching the front shoes and rear shoe of the missile disengage from the tracks substantially simultaneously. Because the missile is held on the tracks against lateral and vertical movement there will be no tip oif when it leaves the ramp.
- the operating length of the ramp can be made extremely short to insure, even below stalling speed of the missile, a satisfactory launching performance.
- FIG. 1 is a side view of one embodiment of the invention
- FIG. 2 is a plan view of the ramp structure
- FIG. 3 is a front view of FIG. 1,
- FIG. 4 is a cross-sectional view of the upper track structure, taken on line IVIV of FIG. 1.
- FIG. 5 is a cross-sectional view of the lower track structure, taken on line VV of FIG. 1.
- the numeral 1 indicates in general the longitudinal frame work girders of the launching ramp which are connected together by transverse structures 2 of suitable construction and by an end beam 3 carrying pivots 4 about which the ramp is tiltable for launching the missile 5, preferably with the wing folded as shown.
- the missile 5 is provided with a pair of lateral shoes 6 bearing on tracks 7 formed by the upper girder members and held in position by guides 8 and 9 secured to the tracks 7 by bolts 10.
- a shoe 11, extending from the bottom and towards the rear of missile 5 bears against a middle track 12 secured to some of the transverse structures 2 by bolts 13 and provided at both sides with guides 14 and 15 fastened by bolts :16 to the track 12.
- the front ends of the upper tracks 7 are staggered against the front end of the lower or middle track .12 a distance A equal to the longitudinal distance between the rear ends of the shoes 6 and the shoe 11, so
- a launching ramp with three tracks for guiding a missile at the sides and at the bottom center to prevent it from changing its upright position during contact with the launching ramp, but to simultaneously disengage all missile shoes from the tracks, so that the launching speed of the missile can be relatively low, even below its stalling speed and, thus, permit a launching ramp of unusually short length requiring least space.
- a self-energized missile a pair of longitudinal short guide shoes positioned on the forward portion of the missile, one shoe extending laterally on each side of the missile, a third longitudinally-short guide shoe connected to the bottom of the rear of the missile, a launching ramp slidably supporting the missile and including a pair of parallel rails slidably supporting a pair of guide shoes, a third rail positioned midway between and parallel to the parallel rails but below the plane thereof and slidably supporting the third guide shoe, the third rail terminating in a forward direction short of the forward end of the parallel rails, the distance between the termination of the third rail and the points of termination of the parallel rails being equal to the distance between the pair of guide shoes and the single shoe whereby the pair of guide shoes leave the parallel rails at the same time as the single guide shoe leaves its rail so that no turning moment exists on the missile to turn it out of line when it is launched.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
Sept. 5, 1961 R. J. COUTS MISSILE LAUNCHING RAMP Filed March 8, 1952 INVEN TOR. Robe/'2" J- Caufs ATTORNEY 2,998,752 NESSILE LAUNCHING RAMP Robert J. Coats, Akron, Ohio, assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Mar. 8, 1952, Ser. No. 275,500 1 Claim. (Cl. 891.7)
This invention relates to a launching ramp for winged missiles, and in particular to the track arrangement thereof which permits a missile to leave the ramp at relatively low speed without tip-01f.
Heretofore, it has been known to provide launching ramps for winged missiles with a pair of tracks for guiding a front pair and a rear pair of shoes attached to the missile. However, in launching such a missile in windy or gusty Weather it occurred that as soon as the front pair of shoes had left the tracks the missile had insufficient guidance and, therefore, the tendency to be side-swept while the rear pair of shoes was still on the traclcs, making a satisfactory take-off difiicult. In other cases, when the direction of thrust of a booster rocket did not go through the center of gravity of the missile, the missile was lifted off the tracks, either at front or rear, thus interfering with a well balanced take-off.
It is the general object of the invention to avoid and overcome the foregoing and other difficulties of and objections to prior art practices by the provision of a launching ramp for missiles whereby all shoes of a missile disengage substantially simultaneously from the ramp tracks.
Another object of the invention is to provide a launching ramp for missiles which is most compact and affords a stabilizing effect to the missile for a satisfactory take-01f.
The aforesaid objects of the invention, and other objects which will become apparent as the description proceeds, are achieved by providing a missile launching ramp with three tracks, engaging shoes attached to the missile. Two of the tracks are laterally spaced and disposed on top of the ramp structure, and the third track is positioned in the center of this structure and below the aforementioned tracks. The front ends of the upper tracks and the front end of the lower track are staggered longitudinally such a distance that in launching the front shoes and rear shoe of the missile disengage from the tracks substantially simultaneously. Because the missile is held on the tracks against lateral and vertical movement there will be no tip oif when it leaves the ramp. The operating length of the ramp can be made extremely short to insure, even below stalling speed of the missile, a satisfactory launching performance.
For a better understanding of the invention reference should be had to the accompanying drawing, wherein FIG. 1 is a side view of one embodiment of the invention,
FIG. 2 is a plan view of the ramp structure,
FIG. 3 is a front view of FIG. 1,
FIG. 4 is a cross-sectional view of the upper track structure, taken on line IVIV of FIG. 1.
FIG. 5 is a cross-sectional view of the lower track structure, taken on line VV of FIG. 1.
