Patent Description:
In order to reduce the radar signature of an aerial vehicle, for example a fighter aircraft, payloads have to be arranged in closable, internal bays. Payloads of this kind may include weapons systems, for example. In order to optimize flight properties in the subsonic and supersonic range, it is advisable for the aerial vehicle to be constructed in the smallest and most compact way possible, in order to save weight and increase the thrust-to-weight ratio and at the same time reduce the fuselage cross section, which increases the slenderness ratio and reduces the wave impedance. The aerial vehicle in question should be capable of deploying the payload within the entire flying range from low subsonic to high supersonic speeds. However, an open bay causes an unsteady air flow at higher speeds, which can influence the process of releasing the payload, and also aero-acoustic loads which are induced in the structure of the aerial vehicle.

In order to improve the air flow, extendable wind deflectors are frequently arranged in front of the bay in the direction of flight, said wind deflectors serving to divert the air flow from the bay. Furthermore, it is known in the art for an oblique rear wall to be arranged at a rear end in the direction of flight, in order to delimit the bay, which rear wall influences the air flow within the bay, in order to reduce the aero-acoustic load. Means of this kind are provided in the F-<NUM> Raptor and the J-<NUM>, for example. However, these features increase the total length of the bay concerned, wherein the height and length of the bay are roughly proportionate to the length and height of the payload in the bay. Furthermore, in addition to the payload itself there is a hinge mechanism for cover flaps of the bay and also a corresponding drive and an additional driver for the necessary width of the bay.

<CIT> describes an aircraft autonomous, reconfigurable internal weapons bay for launching different types of weapons such as air-to-air and air-to-ground missiles with folding or fixed fins. The weapons bay is characterized by having internally folding doors which provide separate shallow compartments. The individual compartments are adaptable for carrying a multitude of different types and sizes of missiles internally or semisubmerged.

<CIT> describes a weapons bay in an aircraft, comprising an aperture in an aircraft fuselage, a platform movable between a first position in which the platform is retracted from the aperture and a second position in which the platform substantially coincides with the aperture, suspension means for suspending stores from the platform. At least one door is arranged to close the aperture when the platform is in the first, retracted position, so that the stores are arranged to be totally accommodated within the aircraft fuselage.

<CIT> describes an aircraft that has a weapons bay. An equipment container is provided which is applied into the weapons bay. The container has a mounting system for fastening a suspended bomb. The container is provided with electrical and or optical connecting mechanisms which can be uncoupled in the weapons bay, such as a bomb suspension tower.

<CIT> describes a radial sonobuoy launch system comprising a clam-shell launch tube and a method for launching a sonobuoy. The clam-shell launch tube radially releases a sonobuoy and the clam-shell launch tube is reloaded during flight. The sonobuoys are pneumatically ejected about parallel to the airstream. A pressure boundary structure, having a door and a gate, maintains cabin pressure during reloading and launching. Support arms and drive arms evenly distribute the ejection accelerations from the firing mechanism and guide the trajectory of the sonobuoy during release. A clam-shell launch tube is capable of launching a multitude of differently sized sonobuoys.

<CIT> desribes a container retention and a release apparatus. An example container retention and release apparatus includes an actuator, a swaybrace coupled to the actuator, and a clamp pivotally coupled to the swaybrace. The clamp pivots between a clamping position to retain a container and a release position to release a container.

The problem addressed may be regarded as that of proposing a device for accommodating and for releasing a payload on an aerial vehicle, which device requires a smaller installation space in a cavity than devices known in the art, yet causes an at least equally low aero-acoustic load when there is a flow through the cavity. In particular, the device is to dispense with deflectors and other surfaces which are customarily used to improve the aero-acoustic properties.

This problem is solved by the subject matter of the independent Claim <NUM>. Further embodiments result from the dependent claims and from the following description.

A device for accommodating and for releasing a payload on an aerial vehicle is proposed, which device has a mounting frame for accommodating the payload, a linear moving means that can be positioned in a cavity of the aerial vehicle, the cavity having an opening, said moving means having a base and at least one holding element, and also a release device arranged on the mounting frame, wherein the mounting frame has a largely planar opening area which is surrounded by an opening edge, wherein the moving means is coupled with the mounting frame on a side of the mounting frame facing away from the opening area by the at least one holding element, wherein the moving means is designed to move the mounting frame linearly and vertically in the direction of the opening in the cavity at a variable distance from the base, wherein the release device is designed to hold the payload in the mounting frame, such that the mounting frame encloses or surrounds the payload at least in part when the mounting frame is in a neutral position or in a release position, wherein the linear moving means is configured to move the mounting frame between the neutral position and the release position, and wherein the release device is designed to move the payload selectively from the mounting frame, where necessary and when the mounting frame is in the release postion, via the opening edge and in a direction facing away from the base and to release the payload.

