DE102021000573B3 - Carrying and launching system for a multi-body flight system - Google Patents

Abstract

A carrying and launching system for attaching a secondary missile to a primary missile and for releasing the secondary missile from the primary missile in flight comprises a guide rail in a release face of the secondary missile; a locking hook on a release side of the primary missile for engaging the guide rail to form a locking state, wherein the locking hook is rotatable from the locking state to a release state in which the locking hook releases the secondary missile, and wherein the locking hook is formed with a release tab which the secondary missile pushes down away from the primary missile upon rotation of the latch hook to the deployment condition; a locating bolt on the firing side of the primary missile for engaging a locating bore in the secondary missile for horizontal fixation along the guide rail in the locking state and for release in the firing state; an ejector on the release side of the primary missile for pushing the secondary missile axially outward in the release direction in the release state; and a sliding guide on a release side of the primary missile for engaging in the guide rail, so that the secondary missile slides along the guide rail in the released state, pushed by the ejector.

Description

The present invention relates to a delivery and launch system for attaching a secondary missile to a primary missile and for releasing the secondary missile from the primary missile in flight. The present invention also relates to a multi-body flight system with such a carrying and dropping system.

Different loads are intended for attachment to external structures of airborne platforms. For example, launch devices such as guided missiles are attached to aircraft in a mechanically detachable manner. Likewise, several missiles can be coupled together to form a multi-body aircraft. Mechanical connection systems used for these and similar purposes include rail launchers, eject launchers and separation mechanisms via extendable trapezoids (so-called scissor mechanisms). For example, the reference describes U.S. 7,624,947 B2 a carrying and triggering system (English: "Carriage and Release System") for the detachable attachment of weapons to an aircraft.

On the one hand, such fastening systems have to meet certain requirements for airworthiness. On the other hand, the external loads should be able to loosen and separate under defined conditions. Such systems sometimes require considerable mechanical primary energy in the ton range and can also generate significant recoil forces. Many systems are also designed for multiple reuse with a long service life. However, there is an increasing need for systems that are optimized for use in just a few deployments and under highly agile conditions.

The pamphlet DE 38 15 022 A1 describes a device for suspending, scraping off and launching missiles.

Document WO 2019/168 643 A1 describes a rail dropping mechanism and a method for dropping a payload.

The publication US 2020/0 391 866 A1 describes a container release device.

Against this background, the object of the present invention is to find flexibly adaptable solutions for the connection and disconnection of multi-body aircraft.

According to the invention, this object is achieved by a carrying and dropping system with the features of patent claim 1 and by a multi-body flight system with the features of patent claim 12.

Accordingly, a delivery and launch system is provided for attaching a secondary missile to a primary missile and for deploying the secondary missile from the primary missile in flight. The carrying and dropping system comprises a guide rail which is formed in a release side of the secondary missile along a release direction of the secondary missile; a locking hook which is designed on a release side of the primary missile in such a way to engage in the guide rail to form a locking state that the primary missile carries the secondary missile in the locking state on the locking hook, the locking hook being rotatable from the locking state into a release state in which the locking hook releases the secondary missile, and wherein the locking hook is formed with a release lug which pushes the secondary missile downward away from the primary missile upon rotation of the locking hook into the release state; a fixing bolt, which is designed on the release side of the primary missile in such a way to engage in a fixing bore in the secondary missile that the secondary missile is fixed horizontally along the guide rail via the fixing bolt in the locking state and is released by the fixing bolt in the release state; an ejector which is configured on the release side of the primary missile to push the secondary missile axially outwards in the release direction in the release state; and a sliding guide, which is designed on the release side of the primary missile to engage in the guide rail in such a way that the secondary missile, pushed by the ejector, slides along the guide rail in the release state.

