Camera pods for military aircraft

Abstract

Camera container (1) for military aircraft, wherein the camera container (1) is designed as a detachable external container, characterized in that the camera container (1) comprises a casing (2) of an inserted guided missile, wherein the camera container (1) includes: - Electronics for the detection of the camera container (1) by the aircraft; - at least one self-contained camera system (5, 9, 10); - Enclosure elements made of optically transparent material (17); - Balancing masses (11) for simulating the mass and center of gravity of a guided missile; and - a pressure equalization valve (12); wherein the camera container (1) is inert; and wherein at least one self-contained camera system (5, 9, 10) is configured to record the departure behavior of guided missiles attached adjacent to the aircraft.

Description

[0001] The invention relates to a camera container for military aircraft for investigating the departure behavior of guided missiles and ballistic munitions dropped from aircraft.

[0002] Investigations into the departure behavior of guided missiles and ballistic munitions from aircraft regularly require the use of photographic recordings for later evaluation and determination of "non-impairment of traffic safety", for providing evidence, but also in the area of ​​operational use of munitions.

[0003] German patent application DE 10 2004 003 773 A1 discloses an aircraft hull element comprising a shell body that forms an inner cavity and includes a viewing window. To achieve largely distortion-free, high-resolution images in the infrared wavelength range and from a wide angular range, it is proposed that the shell body be rotatably mounted about a rotational axis.

[0004] For use in high-speed airflows, it is advantageous to focus on the outer shape of the shell body in order to generate low air resistance.

[0005] US patent application US 2014 / 0139730A1 describes a housing for use in high-velocity airflows. One embodiment describes a housing for imaging devices. The housing has a tapered shape with symmetrical angular truncations, resulting in a wedge-shaped taper with two substantially planar sections. At least one section contains an opening made of optically transparent material.

[0006] For measuring devices, it is also essential that they only need to be carried when required and do not have to remain permanently on the aircraft.

[0007] Utility model DE 79 05 728 U1 discloses a detachable outboard container for aircraft, mounted on outboard struts, for holding equipment such as cameras or measuring instruments. The container consists of a central section attachable to the outboard struts and detachably arranged bow and stern sections, which, when assembled, have the shape of officially approved standard jettisonable outboard containers, characterized in that the parts of the outboard container are equipped internally with retaining devices designed to receive insertable pallets, and that the equipment required for different uses, such as cameras or measuring instruments, is each mounted on pallets that can be inserted into the parts of the outboard container.

[0008] The disadvantage of these known solutions is that they require separate approval for aeronautical certification, must be integrated into the aircraft's system, and are therefore not universally suitable for a wide variety of different military aircraft.

[0009] DE 10 2011 104 023 A1 describes an optical device for guiding radiation from an object scene onto a detector, comprising an alignment means for pivoting the detector's field of view relative to a predetermined direction, a detector optic, and an optical joint for guiding the beam path from the pivoted field of view into the detector optic. To achieve a compact design for the device, it is proposed that the optical joint incorporate a reversing prism in which the radiation is refracted and reflected along the optical axis of the joint.

[0010] DE 10 2015 005 707 A1 describes an infrared seeker head for a guided missile, consisting of an outer spherical shell segment containing an optical dome, and an inner hollow sphere in which the full interior space is available for camera(s), driven by a simple commercially available XY slide via a nipple slidably attached to the surface of the hollow sphere, swiveling up to + / -90° in half-space during use, and swiveling beyond 90° for camera image homogenization.

[0011] DE 10 2015 009 577 A1 describes a seeker head for a guided missile, comprising a 3D camera system for capturing a three-dimensional depth profile.

[0012] DE 10 2015 013 349 A1 describes a weapon system comprising a first magazine comprising a plurality of seekers for a guided missile, a second magazine comprising a plurality of drive and guidance modules for a guided missile, a third magazine comprising a plurality of electronics for a guided missile, a storage device for a plurality of support structures for a guided missile, wherein a support structure can be removed from the storage device to which a seeker ejectable from the first magazine, a drive and guidance module ejectable from the second magazine, and electronics ejectable from the third magazine can be attached in order to obtain a guided missile.