The device can be deployed on an aerial vehicle and is used, in particular, to accommodate and release a payload on an underside of the aerial vehicle. For this purpose, the aerial vehicle may have a bay or a cavity which is predominantly closed during flight by flaps referred to later on and can be selectively opened to release the payload. The linear moving means is then arranged in the cavity and has a base which must be arranged in the cavity in an immovable, i.e., in a structurally fixed, manner. The base may have one or multiple components, with which the moving means can be connected to the aerial vehicle or to the structure thereof. The base is therefore used following installation as the reference point for the movement that can be performed by the moving means.

The mounting frame is an element which is not provided in customary devices to accommodate and release a payload, and which must be arranged along with the payload in the cavity. The mounting frame in this case encloses or surrounds the payload at least in part. The mounting frame preferably has a thin profile, so that the payload projects beyond the mounting frame. The mounting frame may have a shape which forms a rectangle at its outer edges. Inner contours of the mounting frame are preferably adapted to the payload. Depending on the configuration of the payload, the inner contours of the mounting frame may therefore deviate from a purely rectangular shape.

The actual mounting of the payload is guaranteed by the release device which is mechanically coupled with the mounting frame and is detachably connected to the payload. By means of the release device, which is particularly able to move the payload at right angles to the opening area, said payload can be moved out of the mounting frame. The mounting frame is therefore movable relative to the cavity and can be moved as far as the opening area.

The device has the particular advantage that the mounting frame has a favourable influence on the aero-acoustic properties of the cavity, in order to move the payload in said cavity. During the flight, the mounting frame is moved along with the payload facing away from an opening in the cavity in the direction of the inside of the aerial vehicle, and the cavity is closed outwardly. The aerial vehicle therefore has a completely closed surface in this state. In order to release the payload, the mounting frame is therefore moved in the direction of the opening in the cavity, so that the payload is adjacent to the opening in the cavity and can project therefrom. The mounting frame preferably ends flush with the opening in the cavity in this state, so that gaps between the mounting frame and an opening contour of the cavity are closed. The entry of an air flow running to the cavity is thereby largely prevented. Extendable deflectors, oblique end faces or other aerodynamic means for improving the aero-acoustic properties are not therefore necessary. The installation space required for the device according to the invention, in particular parallel to the direction of flight, can thereby be substantially reduced compared with solutions known in the art.

The mounting frame may have a flat underside. This is particularly advisable in the case of aerial vehicle which have a flat underside, at least in sections, in which an opening of the cavity ends, from which the payload is to be delivered. The mounting frame then ends flush with the adjacent surface of the underside. The gap dimensions between the adjacent surface and the mounting frame can be minimized with suitable guidance of the mounting frame, in order to create a largely closed surface with the mounting frame. The aero-acoustic properties are therefore substantially improved.

In addition, the device may have at least one flap for the selective opening of the cavity which can be mounted in a swivelable manner on the aerial vehicle, wherein the at least one flap has at least one lever arm in each case, which is coupled with the moving means, so that the at least one flap is opened or closed during movement of the moving means. The at least one flap may be directly coupled with a structure of the aerial vehicle via the at least one lever arm, so that a predetermined movement can be carried out. The structure may comprise a payload housing forming the cavity, for example, on which the at least one flap is arranged in a swivelable and/or movement-guided manner. A possible embodiment for this purpose is explained in greater detail below. Coupling with the moving means may take place by mounting the at least one flap by means of the at least one lever arm on the mounting frame. If the mounting frame is moved by the moving means, the at least one flap follows the movement of the mounting frame and is therefore likewise moved by the moving means.

The at least one flap may be forced by a spring force into an open position, wherein the at least one lever arm is mounted in a guide element, rests against the mounting frame due to the spring force and is displaced in the guide element by the spring force during movement of the mounting frame. If the mounting frame is moved to the opening of the cavity, the at least one flap can followi the movement of the mounting frame through the continuously adjacent spring force and thereby perform an opening movement. Equally, the at least one flap is closed when the mounting frame is moved in the direction of the inside of the aerial vehicle. A flexible coupling is produced by the spring force. Particularly when using elongate flaps, distortion of the at least one flap can be prevented during a dynamic flight movement of the aerial vehicle.