Furthermore, a multi-body flight system is provided with a secondary missile and a primary missile, the secondary missile being detachably attached to the primary missile via a carrying and launching system according to the invention

One idea on which the present invention is based is to combine several mechanical design elements that are as simple, robust and inexpensive as possible in order to create a system that is easily scalable and individually adaptable to specific requirements with regard to the aerodynamics and flight mechanics of different aircraft. In concrete terms, at least one locking hook is provided here for one-sided engagement in a guide rail, in order to enable two missiles to be fixed vertically to allow nander. This is supplemented by a fixing bolt, which fixes the two remaining translational degrees of freedom in the transverse and axial directions. A rotation of the locking hook not only removes the fixation in the vertical direction. In addition, a lug on the locking hook pushes the secondary missile down in a vertical direction according to a toggle lever principle, so that the fixation in the horizontal direction is also released at the same time, as a result of which the secondary missile is now completely unlocked and can therefore be triggered. The toggle lever counteracts, among other things, the aerodynamic lift acting in flight, which pushes the secondary missile upwards in the vertical direction, ie against the primary missile. During the subsequent release process, a mechanical ejector in combination with a sliding guide ensures that the secondary missile is released in a controlled manner laterally along the guide rail after the locking mechanism has been released. In this case, the guide rail thus specifies the release direction of the secondary missile, for example laterally outwards and more or less obliquely opposite to the direction of flight of the primary missile.

As a result, a special fastening, locking and unlocking mechanism is provided, in particular for multi-body aircraft, which takes into account the forces and moments from aerodynamic air loads and inertial forces acting on both bodies in the state of separation and enables a controlled separation process. The approach described combines classic design elements of mechanical engineering in an innovative way and can advantageously be implemented in lightweight construction and designed for a limited number of uses. Furthermore, the system can easily be adapted to future aircraft that are still under development or are still to be developed.

Advantageous refinements and developments result from the further dependent claims and from the description with reference to the figures.

According to a development, the locking hook, the ejector and/or the sliding guide can be spring-loaded relative to the secondary missile.

For this purpose, these elements can be arranged in a defined position and orientation during assembly or attachment of the secondary missile to the primary missile and can be pretensioned with a suitably dimensioned spring mechanism. This ensures that the elements practically act by themselves after release and execute a defined movement sequence with preset force and moment ratios.

According to a development, the locking hook and the ejector can be triggered by a gas generator in a timely manner.

Of course, other suitable triggering mechanisms can also be used as an alternative, e.g. purely mechanical solutions, electromechanical actuators, hydraulic or pneumatic approaches, etc.

According to a further development, the guide rail can be designed with a horizontal angle of inclination in the triggering side of the secondary missile, so that the guide rail is oriented obliquely backwards in relation to a flight direction of the primary missile in the locking state.

In this development, aerodynamic resistance and suction are used to support or facilitate the separation process. It is thus based on a natural separation direction in order to make the ejection process as free of force and moment as possible.

According to a development, the fixing bolt can be formed on the sliding guide.

In general, it is advantageous if the system is restricted to as few individual components as possible in order to keep the complexity and thus the potential susceptibility to errors low. If the fixing bolt is attached to and/or on the sliding guide, e.g. as a projecting lug, the complementary fixing bore can be provided on the side of the guide rail. The sliding guide together with the bolt can be lifted with the rotary movement of the locking hook or hooks until the bolt is freed from the hole. The sliding guide can be designed and dimensioned in such a way that it continues to slide against the guide rail and presses against it with a certain pretension in order to enable a controlled sliding movement.

According to a further development, the ejector can bear against the secondary missile at an axially inward end of the guide rail in the locked state.

In a specific example, the ejector can be designed as a rotating element with spring preload, which in the locked state rests directly against the axially inner end of the guide rail and, after unlocking by locking hooks and fixing bolts Secondary missile by means of the bias pushes laterally outwards.

According to a development, the locking hook, the ejector and/or the sliding guide can be designed to rotate from the deployment state into a stowed state within the primary missile as soon as the secondary missile has been ejected.

These elements can thus be folded away surface-neutrally in an aerodynamically advantageous manner. For this purpose, their prestressing relative to the secondary missile can be used in a particularly elegant manner, which, after the secondary missile has been ejected, leads to the elements being continued in their effective direction of movement, e.g. along their axes of rotation, and thus being folded in.

