Ammunition and explosives – Drop bombs – With drop-retarding means
Reexamination Certificate
1999-11-22
2001-10-30
Jordan, Charles T. (Department: 3644)
Ammunition and explosives
Drop bombs
With drop-retarding means
C102S293000, C102S400000, C102S501000, C416S142000, C416S087000, C416S140000
Reexamination Certificate
active
06308632
ABSTRACT:
BACKGROUND OF THE INVENTION
The present invention relates to a propeller assembly, and more specifically to an apparatus and method for deploying a propeller assembly, a which is diametrically larger than an aerial projectile's diameter, from a folded configuration to a deployed configuration during the fight of the aerial projectile.
Some projectiles, which require a propeller assembly, are fired from a gun or some other launching system that has a constricted launch area. These projectiles may have a propeller assembly that is diametrically larger than the projectile's diameter. The gun or other launching system may have a constricted launch area that may only contain the projectile body but not the diametrically larger propeller assembly.
One option for fitting both a projectile and its propeller assembly inside a limited launch area is to package the propeller assembly so that the propeller blades are not diametrically larger than the projectile prior to launch. For example, it is believed that U.S. Pat. No. 4,986,185 discloses dual blade propellers made of flexible metal or fabric loops or strips. The propeller blades are folded in a closely packed, nesting arrangement. However, this prior art is designed to deploy the propeller blades as soon as the projectile is free of the restricted launch area. Furthermore, the blades are loops, thus each blade has a limited surface area.
Propeller blades hinged to a hub are also known in the prior art. For example, it is believed that U.S. Pat. No. 4,204,806 discloses a foldable marine propeller assembly that is attached to a drive shaft. Though the folded propeller assembly appears to have an aerodynamically efficient configuration, once employed, the area once occupied by the propeller blades is now a flat, blunt area that is no longer as aerodynamically efficient.
Accordingly, it would be advantageous to provide an apparatus and method that is simple and robust enough to deploy solid propellers other than immediately after launch where the propeller blades are capable of withstanding the environment experienced in launching the projectile. It would also be advantageous for the propeller assembly to maintain an aerodynamically efficient configuration after the deployment of the propeller blades.
SUMMARY OF THE INVENTION
One object of the present invention is to provide a highly reliable method for rapidly deploying a folded propeller assembly to an operational configuration where a minimum of the components is under stress prior to deployment. The propeller assembly comprises several components including a drive shaft, drive shaft bevel gear, hub, nut hub, journal, propeller blades, and propeller bevel gears. The propeller blade in an integral unit, consisting of a foil, attachment shaft, and a propeller base. Since the propeller blades are integral units, the propeller blades nutate from the folded configuration to an operational configuration. Nutating the propeller blades into its operational configuration allows for the hub and hub nut to be designed in an aeronautically efficient configuration such as a conical shape.
In one embodiment of the present invention, the propeller blades are initially stowed or folded and the hub is statorized, or physically held in place, against the projectile. An engine or some other prime mover causes the drive shaft to rotate, which in turn activates the bevel gears inside of the statorized hub. The rotating of the bevel gears nutates the propeller blades within the statorized hub from a folded position to a deployed operational position. At the end of deployment within the statorized hub a stopper device, for example a spring loaded detent secures the drive shaft to the statorized hub and then a shear pin is broken freeing the now bladed hub to turn with each revolution of the drive shaft.
REFERENCES:
patent: 866369 (1907-09-01), Learnard
patent: 3709634 (1973-01-01), Lorenz
patent: 4072107 (1978-02-01), Saxe et al.
patent: 4204806 (1980-05-01), Blachard
patent: 4364711 (1982-12-01), Brandt et al.
patent: 4726292 (1988-02-01), Gatti
patent: 4768927 (1988-09-01), Munk
patent: 4801243 (1989-01-01), Norton
patent: 4936526 (1990-06-01), Gries
patent: 4986185 (1991-01-01), Kuhnle et al.
patent: 5299912 (1994-04-01), Fradenburgh et al.
patent: 6152693 (2000-11-01), Olsen et al.
Beusse Brownlee Bowdoin & Wolter P.A.
Jordan Charles T.
Maire, Esq. David G.
Sanks, Esq. Terry M.
Smith Kimberly S
LandOfFree
Deployable folded propeller assembly for aerial projectiles does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Deployable folded propeller assembly for aerial projectiles, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Deployable folded propeller assembly for aerial projectiles will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2616855