The at least one lever arm may have a guide body which is guided in a guide track as the guide element which can be attached in the aerial vehicle in a structurally fixed manner. The guide track may be arranged on a front end of a payload housing forming the cavity, for example, and configured as a curved recess or a curved projection. The guide body is configured in a manner corresponding thereto and may be guided in the guide track between a first position which corresponds to a closed at least one flap and a second position which corresponds to an open at least one flap. The guide body may slide along the guide track or be rolled along by means of rolling bodies.

The moving means may have a spindle drive. This may comprise an electric motor or a hydraulic motor which is coupled with an elongate spindle, said spindle being rotated about its longitudinal axis. The spindle may be a threaded spindle or a recirculating ball spindle. By rotating in a first direction, the mounting frame is moved in the direction of the opening in the cavity. During rotation in a second direction contrary to the first direction, the mounting frame is however moved into the inside of the cavity. The spindle drive is extremely reliable, robust, easily adapted to the anticipated loads and easy to maintain.

The spindle drive may be arranged largely parallel to the opening area and connected at each of two ends opposite one another to a rocker lever that can be mounted in a structurally fixed manner, wherein the respective rocker lever can be coupled with the mounting frame via a connecting link mounted in a swivelling manner on both sides. Two sides of the mounting frame which lie opposite one another are therefore moved simultaneously by the spindle drive. The spindle drive may be arranged in a floating manner between the two rocker levers and perform an axial expansion or contraction. The rocker levers convert the change in length of the spindle drive parallel to the opening area into a movement with a component vertical to the opening area. The connecting links may be swivelable on both sides and realized as a pendulum support, for example. They lead to a purely linear movement of the mounting frame in a direction vertical to the opening area.

A further rocker lever which is arranged parallel to, and at a distance from, the other rocker lever and is mechanically coupled may be provided at each end of the spindle drive, wherein the rocker levers at each of two ends are arranged in a mirror-inverted manner to each other. The mounting frame is therefore coupled with the spindle drive by a total of four rocker levers, so that a uniform movement can be performed vertically to the opening area.

A connecting line of hinged joints of each rocker lever and of hinged joints of the associated connecting link may form a straight line when the mounting frame is in an extended position. The extended position is thereby clearly defined mechanically to begin with. When a straight line is adopted, a force effect directed from outside on the mounting frame, independently of the spindle drive, can also be conducted completely into the structure of the aerial vehicle.

At least one of each pair of rocker levers and the associated connecting link may have an end stop which is designed so that the associated rocker lever and the associated connecting link form the straight line in the extended position. The straight line may therefore be achieved automatically when the moving means is completely extended. The end stop is furthermore advantageous, in order for the extended position to be adopted and retained very precisely. It is conceivable for the moving means to stop automatically when it reaches an end stop of this kind on account of a substantial load increase being detected.

The device may furthermore have a linear guide for conducting the mounting frame in a direction at right angles to the opening area. The linear guide allows the mounting frame to be guided in a direction parallel to an opening in the cavity. Very precise placement of the mounting frame in the opening can thereby be achieved, so that gap dimensions between the mounting frame and the opening can be reduced to a minimum.

The device may also have two side walls arranged parallel to one another and spaced apart from one another and two front walls opposite one another and connecting the side walls, wherein the front walls each have at least one guide track. The guide track may realize the previously represented guide element in which the at least one lever arm is guided. Through the structurally fixed arrangement of the guide track, the relative movement of the at least one flap on the aerial vehicle can be precisely defined. If multiple flaps should be used, each of the flaps may be assigned a pair of guide tracks lying opposite one another. In this case, the flaps lying opposite one another are parallel to one other and congruent, meaning that the flap concerned can be opened uniformly and in and at least largely distortion-free manner.

It is preferable for the mounting frame to enclose a gap of less than <NUM> with the side walls and the front walls. The aero-acoustic properties can thereby be affected very favourably; the gap size is particularly small. This can be achieved, in particular, through a precise guidance and/or uniform movement of the mounting frame.

The invention further relates to an aerial vehicle, having a structure with a cavity formed therein and a device arranged in the cavity according to the preceding description.

The cavity may have an opening which is arranged on the underside of the aerial vehicle, so that the payload can be released from the underside of the aerial vehicle.

The exemplary embodiments are looked at in greater detail below with the help of the attached drawings. The representations are schematic and not true-to-scale. The same reference signs relate to the same or similar elements. In the drawing:.

