DE3838737C2 - Submunition missile - Google Patents

Description

The invention relates to a submunition missile the fuselage is arranged on the outside of the sliding wing holder are on which sliding wings are exhibited, whereby at least one of the sliding wing holders on the fuselage around it Longitudinal axis is pivotally mounted and in the Transport position to one of the other sliding wing holders is pivoted, according to patent application P 37 30 019.9.

Such a submunition missile has the advantage that the outer sliding wing holder in a carrier take up little space. However, at least one must the sliding wing holder after the submunition has been ejected be brought from the carrier into its flight position. In patent application P 37 30 019.9 is one for this Torsion spring provided. The arrangement of the torsion spring has mechanical weakening of the trunk.

The object of the invention is a Submunition missiles of the type mentioned at the beginning propose where the moving Sliding wing holder can be swiveled into flight position can without significantly weakening the fuselage Breakthroughs are necessary.

According to the invention, the above task is for a submunition Missile of the type mentioned solved in that the swiveling sliding wing holder on an outside of the  Fuselage lying attachment point with a flexible Pull piece is connected that the pull piece by a Breakthrough of the fuselage from its outer circumference in its Interior is guided, the in the transport position of the sliding wing holder on the circumference of the fuselage external part of the tension piece is so long that by means of of the pull piece of the sliding wing holder from its Transport position is pivotable into its flight position, that a linear on the tension piece in the interior of the fuselage acts force element whose stroke is smaller than the distance of movement of the attachment point from the Transport position in the flight position of the Sliding wing holder, and that between the force element and the breakthrough the pull piece via a pulley is led.

This ensures that the breakthrough does not affect the fuselage weakens on its entire circumference. It is sufficient if the Breakthrough is only so large that the pull piece with his Cross section fits straight through it. Is cheap also that the pivoting movement of the sliding wing holder can be achieved by a linear, rectilinear movement can. The pulley has the advantage that a Reduction of movement between the movement distance of the Sliding wing holder and the force element is reached.

It is also favorable that the force element compared to the torsion springs is easier to control, so that Swiveling the sliding wing holder over time the flight conditions are customizable.

Further advantageous embodiments of the invention result from the subclaims and the following Description of an embodiment. In the drawing demonstrate:

Fig. 1 shows a submunition missile schematically in section in the transport position and

Fig. 2 is a partial view of FIG. 1.

A submunition missile has a fuselage ( 1 ) on which two sliding wing holders ( 2 , 3 ) are fixed. The fuselage ( 1 ) is enclosed by an annular body ( 4 ) on which two further sliding wing holders ( 5 , 6 ) are fixedly arranged. The ring body ( 4 ) can be rotated against the fuselage ( 1 ) about its longitudinal axis (L).

Each sliding wing holder ( 2 , 3 , 5 , 6 ) has a sliding wing ( 7 ) that can be raised.

A flexible pulling piece ( 9 ) engages with one end on the ring body ( 4 ) at a fastening point ( 8 ). The tension piece ( 9 ) is formed, for example, by a wire or a plastic band.

The tension piece ( 9 ) runs from the fastening point ( 8 ) to an opening ( 10 ) of the fuselage ( 1 ) between the ring body ( 4 ) and the fuselage ( 1 ), ie outside the fuselage ( 1 ). The opening ( 10 ) is only slightly larger than the cross section of the tension piece ( 9 ). The traction element ( 9 ) is guided through the opening ( 10 ) into the interior ( 11 ) of the fuselage ( 1 ).

The end of the pull piece ( 9 ), which is located in the interior ( 11 ), is connected to a piston-cylinder device ( 12 ). The tension piece ( 9 ) is placed around a pulley block ( 13 ) between the piston-cylinder device ( 12 ) and the opening ( 10 ). This is designed so that it translates the movement distance of the piston-cylinder device ( 12 ) for the attachment point ( 8 ).

In Fig. 1, the sliding wing holders ( 5 , 6 ) are shown in their transport position, in which they are close to the fixed sliding wing holders ( 2 , 3 ). In this position, the length (A) of the part of the tension piece ( 9 ) lying between the fastening point ( 8 ) and the opening ( 10 ) is greater, in particular slightly greater, than the distance which corresponds to the angle (W) by which the sliding wing holder ( 5 , 6 ) are to be swiveled from their transport position into the flight position. This angle (W) is approximately 70 °.

The functioning of the described device is approximately as follows:
The submunition missile is ejected from the carrier in the position of its sliding wing holder ( 2 , 3 , 5 , 6 ) shown in FIG. 1. Then the piston-cylinder device ( 12 ) is initiated so that it pulls on the pull piece ( 9 ). As a result, the ring body ( 4 ) is pivoted about the longitudinal axis (L) of the fuselage ( 1 ) via the block and tackle ( 13 ) until the sliding wing holders ( 5 , 6 ) are pivoted by the angle (W). They are then offset by 90 ° on the fuselage ( 1 ) opposite the sliding wing holders ( 2 , 3 ). Then the sliding wings ( 7 ) are issued.

It is also possible to dispense with the ring body ( 4 ) and to mount the sliding wing holders ( 5 , 6 ) so that they can pivot from the outer jacket about its longitudinal axis (L). Each of the sliding wing holders ( 5 , 6 ) can then engage its own pull piece ( 9 ), which is moved via a single or two piston-cylinder devices ( 12 ).

Claims (5)

1. Submunition missile, on the fuselage of which sliding wing holders are arranged on the outside, on which sliding wings can be raised, at least one of the sliding wing holders being fastened to an annular body ( 4 ) which is pivotally mounted on the outside of the fuselage about its longitudinal axis and in the transport position one of the other sliding wing holders is pivoted, according to patent application P 37 30 019.9, characterized in that the ring body ( 4 ) is connected at a fastening point ( 8 ) lying outside the fuselage ( 1 ) to a flexible tension piece ( 9 ) that the tension piece is performed (9) through an opening (10) of the hull (1) from its outer circumference in the interior space (11), said in the transport position of the Gleitflügelhalter (5, 6) external to the perimeter of the hull (1) part of the pull tag ( 9 ) is so long that by means of the pull piece ( 9 ) the sliding wing holder ( 5 , 6 ) sch from its transport position into its flight position it is pivotable that a linearly acting force element ( 12 ) acts on the tension piece ( 9 ) in the interior ( 11 ) of the fuselage ( 1 ), the stroke of which is smaller than the movement distance of the fastening point ( 8 ) from the transport position into the flight position of the sliding wing holder ( 5 , 6 ) and that between the force element ( 12 ) and the opening ( 10 ), the pull piece ( 9 ) is guided via a block and tackle ( 13 ). 2. Submunition missile according to claim 1, characterized in that the pull piece ( 9 ) on the ring body ( 4 ) is attached and from the attachment point ( 8 ) to the opening ( 10 ) between the ring body ( 4 ) and the outer circumference of the fuselage ( 1 ) runs. 3. Submunition missile according to claim 1 or 2, characterized in that the force element is a cylinder-piston device ( 12 ). 4. Submunition missile according to one of the preceding claims, characterized in that the opening ( 10 ) is only so large that the traction piece ( 9 ) with its cross section fits through it. 5. Submunition missile according to one of the preceding claims, characterized in that the pull piece ( 9 ) is a wire or a plastic band.