According to a further development, the secondary missile can have a sliding locking plate which is designed to close the guide rail of the secondary missile as soon as it has been dropped.

The guide rail on the secondary missile can thus also be closed surface-neutrally with a prestressed sliding locking plate or the like. For example, the sheet metal can be held back by the locking hooks and/or the sliding guide. As soon as the secondary missile is released, the prestressed metal sheet is no longer blocked by the locking elements and can therefore slide in front of the guide rail and close it.

Likewise, the primary missile may have one or more sliding strike plates designed to surface-neutrally close the appropriate elements of the primary missile (i.e., the locking hook(s), the ejector(s), and/or the slide guides) once the secondary missile has been jettisoned and placed in the stowed state within of the primary missile have been brought.

According to a further development, the primary missile can have a number of locking hooks for engaging in the guide rail.

For example, two locking hooks can be provided per guide rail. In principle, however, it can also be advantageous for certain applications to provide three, four or more such hooks for each guide rail.

According to a further development, the secondary missile can have several guide rails. The primary missile can have locking hooks, fixing bolts, ejectors and/or sliding guides associated with each guide rail.

The above configurations and developments can be combined with one another as desired, insofar as this makes sense. Further possible configurations, developments and implementations of the invention also include combinations of features of the invention described above or below with regard to the exemplary embodiments that are not explicitly mentioned. In particular, the person skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.

• 1 schematische Perspektivansicht eines Mehrkörperflugsystems von schräg vorne gemäß einer Ausführungsform der Erfindung;
• 2 schematische Perspektivansicht eines Trage- und Abwurfsystems gemäß einer Ausführungsform der Erfindung, wie es in dem Mehrkörperflugsystem der 1 zur Anwendung kommt; und
• 3-5 schematische Perspektivansichten des Trage- und Abwurfsystems aus 2, die die zeitliche Abfolge während eines Auslösevorgangs darstellen.

The present invention is explained in more detail below with reference to the exemplary embodiments given in the schematic figures. They show:

• 1 schematic perspective view of a multi-body flight system obliquely from the front according to an embodiment of the invention;
• 2 schematic perspective view of a carrying and launching system according to an embodiment of the invention, as in the multi-body flight system 1 applies; and
• 3-5 schematic perspective views of the carrying and dropping system 2 , which show the time sequence during a tripping process.

The accompanying figures are intended to provide a further understanding of embodiments of the invention. They illustrate embodiments and, together with the description, serve to explain principles and concepts of the invention. Other embodiments and many of the foregoing advantages will become apparent by reference to the drawings. The elements of the drawings are not necessarily shown to scale with respect to one another.

In the figures of the drawing, elements, features and components that are the same, have the same function and have the same effect--unless stated otherwise--are each provided with the same reference symbols.

1 shows a schematic perspective view of a multi-body flight system 100 according to an embodiment of the invention. 2 shows a schematic perspective view of a carrying and launching system 1 according to an embodiment of the invention, as in the multi-body flight system 100 of FIG 1 is applied.

In this exemplary embodiment, the multi-body flight system 100 comprises a second darmissile 2 and a primary missile 3. The secondary missile 2 is releasably attached to the primary missile 3 via the carrying and dropping system 1 from below and can be triggered laterally in a triggering direction 6 and dropped from there at any time during flight.

The multi-body flight system 100 can be a modular guided missile system, for example, which can be divided into two, three or more individual components during flight. For example, as in the present case, a single secondary missile can be detachably coupled to a main missile. In principle, however, two, three or more secondary missiles can also be connected to a central main body in a corresponding manner.

The solution approach for the carrying and dropping system 1 described below provides a combination of several mechanical elements and is designed to be able to meet the specific aerodynamic and flight mechanical requirements for separating several aircraft. The approach is intended for a limited number of applications, with low operating energy and minimal reaction to the bodies to be separated during the separation process.

The carrying and dropping system 1 comprises two guide rails 4, each of which is formed in a triggering side 5 of the secondary missile 2, e.g. The guide rails 4 and thus also the triggering direction 6 are aligned at an angle of inclination 14 relative to an axial longitudinal extension of the two missiles 2, 3.