<FIG> shows a device <NUM> for accommodating and deploying a payload <NUM> on an aerial vehicle. The device <NUM> comprises a mounting frame <NUM> for accommodating the payload <NUM>, which has a flat underside <NUM> in this exemplary embodiment, in which a planar opening area <NUM> lies. The opening area <NUM> is surrounded by an opening edge <NUM> which forms a largely rectangular area. The mounting frame <NUM> is provided to enclose the payload <NUM> at least partially and to move it, where necessary, in a vertical direction, i.e., vertically to the area formed by the opening edge <NUM>. The payload <NUM> projects partially from the mounting frame <NUM> beyond the opening area <NUM>. The opening area <NUM> is arranged on the underside <NUM>, so that the payload <NUM> is released downwardly.

A release device <NUM> is provided for holding and moving the payload <NUM>, said release device comprising two curved pieces <NUM> which are linearly movable and which are each arranged on a linear drive <NUM>. The linear drives <NUM> are arranged on the mounting frame <NUM> and oriented in such a manner that the curved pieces <NUM> can be moved transversely to the opening area <NUM>, i.e., downwards and upwards. They hold the payload <NUM> and can move it from the mounting frame <NUM>, where necessary, and release it. The linear drives <NUM> may comprise spindle drives, hydraulic actuators or other means which can perform a purely linear movement.

The particular advantage of this exemplary embodiment of the device <NUM> lies in the fact that a cavity can be configured free from wind deflectors or similar flow-mechanical means in an aerial vehicle in which the device <NUM> is to be arranged, so that optimal aero-acoustic properties are exhibited wherever possible when the payload <NUM> is released. The installation position is depicted in the figures shown below.

<FIG> shows the release device <NUM> which is arranged on the mounting frame <NUM>. In this case, flaps <NUM> are furthermore depicted which each have lever arms <NUM> which extend in the direction of the mounting frame <NUM> and beyond and are each laterally bent slightly outwards. A bend angle may be roughly <NUM>° and may determine the opening angle of the flaps <NUM> according to the details specified below. The flaps <NUM> are mounted on the mounting frame <NUM> so as to be swivelable about an axis <NUM>. For this purpose, a series of hinges <NUM> is provided which are arranged on the opening edge <NUM> of the mounting frame <NUM>.

<FIG> shows a payload housing <NUM>, in which a cavity <NUM> is provided which opens out into a fuselage skin <NUM>. The payload housing <NUM> has two side walls <NUM> arranged parallel to one another and spaced apart from one another, wherein front walls <NUM> run between two ends of the side walls <NUM> and thereby complete the payload housing <NUM>. The arrangement shown in <FIG> may be integrated into the cavity <NUM>, so that the flaps <NUM> end flush with the fuselage skin <NUM> and the release device <NUM> is fastened to an upper installation portion <NUM>. The fuselage skin <NUM> and also the payload housing <NUM> are part of an aerial vehicle which carries the payload and releases it from the cavity <NUM> where necessary.

According to the invention, it is provided that the mounting frame <NUM> is movable along with the release device <NUM> within the cavity at right angles to the fuselage skin <NUM> or to an opening <NUM> formed therein. If the mounting frame <NUM> is moved in the direction of the opening <NUM>, the payload <NUM> projects partially beyond the fuselage skin <NUM> and can finally be released by the release device <NUM>. In this case, the mounting frame <NUM> closes any gaps between the payload <NUM> and the opening <NUM> almost completely. In this way, the aero-acoustic properties are favourably influenced.

<FIG> shows moving means <NUM> for moving the mounting frame <NUM>. The moving means <NUM> has a spindle drive <NUM> which is arranged parallel to the opening area <NUM> and preferably oriented parallel to the longitudinal axis of the aerial vehicle. The spindle drive <NUM> has a first end <NUM> and a second end <NUM>. Operating the spindle drive <NUM> causes the two ends <NUM> and <NUM> to move away from, or towards, one another. The spindle drive <NUM> also has a guide lever <NUM> which is mounted in a swivelable manner transversely to the movement direction. In this way, the spindle drive <NUM> is held on the payload housing <NUM> in a narrowly restricted range of motion.

Two rocker levers <NUM> are arranged at each of the two ends <NUM> and <NUM>, said rocker levers being mounted in the payload housing <NUM> in a swivelable manner. For this purpose, they are arranged on an axle <NUM>, for example, which runs transversely to the movement direction of the spindle drive <NUM>. The axle <NUM> is at the same time used for coupling the two rocker levers <NUM>.

