DE1061630B - Device for vertical take-off of aircraft - Google Patents

Description

Equipment for vertical take-off of aircraft. In addition to the normal take-off procedure in the horizontal direction, the method has been used more and more recently, Planes also take off and land vertically. The ones available today high engine thrusts, some of which significantly exceed the take-off weight this procedure is possible.

According to the previously known embodiments are for the vertical takeoff basically other types of aircraft are necessary. The characteristic of vertical takeoff aircraft are, apart from the corresponding stabilizers, three or four Outriggers or control surfaces that can be used as such to control the on the Rear standing aircraft to give the necessary stability and at the same time To carry structural members to absorb landing shocks.

Such aircraft can and must only take off and land vertically with appropriate ground equipment for the transport either folded over or with special constructed wagons can be transported to and from the deployment site. With the invention a method is shown that can be used both horizontally and vertically Makes take-off of an aircraft possible and also the righting and lowering of the aircraft with on-board resources, i.e. without the aid of more or less extensive ground equipment permitted and also has the advantage that a transport or maneuvering on the ground can be done on its own wheels. To meet the requirements for To meet this method, the aircraft according to the invention has one on one rear part of the fuselage pivotable about a transverse axis connected variable-length Strut, the free end of which is designed as a support member and at the z. B. about in the middle a support strut is hinged, the other end further forward is hinged to the fuselage and is also variable in length.

The aircraft identified above has optional for the horizontal and vertical takeoff, in addition to its normal landing gear, preferably with nose wheel arrangement in a known manner, cell-side devices for vertical take-off. An embodiment of the invention is shown in the drawing.

Underneath the fuselage is a length-adjustable swiveling device that can be pivoted about a transverse axis Strut 1 mounted, which is guided by a support strut 2, which is also variable in length will.

In addition, wear the wingtips or about to the in a known manner Containers attached to the wing tips or keel fins required for other reasons under these containers strut-like members 3, which are parallel to the fuselage axis are arranged. Similarly, the rudder unit is also known in a known manner provided with such a shock absorber 4.

The process of changing aircraft attitude is as follows: Will the strut 1 under the fuselage and in a suitable relationship to the strut 2 extended, the former first touches the ground in front of the main landing gear and tips over if it is extended further, the aircraft around the points of contact between wheels and Ground backwards until the shock absorbers 3 at the wing tips touch the ground and thus create a support base the size of the wing spans. Around The aircraft then becomes support points when the lifting device is extended further gradually straightened up to the vertical.

In a vertical position the aircraft rests on four points, namely: the two shock absorbers 3 on the wing tips, the shock absorber on the vertical stabilizer 4 and the support strut 1, which is also designed as a shock absorber.

In reverse to the righting process, the aircraft can operate in a similar manner moved from the vertical to the horizontal position.

In this way it is possible before a vertical takeoff or after maneuvering a vertical landing in a horizontal position on its own landing gear. If z. B. waived the possibility of horizontal starting in principle is, the normal chassis is only used for transport on the ground and can because of the minor that occurs. Stress can be made lighter accordingly.

The two struts 1 and 2 shown in the sketch only adjust It is just as technically feasible, for. B. only with one single adjustable-length strut to work that by a Support of constant length is performed, or in place of the telescopically extendable Strive for another facility, e.g. B. in the manner of the Nuremberg scissors to use.

Claims (3)

PATENT CLAIMS: 1. On-board lifting device for from the rear stand aircraft taking off with at least two preferably retractable and extendable supports at the ends of mainly positive swept wings or on the underside of the fuselage or on the tail unit, characterized by one at a rear point of the fuselage About a transverse axis pivotally connected variable-length strut (1), whose free end is designed as a support member and at the z. B. in the middle one Support strut (2) is hinged, the other end to a further forward on Joint lying on the trunk is connected and is also variable in length, wherein the strut (1) pivoted backwards with primarily full length expansion has such a position that the support member of the strut (1) the third point of a Three-point support or - the fourth point of a four-point support of the vertical one Aircraft forms, while the forward swiveled strut (1) in cooperation with the other and possibly additional supporting organs, such as an additional nose wheel, results in a normal prone position of the aircraft. 2. Erecting device according to claim 1, characterized in that the strut (1) and the support strut (2) as electrically, hydraulically, pneumatically or mechanically operated telescopic struts are trained. 3. Erecting device according to claim 1 and 2, characterized in that that the strut (1) and the support strut (2) beyond the front supporting end position are fully retractable so that. a conventional tricycle undercarriage is effective.