The guide rails 4 are thus oriented axially outwards and obliquely backwards in relation to a flight direction 16 of the missiles 2, 3.

Each guide rail 4 is provided with a rail receptacle 15 along its longitudinal extent in the release direction 6, which allows the engagement of several locking and separation components that are formed on a release side 8 of the primary missile 3, e.g. an underside of the primary missile. It goes without saying that the number of two guide rails 4 with associated locking and triggering elements shown here as an example only serves as an example. As will be apparent to those skilled in the art, the number of elements used can vary depending on the application. For example, a single guide rail may be sufficient in certain applications, while three or more rails may be used in other applications.

The locking and release elements on the release side 8 of the primary missile 3 include for each guide rail 4 two locking hooks 7 for vertical fixation of the secondary missile 2 in a locked state, a fixing bolt 10 for horizontal fixation along the respective guide rail 4 in the locked state, an ejector 12 for pushing of the secondary missile 2 along the guide rail 4 during a triggering process following unlocking, and a sliding guide 13 for the controlled guidance of the secondary missile 2 along the guide rail 4 during the triggering process. The fixing bolt 10 is arranged as a protruding lug on the sliding guide 13 in order to be able to engage in a complementary fixing bore 11 in the guide rail 4 .

All of these structural elements are prestressed in relation to the secondary missile 2 by means of defined springs and act in a chronologically coordinated sequence after the separation process of the two missiles 2, 3 has been initiated. For example, the components can be triggered or driven by a gas generator or the like. Here, the locking hooks 7 are designed to be rotatable about a first axis of rotation R1. Correspondingly, the sliding guide 13 can be rotated about a second axis of rotation R2 and the ejector 12 can be rotated about a third axis of rotation R3 (cf. 2 ).

The chronological sequence of a separation process between the secondary missile 2 and the primary missile 3 is with reference to 3 until 5 described below. These figures show three states in the course of separation. 3 shows the locked state in which both missiles 2, 3 are coupled to one another and fixed to one another. In 4 the system is already unlocked and the release process can be started. In 5 the secondary missile 2 is finally ejected along the triggering direction 6 .

As in 2 until 5 is shown, two locking hooks 7 are formed on the triggering side 8 of the primary missile 3 for each guide rail 4 to engage in the respective guide rail 4 to form the locking state. As a result, the secondary missile 2 is fixed to the primary missile 3 in the vertical direction, ie perpendicular to the guide rail 4 . In the locked state, the primary missile 3 thus holds or carries the secondary missile 2 on its release side 8 by means of the locking hooks 7.

Each locking hook 7 is spring-loaded and, after corresponding release, can be rotated from the locking state into the triggering state, in which the respective locking hook 7 releases the secondary missile 2 . this is in 4 shown (see arrows). As can be seen there, each locking hook 7 is released in a defined manner by being guided away by means of a rotary movement counter to the direction of flight 16, ie backwards, about the first axis of rotation R1. Each locking hook 7 is designed with a release lug 9 which pushes the secondary missile 2 downward away from the primary missile 3 when the locking hook 7 rotates into the release state. This toggle lever approach thus counteracts the aerodynamic lift 19 which would otherwise press the secondary missile 2 vertically upwards against the primary missile 3 and thus counteract a separation of the two bodies.

As continues in 2 until 5 is shown, a fixing bolt 10 is provided on the triggering side 8 of the primary missile 3 for each guide rail 4 . The fixing bolt 10 is designed on the release side 8 of the primary missile 3 to engage in a fixing bore 11 in the guide rail 4 and/or on the guide rail 4 of the secondary missile 2 such that the secondary missile 2 in the locked state can be moved horizontally via the fixing bolt 10 along the guide rail 4 is fixed. The secondary missile 2 in the locked state is thus fixed in all three spatial directions on the primary missile 3 (via the locking hooks 7 in the vertical direction and via the fixing bolts 10 in the transverse and axial directions). By providing two guide rails 4 with corresponding locking counter-elements on the primary missile 3, the secondary missile 2 can thus be securely fixed in all directions.