The rocker levers <NUM> are each connected to the mounting frame <NUM> by a pivotably fastened connecting link <NUM>. The connecting links <NUM> more or less act as a pendulum support in each case. When the spindle drive <NUM> is extended, the two ends <NUM> move apart from one another and the rocker levers <NUM> are moved out of their oblique position in <FIG> in a substantially vertical orientation. In this way, outer bearing points <NUM> of the swivelable connecting links <NUM> move away from the spindle drive <NUM> downwards. The mounting frame <NUM> is thereby moved downwards. The spindle drive <NUM> can be displaced by the guide lever <NUM> in a compensating manner parallel to its linear movement, so that the rocker levers <NUM> are moved uniformly at both ends <NUM> and <NUM>.

<FIG> shows the device <NUM> with the mounting frame <NUM> in a neutral position, i.e., a position spaced inwardly as far away from the fuselage skin <NUM> as possible. The rocker levers <NUM> are at an angle α of approximately <NUM>° to the spindle drive <NUM>. The flaps <NUM> are closed and the payload <NUM> is located completely within the aerial vehicle or the cavity <NUM>. <FIG> shows the guide lever <NUM> with the spindle drive <NUM> completely extended.

<FIG> show the rocker levers <NUM> in the retracted position (neutral position) (<FIG>) or with the mounting frame <NUM> completely lowered (<FIG>). The individual rocker levers <NUM> have a first end stop <NUM> on a side facing away from the spindle drive <NUM>. The connecting links <NUM> face a second end stop <NUM> on the corresponding side. If the rocker lever <NUM> is located in a vertical position and is therefore at an angle of roughly <NUM>° to the spindle drive <NUM>, the first end stop <NUM> and the second end stop <NUM> come into flush planar contact. Further swivelling of the rocker levers <NUM> is not possible in this case and the completely extended position of the mounting frame <NUM> is guaranteed. In this case, the rocker levers <NUM> and the associated connecting links <NUM> each form a straight line.

The process involved in opening the flaps <NUM> is depicted in greater detail in <FIG> shows the neutral position in which the mounting frame <NUM> is spaced as far away as possible from the fuselage skin <NUM> in the direction of the inside of the cavity <NUM>. The flaps <NUM> are closed in this case. The lever arms <NUM> project substantially vertically from the flaps <NUM> or the fuselage skin <NUM> in the direction of the mounting frame <NUM>, penetrate these and are bent outwardly in the lateral direction. The ends of the lever arms <NUM> each have a guide body <NUM> which is guided in a guide track <NUM> of a side wall <NUM> of the payload housing <NUM> (see <FIG>). If the mounting frame <NUM> is moved into the release position in <FIG>, the hinges <NUM> of the flaps <NUM> are moved along outwardly. The lever arms <NUM> follow the movement and the guide bodies <NUM> are moved in the associated guide track <NUM>, so that they move laterally to open, in addition to the downwardly oriented movement. The guide tracks <NUM> of two adjacent flaps <NUM> may have a substantially curved V-shape.

In addition, it can be seen in <FIG> that the flaps <NUM> are spring-mounted by means of a torsion spring <NUM> on the hinges <NUM> concerned. This results in the flaps <NUM> constantly being forced into a closed position.

Claim 1:
Device (<NUM>) for accommodating and for releasing a payload (<NUM>) on an aerial vehicle, having:
a mounting frame (<NUM>) for accommodating the payload (<NUM>),
a linear moving means (<NUM>) that can be positioned in a cavity (<NUM>) of the aerial vehicle, the cavity (<NUM>) having an opening (<NUM>), said moving means having a base and at least one holding element,
a release device (<NUM>) arranged on the mounting frame (<NUM>),
wherein the mounting frame (<NUM>) has a largely planar opening area (<NUM>) which is surrounded by an opening edge (<NUM>),
wherein the moving means (<NUM>) is coupled with the mounting frame (<NUM>) on a side of the mounting frame (<NUM>) facing away from the opening area (<NUM>) by the at least one holding element,
wherein the moving means (<NUM>) is designed to move the mounting frame (<NUM>) linearly and vertically in the direction of the opening (<NUM>) in the cavity (<NUM>) at a variable distance from the base,
wherein the release device (<NUM>) is designed to hold the payload (<NUM>) in the mounting frame (<NUM>), such that the mounting frame (<NUM>) encloses or surrounds the payload (<NUM>) at least in part when the mounting frame (<NUM>) is in a neutral, retracted position or in a release, extended position,
wherein the linear moving means (<NUM>) is configured to move the mounting frame (<NUM>) between the neutral position and the release position, and
wherein the release device (<NUM>) is designed to move the payload (<NUM>) selectively from the mounting frame (<NUM>), where necessary and when the mounting frame (<NUM>) is in the release position, via the opening edge (<NUM>) and in a direction facing away from the base and to release the payload (<NUM>).