Aeronautics and astronautics – Missile stabilization or trajectory control – Externally mounted stabilizing appendage
Reexamination Certificate
1999-06-15
2001-03-20
Tudor, Harold J. (Department: 3641)
Aeronautics and astronautics
Missile stabilization or trajectory control
Externally mounted stabilizing appendage
C244S046000, C244S049000
Reexamination Certificate
active
06202958
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention concerns a mounting arrangement for the pivotally openable rudder blades, which cross each other in pairs, of a guided missile, particularly a projectile which can be fired through the intermediary of a propellant charge gas pressure.
2. Discussion of the Prior Art
A mounting arrangement of that kind is known from DE 34 41 534 A1. In that known mounting arrangement, an elastically upsettable sealing ring is provided between the one annular shoulder on the respective shaft trunnion, and the associated second annular shoulder which is provided on the tail structure of the missile. A sealing effect and a return function are implemented by means of that sealing ring when the missile is launched by means of the propellent charge. Sealing rings of that kind consisting of elastically upsettable material however are only suitable for certain gas pressures which are limited in an upward direction. In addition, elastically upsettable sealing rings of that kind suffer from material ageing which has an effect on the properties thereof in terms of stock-keeping and durability.
Furthermore, with that known mounting arrangement of the above-described kind, it is necessary for the shaft trunnion of the corresponding rudder blade holder to be provided with an inclinedly extending opening into which an associated screwthreaded pin projects in order to provide for axial adjustment in force-locking relationship. Furthermore each shaft trunnion is provided with the coupling element by means of a key-and-spline connection in order to afford definedly limited radial mobility of the respective rudder blade. All those components however involve production tolerances which cannot be eliminated, and that has a corresponding effect on the angular positioning of each rudder blade. In addition the manufacture of that known mounting arrangement involves corresponding costs. Furthermore the elastically upsettable sealing rings result in the creation between the tail structure of the missile and the rudder blade holders for the rudder blades of a friction which cannot be disregarded and which has an effect on displacement of the rudder blades.
SUMMARY OF THE INVENTION
In consideration of those factors the object of the present invention is to provide a mounting arrangement of the kind set forth in the opening part of this specification, in which dimensional tolerances between the components or individual parts of the mounting arrangement do not have any influence on the angular position of the rudder blades, which is suitable for comparatively high gas pressures of the missile which can be fired by means of propellent charge gas pressure, which enjoys excellent storability and in which the friction aspects are substantially reduced.
In the case of the mounting arrangement according to the invention, the spacing between the first annular shoulder provided on the rudder blade holder and the second annular shoulder provided on the tail structure of the missile is slightly greater than the thickness of the ring element which is disposed therebetween and which comprises an inelastic material, preferably metal, so that between the ring element and the first and second annular shoulders there is an axial tolerance play considered in relation to the associated trunnions. That provides for the attainment of a comparatively low level or precisely predictable degree of friction. The respective ring element of inelastic material or metal affords the advantage that the mounting arrangement according to the invention is not only suitable for higher gas pressures but that in addition material ageing is also prevented and thus storability over a longer period of time is achieved.
The fact that, in the mounting arrangement according to the invention, the trunnions of the respective pair of trunnions are rigidly connected to the associated coupling element which is of a limitedly resilient nature in the radial direction of the projectile affords the advantage that manufacturing tolerances between the corresponding parts of the mounting arrangement do not have any influence on the angular positioning of the rudder blades, that is to say angular positioning of the rudder blades is possible in a highly precise fashion in a simple manner.
The angular position of the rudder blades or the angular position of the rudder blade holders for the rudder blades in relation to each other is determined simply and solely by the degree of connecting accuracy between the respective rudder blade holder and the associated trunnion. As in accordance with the invention the trunnions of the respective pair thereof are rigidly connected to the associated coupling element, the degree of manufacturing accuracy of those parts advantageously has no influence on the angular position of the rudder blade holders or the respective pair of trunnions. That rigid connection can be implemented for example by the respective trunnion being pinned, glued, welded or clamped to the associated coupling element. The respective coupling element desirably has a pair of mutually spaced mounting end portions for the associated trunnions and a connecting central portion which radially elastically resiliently connects the two mounting end portions. The connecting central portion can be of a meander-shaped, arcuate, zig-zag shaped or any other configuration, the only consideration of importance being that it is limitedly elastically resiliently yielding in the racial direction of the projectile.
The mounting end portions can be for example of a sleeve-shaped or socket-shaped configuration or a journal or trunnion configuration. The shaft trunnions of the rudder blade holders are of a configuration which is adapted thereto. So that the connecting central portions of the two mutually crossing coupling elements do not impair each other in respect of their mobility, the connecting central portion of at least one of the two coupling elements can be disposed eccentrically in relation to the associated mounting end portions.
It will be appreciated that it is also possible for the connecting central portions of the two coupling elements to be disposed eccentrically in relation to the associated mounting end portions.
To provide for the defined angular setting as desired of the rudder blade holders or the pairs of rudder blades, the respective coupling element can be provided at one of its two mounting end portions with a control projection which extends radially away therefrom. The respective control projection is engaged by an actuating or drive element of a control drive of the guided missile or projectile.
REFERENCES:
patent: 4660786 (1987-04-01), Brieseck et al.
patent: 4728058 (1988-03-01), Brieseck et al.
patent: 5211357 (1993-05-01), Leidenberger
patent: 2410255 C2 (1974-10-01), None
patent: 3441534 A1 (1986-05-01), None
Dommer Josef
Schroppel Werner
Staudenmeir Martin
Diehl Stiftung & Co.
Scully Scott Murphy & Presser
Tudor Harold J.
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