The rotation of the locking hooks 7 described above presses the secondary missile 2 downwards, with the fixing bolts 10 also being pulled out of the associated fixing bores 10 . The system 1 can thus be completely unlocked in an elegant manner by simply rotating the pretensioned locking hooks 7 .

In order to prevent uncontrolled lateral relative movements, the system 1 also includes a sliding guide 13 for each guide rail 4 on the release side 8 of the primary missile 2. This sliding guide 13 is designed as a web for engaging in the associated guide rail 4 in order to ensure a controlled sliding movement along a wall of the To allow rail receptacle 15, and for this purpose similar to the locking hook 7 biased by a suitably dimensioned spring mechanism against the secondary missile 2. The sliding guide 13 can be rotated about a second axis of rotation R2. Regarding 3 until 5 this means that the sliding guide 13 presses against the guide rail 4 along its length.

As in 2 until 5 As can be seen, the system 1 further comprises an ejector 12 for each guide rail 4, which is formed on the triggering side 8 of the primary missile 3 and rests against an axially inward end of the respective guide rail 4 in the locked state. Like the sliding guide 13, the ejector 12 is spring-loaded relative to the secondary missile 2 and can rotate about a third axis of rotation R3 after the locking has been released (cf. 5 ).

As soon as the locking is released, the ejector 12 thereby pushes the secondary missile 2 axially outwards in the triggering direction 6, with the secondary missile 2 being pushed by the ejector 12 and guided by the sliding guide 13 sliding along the guide rail 4 (i.e. to the right in 5 , see arrows in 5 ). In this case, the secondary missile 2 can optionally already fall away from the primary missile 3 in a downward direction. Both the release nose 9 and the fixing bolts 10 keep the secondary missile 2 at a distance from the primary missile 3 in the vertical direction. Due to the angle of inclination 14 of the guide rails 4, the aerodynamic resistance 17 and the suction effect 18 are utilized during the lateral movement of the secondary missile 2 in order to ensure that the two missiles 2, 3 separate as frictionlessly as possible. The system 1 thus enables the secondary missile 2 to be held and guided for as long as possible in the course of the unlocking and dropping process, in order to allow it to slide away as controlled and recoil-free as possible.

In order to further improve the aerodynamic behavior, the elements of the system 1 can be covered or retracted after the secondary missile 2 has been dropped. For this purpose, the prestressing of the locking hooks 7, the ejector 12 and the slideway 13 can advantageously be used, in that these elements are guided further along their respectively effective direction of movement, i.e. around their respective axes of rotation R1-R3 (the secondary missile 2 has already been released and is therefore not blocked more the respective movement). The elements can thus rotate from the deployed state to a stowed state within the primary missile 3 as soon as the secondary missile 2 has been jettisoned, so that the elements terminate in a surface-neutral manner with the deployment side 8 of the primary missile 3 .

The guide rails 4 on the secondary missile 2 can also be closed without affecting the surface, e.g. by sliding a sliding locking plate (not shown) over the rail mounts 15 (due to a suitable pretension), which was previously held back by the locking hook 7 and the sliding guide 13.

In the foregoing Detailed Description, various features have been grouped together in one or more examples to improve the rigor of presentation. However, it should be understood that the above description is merely illustrative and in no way restrictive. It is intended to cover all alternatives, modifications, and equivalents of the various features and embodiments. Many other examples will be immediately and immediately apparent to those skilled in the art in view of the above description.

The exemplary embodiments were selected and described in order to be able to present the principles on which the invention is based and its possible applications in practice in the best possible way. This enables those skilled in the art to optimally modify and use the invention and its various exemplary embodiments in relation to the intended application. In the claims and the description, the terms “including” and “having” are used as neutral terms for the corresponding terms “comprising”. Furthermore, the use of the terms “a”, “an” and “an” should not fundamentally exclude a plurality of features and components described in this way.