With specific reference to the form of the invention illustrated in the drawing, the numeral 1 indicates in general the longitudinal frame work girders of the launching ramp which are connected together by transverse structures 2 of suitable construction and by an end beam 3 carrying pivots 4 about which the ramp is tiltable for launching the missile 5, preferably with the wing folded as shown. The missile 5 is provided with a pair of lateral shoes 6 bearing on tracks 7 formed by the upper girder members and held in position by guides 8 and 9 secured to the tracks 7 by bolts 10. Similarly a shoe 11, extending from the bottom and towards the rear of missile 5, bears against a middle track 12 secured to some of the transverse structures 2 by bolts 13 and provided at both sides with guides 14 and 15 fastened by bolts :16 to the track 12. The front ends of the upper tracks 7 are staggered against the front end of the lower or middle track .12 a distance A equal to the longitudinal distance between the rear ends of the shoes 6 and the shoe 11, so
that, in launching, the missile will disengage from all tracks substantially simultaneously. This is important for successfully launching the missile. i
It will be recognized that the objects of the invention have been achieved by providing a launching ramp with three tracks for guiding a missile at the sides and at the bottom center to prevent it from changing its upright position during contact with the launching ramp, but to simultaneously disengage all missile shoes from the tracks, so that the launching speed of the missile can be relatively low, even below its stalling speed and, thus, permit a launching ramp of unusually short length requiring least space.
While certain representative embodiments and details have been shown for the purpose of illustrating the invention, it will be apparent to those skilled in this art that various changes and modifications may be made therein without departing from the spirit and scope of the invention.
What is claim is:
In combination, a self-energized missile, a pair of longitudinal short guide shoes positioned on the forward portion of the missile, one shoe extending laterally on each side of the missile, a third longitudinally-short guide shoe connected to the bottom of the rear of the missile, a launching ramp slidably supporting the missile and including a pair of parallel rails slidably supporting a pair of guide shoes, a third rail positioned midway between and parallel to the parallel rails but below the plane thereof and slidably supporting the third guide shoe, the third rail terminating in a forward direction short of the forward end of the parallel rails, the distance between the termination of the third rail and the points of termination of the parallel rails being equal to the distance between the pair of guide shoes and the single shoe whereby the pair of guide shoes leave the parallel rails at the same time as the single guide shoe leaves its rail so that no turning moment exists on the missile to turn it out of line when it is launched.
References Cited in the file of this patent UNITED STATES PATENTS Sweden Feb. 13, 1951 Patented Sept. 5, 1961
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US275500A US2998752A (en) | 1952-03-08 | 1952-03-08 | Missile launching ramp |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US275500A US2998752A (en) | 1952-03-08 | 1952-03-08 | Missile launching ramp |
Publications (1)
Publication Number | Publication Date |
---|---|
US2998752A true US2998752A (en) | 1961-09-05 |
Family
ID=23052572
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US275500A Expired - Lifetime US2998752A (en) | 1952-03-08 | 1952-03-08 | Missile launching ramp |
Country Status (1)
Country | Link |
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US (1) | US2998752A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3225655A (en) * | 1964-05-25 | 1965-12-28 | Gen Dynamics Corp | Controlled tip-off launcher |
US4098168A (en) * | 1970-09-15 | 1978-07-04 | Vereinigte Flugtechnische Werke-Fokker G.M.B.H. | Mechanical structure |
US4327624A (en) * | 1980-06-23 | 1982-05-04 | General Dynamics, Pomona Division | Tip off rate reducer |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US534651A (en) * | 1895-02-26 | kruckeil | ||
GB189425326A (en) * | 1894-06-04 | 1895-03-09 | Eugene Turpin | Improved Apparatus to be used in Discharging Rocket Projectiles. |
US1558542A (en) * | 1925-03-07 | 1925-10-27 | Raymond W Holland | Skyrocket |
US1706065A (en) * | 1927-07-12 | 1929-03-19 | Jenkins Charles Francis | Airplane-launching gear |
US2481542A (en) * | 1946-08-13 | 1949-09-13 | Us Navy | Displacement launcher for projectiles |
US2549778A (en) * | 1945-12-14 | 1951-04-24 | Crawley Blick | Projectile launching |
US2591834A (en) * | 1948-07-21 | 1952-04-08 | Lockheed Aircraft Corp | Retractable rocket launcher |
US2604014A (en) * | 1949-10-20 | 1952-07-22 | Earl C Walker | Missile launcher |
-
1952
- 1952-03-08 US US275500A patent/US2998752A/en not_active Expired - Lifetime
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US534651A (en) * | 1895-02-26 | kruckeil | ||
GB189425326A (en) * | 1894-06-04 | 1895-03-09 | Eugene Turpin | Improved Apparatus to be used in Discharging Rocket Projectiles. |
US1558542A (en) * | 1925-03-07 | 1925-10-27 | Raymond W Holland | Skyrocket |
US1706065A (en) * | 1927-07-12 | 1929-03-19 | Jenkins Charles Francis | Airplane-launching gear |
US2549778A (en) * | 1945-12-14 | 1951-04-24 | Crawley Blick | Projectile launching |
US2481542A (en) * | 1946-08-13 | 1949-09-13 | Us Navy | Displacement launcher for projectiles |
US2591834A (en) * | 1948-07-21 | 1952-04-08 | Lockheed Aircraft Corp | Retractable rocket launcher |
US2604014A (en) * | 1949-10-20 | 1952-07-22 | Earl C Walker | Missile launcher |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3225655A (en) * | 1964-05-25 | 1965-12-28 | Gen Dynamics Corp | Controlled tip-off launcher |
US4098168A (en) * | 1970-09-15 | 1978-07-04 | Vereinigte Flugtechnische Werke-Fokker G.M.B.H. | Mechanical structure |
US4327624A (en) * | 1980-06-23 | 1982-05-04 | General Dynamics, Pomona Division | Tip off rate reducer |
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