DE1231116B - Flying body, in particular a spacecraft, with a fold-out replacement wing - Google Patents

Description

Missile, in particular spacecraft, with a replacement wing that can be folded out The invention relates to a missile, in particular to a spacecraft, with a preferably heavily swept wing, a tail unit and a spare wing in the form of a fold-out flexible wing with a central keel.

Spacecraft that have the task of completing their mission Returning to Earth in orbit must be specific to the flight conditions be designed aerodynamically in hypersonic and supersonic. Furthermore, there must be problems the cell heating during the immersion phase of the missile in the atmosphere great attention should be paid to. Therefore, such spacecraft must have wings be equipped with great sweep; in most cases they are delta wings.

The ratio of take-off weight to landing weight is very large in such missiles, so that one has a small wing loading and thus a relatively low landing speed for the landing approach. Delta wings with a small aspect ratio, however, have a small dcA / dx, i.e. That is, in order to achieve a fairly high CA for the landing approach, the wing and thus the entire missile must be inclined very steeply. With large angles of attack of delta wings, the longitudinal and lateral stability and the rudder effectiveness decrease very strongly.

So in many cases it is not even possible with the necessary high cA values to keep the aircraft stable. Relatively high c #, i values with low Employment can be achieved with wings with a small arrow and the resulting larger aspect ratio; associated with this is also a better stability behavior. To prevent high-speed aircraft with heavily swept wings when landing or To help in the start phase to high lifts with a small wing pitch, arranged the wings can be pivoted about vertical axes. The arrow angle is reduced, the aspect ratio increases and the gradient dcA / dx increases. The swivel mechanism for the wings is already quite complicated and with relatively small aircraft associated considerable weight. One such solution is for space transporters their size and severe weight conditions are not very suitable for increasing the dcA / da value raise.

It is also already known to have a replacement wing in the form of a fold-out one to provide flexible wing. This wing replaces that aerodynamically, so to speak rigid structure of the missile. The aspect ratio of the replacement wing is larger and the arrow angle smaller than the original wing. Its area corresponds to approximately the projection area of the entire missile. The replacement wing is on the missile mounted so that it has a large angle of attack compared to the Hull occupies. But since it is suspended on ropes, the generated on the missile can Control moments are not simply transferred to the replacement wing.

According to the invention, the most important control torque, the pitching torque, to be able to transfer to the replacement wing, its central keel in the rear area pivotable about a transverse axis with respect to the fuselage of the missile and in the front Area through a telescopically extendable handlebar with the fuselage of the missile tied together. The adjustability of the length of the telescopic support makes it possible to adjust the angle of attack of the central keel with respect to the fuselage of the missile. The occurring The change in pitching moment is compensated for by the elevators attached to the missile and transferred to the replacement wing through the triangular bond created.

The invention can be applied not only to space transporters, but also apply to other aircraft to which the above criteria apply.

The invention is illustrated using an exemplary embodiment with reference to the drawing explained.

The fuselage 1 and the very slim delta wing 2 are designed according to the criteria of hypersonic and high supersonic flow. Behind the trailing edge of the wing are the elevators 3, which can also be used as ailerons in a known manner. Vertical stabilizers 4 bring about stability around the vertical axis. The replacement wing 5 is a known flexible wing. The wing is folded up and stowed in the upper part of the fuselage. The keel 6 is pivoted upward about a joint 8 by a telescope 7 and forms an angle between itself and the axis of the fuselage. The spars 9 and 10 are directed away from the keel by a spreading mechanism and form a fixed arrow angle. The ends of the outer spars are connected to the missile by cables 11 and 12 or the like.

The control around all three axes is carried out by the installed control units performed, in contrast to the known control systems of the previously known Arrangements in which changes in the curvature #, of the wing were controlled.

Claims (1)

Claim missile, in particular spacecraft, with a preferably heavily swept wing, a tail unit and a spare wing in the form of a foldable flexible wing with a central keel, characterized in that the Central keel of the replacement wing in the rear area around a transverse axis opposite the fuselage of the missile is pivotable and in the front area by a telescopic extendable handlebar is connected to the fuselage of the missile.