Reference List

1

carrying and dropping system

2

secondary missile

3

primary missile

4

guide rail

5

Release side of the secondary missile

6

release direction

7

locking hook

8th

Release side of the primary missile

9

release tab

10

fixing bolts

11

fixing hole

12

ejector

13

sliding guide

14

tilt angle

15

rail mount

16

flight direction

17

aerodynamic drag

18

aerodynamic suction

19

boost

100

multi-body flight system

R1

first axis of rotation

R2

second axis of rotation

R3

third axis of rotation

Claims (12)

Carrying and launching system (1) for attaching a secondary missile (2) to a primary missile (3) and for releasing the secondary missile (2) from the primary missile (3) in flight, comprising: a guide rail (4) which is formed in a release side (5) of the secondary missile (2) along a release direction (6) of the secondary missile (2); a locking hook (7) which is designed on a triggering side (8) of the primary missile (3) to engage in the guide rail (4) to form a locking state such that the primary missile (3) engages the secondary missile (2) in the locking state on the carries locking hook (7), wherein the locking hook (7) can be rotated from the locking state into a release state in which the locking hook (7) releases the secondary missile (2), and wherein the locking hook (7) is designed with a release nose (9). which pushes the secondary missile (2) downwards away from the primary missile (3) when the locking hook (7) rotates into the release state; a fixing bolt (10) which is designed on the release side (8) of the primary missile (3) to engage in a fixing bore (11) in the secondary missile (2) in such a way that the secondary missile (2) in the locked state via the fixing bolt (10 ) is fixed horizontally along the guide rail (4) and is released from the fixing bolt (10) in the release state; an ejector (12) which is designed on the release side (8) of the primary missile (3) to push the secondary missile (2) in the release state in the release direction (6) axially outwards; and a sliding guide (13) which is designed on the release side (8) of the primary missile (3) to engage in the guide rail (4) in such a way that the secondary missile (2) is pushed against the guide rail (4) by the ejector (12) in the release state 4) slides along. Carrying and dropping system (1) according to claim 1 , wherein the locking hook (7), the ejector (12) and/or the sliding guide (13) are spring-biased relative to the secondary missile (2). Carrying and dropping system (1) according to claim 1 or 2 , wherein the locking hook (7) and the ejector (12) are timed to be triggered by a gas generator. Carrying and dropping system (1) according to one of Claims 1 until 3 , wherein the guide rail (4) is formed with a horizontal angle of inclination (14) in the triggering side (5) of the secondary missile (2), so that the guide rail (4) in the locking state is inclined backwards relative to a flight direction (16) of the primary missile ( 3) is aligned. Carrying and dropping system (1) according to one of Claims 1 until 4 , wherein the fixing bolt (10) is formed on the sliding guide (13). Carrying and dropping system (1) according to one of Claims 1 until 5 , wherein the ejector (12) rests against the secondary missile (2) in the locking state at an axially inward end of the guide rail (4). Carrying and dropping system (1) according to one of Claims 1 until 6 , wherein the locking hook (7), the ejector (12) and/or the sliding guide (13) are designed to rotate from the deployed state to a stowed state within the primary missile (3) as soon as the secondary missile (2) is jettisoned. Carrying and dropping system (1) according to claim 7 , wherein the primary missile (3) has at least one sliding locking plate which is designed to close the locking hook (7), the ejector (12) and/or the sliding guide (13) in the primary missile (3) as soon as it is in the stowed state have been brought. Carrying and dropping system (1) according to one of Claims 1 until 8th , wherein the secondary missile (2) has a sliding locking plate which is designed to close the guide rail (4) of the secondary missile (2) as soon as it has been jettisoned. Carrying and dropping system (1) according to one of Claims 1 until 9 , wherein the primary missile (3) has a plurality of locking hooks (7) for engaging in the guide rail (4). Carrying and dropping system (1) according to one of Claims 1 until 10 , the secondary missile (2) having a plurality of guide rails (4), the primary missile (2) having locking hooks (7), fixing bolts (10), ejectors (12) and/or sliding guides (13) associated with each guide rail (4). Multi-body flight system (100) with a secondary missile (2) and a primary missile (3), wherein the secondary missile (2) on the primary missile (3) via a carrying and launching system (1) according to one of Claims 1 until 11 is releasably attached.

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