Aeronautics and astronautics – Missile stabilization or trajectory control – Externally mounted stabilizing appendage
Reexamination Certificate
1999-06-15
2001-04-24
Tudor, Harold J. (Department: 3641)
Aeronautics and astronautics
Missile stabilization or trajectory control
Externally mounted stabilizing appendage
C244S049000
Reexamination Certificate
active
06220544
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention concerns a guided missile in particular a projectile which can be fired through the intermediary of a propellent charge gas pressure.
2. Discussion of the Prior Art
A guided missile of that kind or a mounting arrangement for the rudder blade of such a missile, in particular a projectile which can be fired by means of propellent charge pressure and which can be maneuvered by way of an over-calibre crossed-rudder system is known for example from DE 34 41 534 A1. When such a projectile is fired the rudder blades are folded in, that is to say they are mounted in associated guide and mounting slots in the projectile. Due to the usual, slightly irregular combustion of the propellent charge powder differential pressures occur in the propellent charge chamber, which can bend or twist the rudder blades. In order to prevent the rudder blades from being bent or twisted in that way the rudder blades are mounted or guided in guide slots. In the known projectiles the guide slots are open at the front end in order to make it easier for the rudder blades to be pivoted into the open condition after the respective projectile has been launched. Due to the guide slots being open at their front end in the known projectiles of the kind set forth in the opening part of this specification however it is only possible to a limited extent to avoid bending or twisting of the rudder blades due to the differential pressures in the propellent charge chamber.
SUMMARY OF THE INVENTION
Therefore the object of the present invention is to provide a guided missile of the kind set forth in the opening part of this specification in which such deformations of the rudder blades by bending or twisting as a result of the pressure differences obtaining in the propellent charge chamber are avoided to a further improved extent.
The fact that, in the guided missile according to the invention, each guide slot is closed at its front end by an end portion which is formed with a spoiler end face affords the advantage that, when the projectile is launched, a direct and immediate afflux flow in relation to the rudder blades at their distal end face, that is to say their end face which is remote from their pivot axis, is prevented, which affords the result that flexural and twisting deformation phenomena of the rudder blades can be prevented to a further improved degree. The respective spoiler end face advantageously produces an air flow in such a way that a force component radially inwardly in relation to the longitudinal axis of the projectile, which would prevent or slow down deployment of the rudder blades is avoided.
It is quite particularly desirable if, in the guided missile according to the invention, the end portion protrudes in a radial direction of the projectile beyond the longitudinal ribs and the associated rudder blade is provided at its distal end portion with narrow guide ribs which project out of the rudder blade profile and which are disposed in laterally mutually opposite relationship. Such a design configuration for which independent patent protection is requested optimally prevents undesired deformation of the rudder blades due to bending or twisting as a result of the inevitable differential pressures in the propellent charge chamber because. in the inwardly folded condition of the rudder blades, said guide ribs are in contact in the guide slot which is of increased height at its front end, thereby providing for suitable support for the respective rudder blade.
In the case of longer rudder blades, each rudder blade can be formed in a central portion with additional narrow guide ribs which are disposed in laterally mutually opposite relationship.
In order further to improve the pivotal opening movement of the rudder blades after the projectile according to the invention has been launched, it is desirable if a spring element is provided between the root portion of the respective rudder blade and the associated rudder blade holder for deployment of the rudder blade. The respective spring element can be formed by a spiral spring which with its spiral turns extends around the pivot axis about which the rudder blade can be pivoted open in relation to the associated rudder blade holder.
A protected and aerodynamically favourable arrangement of the respective spring element is afforded if the root portion of the rudder blade, for receiving the spiral turns of the spiral spring, is formed with a partially open gap or slot space which extends in an annular configuration around the pivot axis.
The guided missile according to the invention provides for a comparatively desirable flow therearound. That desirable flow around the missile advantageously results in unimpeded and consequently faster and more uniform, that is to say symmetrical, opening pivotal movement of the rudder blades. In addition, upon launch the mechanical loading on and thus the deformation of the rudder blades are relatively slight, thereby advantageously resulting in the positioning and control accuracy of the rudder blades being maintained.
The configuration of the longitudinal ribs which laterally delimit the respective guide slot, with an end portion which is closed at the front end and which projects beyond the longitudinal ribs in the radial direction of the projectile, and the configuration of the respective rudder blade with laterally mutually oppositely disposed guide ribs at the distal end portion of the respective rudder blade, that is to say the improved guidance effect for the respective rudder blade at its distal end portion, afford the further considerable advantage that the torques which take effect on the root portion of the respective rudder blade upon launch of the missile are considerably reduced. That has a correspondingly positive effect on the positional and control accuracy for the rudder blades. as has already been mentioned above.
REFERENCES:
patent: 3598345 (1971-08-01), Suter
patent: 3690595 (1972-09-01), Rusbach
patent: 4334657 (1982-06-01), Mattson
patent: 4641802 (1987-02-01), Zalmon et al.
patent: 4728058 (1988-03-01), Brieseck et al.
patent: 4869441 (1989-09-01), Steuer
patent: 5111553 (1992-05-01), Muggeridge et al.
patent: 5114095 (1992-05-01), Schroppel et al.
patent: 5685503 (1997-11-01), Trouillot et al.
patent: 19 25 055 (1970-09-01), None
patent: 3441534 A1 (1986-05-01), None
patent: 251890 (1988-01-01), None
Dommer Josef
Schroppel Werner
Staudenmeir Martin
Diehl Stiftung & Co.
Scully Scott Murphy & Presser
Tudor Harold J.
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