Aeronautics and astronautics – Missile stabilization or trajectory control – Stabilized by rotation
Patent
1986-07-23
1987-10-13
Kyle, Deborah L.
Aeronautics and astronautics
Missile stabilization or trajectory control
Stabilized by rotation
244 329, F42B 1332
Patent
active
046993347
DESCRIPTION:
BRIEF SUMMARY
FIELD OF THE INVENTION
The present invention relates to a wing for an aircraft. More particularly this invention concerns a tail unit for a missile or projectile.
BACKGROUND OF THE INVENTION
A deployable tail unit as described in German Pat. No. 3,026,409 has wings each constituted as a textile two-wall cover and a partially telescoping strut arrangement that erects it. The strut arrangement is formed of a plurality of parts which take up a relatively large space within the missile and therefore constitute a considerable portion of lost space, and the construction of these parts is fairly expensive. In addition the deployment of the wing is problematic in view of the high acceleration forces created when the aircraft in question is fired or launched.
A fold-down wing is known which is a simple flap that folds against the side of the aircraft and that is erected by a spring when the projectile is launched, typically when it exits the barrel of the cannon from which it is fired. The wings are, however, invariably relatively flimsy and this lack of rigidity reduces their aerodynamic effectiveness.
Another disadvantage of the known wings is that they are unable to impart spin to the vehicles because they are not rigid enough to withstand the angular forces created in such a situation.
OBJECTS OF THE INVENTION
It is therefore an object of the present invention to provide an improved wing for an aircraft such as a projectile or missile.
Another object is the provision of such a wing for an aircraft such as a projectile or missile which overcomes the above-given disadvantages, that is which takes up very little space when not deployed, which is relatively simple and inexpensive, and which is nonetheless fairly rigid when erect, because the wing plates are curved like buckles about two axes when deployed.
SUMMARY OF THE INVENTION
A wing for an aircraft extending along and normally intended to move along a main axis comprises a first pivot fixed on the aircraft and defining a fixed pivot axis generally parallel to the main axis, a guide extending angularly on the aircraft adjacent the first pivot, and a second pivot defining a movable axis generally parallel to the main axis and displaceable in the guide between an inner end position closely juxtaposed with the fixed axis and an outer end position spaced angularly therefrom. A first wing plate is pivotal about the fixed axis and has an inner end fixed to the fixed pivot and an outer end and a second wing plate is pivotal about the movable axis and has an outer end fixed to the outer end of the first plate and an inner end fixed to the second pivot. The wings are displaceable between an undeployed position lying against one another and against the aircraft with the movable axis in the inner end position close to the fixed axis and a deployed position with both wings extending at an angle to each other and generally radially of the aircraft and with the movable axis in the outer end position far from the fixed axis.
According to this invention both wing plates are flexible and elastic and this elasticity is what moves them into the deployed position. More particularly the wing plates are more elastically deformed in the undeployed than in the deployed position so that when unconstrained they naturally move into the deployed position.
According to another feature of this invention each pivot includes at least one pivot pin extending along the respective pivot axis and secured to the respective inner plate end. The pivot pin of the second plate is displaceable along the guide. In addition at least one of the pins is comprised of two pin parts arranged coaxially of the respective axis. This two-part pin is the pin of the second plate and is engaged in the guide and the guide is two grooves into which the respective pin parts are engaged and has ends remote from the fixed pivot formed with inwardly open recesses. In this case the wing has springs engaged with the pin parts for urging same outwardly and for pressing same lockingly into the recesses when the resp
REFERENCES:
patent: 2923241 (1960-02-01), House
patent: 3103886 (1963-09-01), Popenoe
Carone Michael J.
Kyle Deborah L.
Rheinmetall GmbH
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