[0013] DE 10 2019 002 665 A1 describes a radar antenna. To reduce the optical aperture when a forward-facing radar antenna is present, the document proposes that the radar antenna be designed as an optically transparent metallic coating formed in an antenna shape and applied to an optically transparent body.

[0014] The object of the invention is therefore to propose a camera container for military aircraft for investigating the departure behavior of guided missiles and ballistic drop munitions from aircraft, which does not require aeronautical approval, does not interfere with the aircraft's system and is universally applicable to a variety of military aircraft.

[0015] This problem is solved by the characterizing features of independent claims 1 and 4. Advantageous embodiments are described in the dependent claims.

[0016] The advantage of the camera container according to the invention is that a housing for an inserted guided missile can be carried on all stations of a flying weapon system approved by the certification. Even for future weapon systems equipped with corresponding guided missiles, the use of the camera container according to the invention is already possible. Naturally, the camera container can also be used on weapon systems of the same design but from other nations.

[0017] Existing guided missiles are converted into a shell according to the invention by removing all explosives, detonators, and electronics. Only the electronics for the aircraft's recognition of the guided missile remain in the missile. Guided missiles already intended solely for supervised flight, which are used only for integration and training, can be used directly as shells.

[0018] The use of a self-contained camera system has the advantage that there is no connection to the aircraft or the pilot. The camera system has its own power supply and a storage medium sufficient for the duration of the mission. The camera is simply switched on before the start of the flight and switched off after the flight, at which point the storage medium is removed. During operation, the self-contained camera system continuously records, in particular the trajectory behavior of nearby guided missiles or ballistic munitions launched or dropped from the aircraft.

[0019] The housing element of the camera container incorporates sections made of optically transparent material. This transparent material is integrated into the housing element where the optics of the self-contained camera systems protrude from the housing to record the surroundings. The use of an optically transparent material to complete the housing element protects the camera system from damage, such as bird strikes, ensures the original flight characteristics of the housing due to consistent surface aerodynamics, and allows the self-contained camera systems to be installed at virtually any point on the housing.

[0020] Investigating the launch behavior of guided missiles requires positioning the self-contained camera systems at various locations within the hull. To maintain a constant mass and center of gravity of the camera pod despite these different camera positions, counterweights are used to ensure a balanced mass distribution with minimal deviation in the center of gravity.

[0021] Unlike passenger aircraft, where cabin pressure is kept constant as altitude increases and outside air pressure decreases, the camera container has a pressure equalization valve to adjust the internal pressure of the camera container to the outside air pressure.

[0022] An advantageous embodiment of the camera housing according to the invention is described in dependent claim 2. The lenses of camera systems capture different sections of their surroundings. The distortion of the captured images increases with the wider the angle of view. To obtain the largest possible angle of view with minimal distortion, it is advantageous to mount the independent camera systems along the longitudinal axis of the camera housing at at least two different angles to the vertical. This means, for example, that a first independent camera system is mounted horizontally at an angle of 90° to the vertical to capture the surroundings to the right or left, and a second independent camera system is mounted along the longitudinal axis, for example, at an angle of 135° to the vertical. The second independent camera system captures the surroundings either to the right or left, but always diagonally downwards.This arrangement of at least two autonomous camera systems achieves a wider recording angle with low distortion from the optics.

[0023] The sensor dome of guided missiles is located at the front and is made of optically transparent material. It is particularly advantageous to mount an independent camera system in the sensor dome area, with its recording area parallel to the steering axis and oriented in the direction of flight. This arrangement makes it possible to track the trajectory of a launched guided missile in close proximity to the aircraft.

[0024] For better understanding, the following method for the camera container according to the invention is described: From an existing and certified guided missile, the explosives, detonators, and electronics are removed, except for the components required for missile detection by the aircraft. The optimal positions for self-contained camera systems for investigating the missile's launch behavior from aircraft are determined within the camera housing, and the recording direction is defined. Openings are cut into the former missile's housing and then sealed with optically transparent material. Self-contained camera systems are mounted inside. To restore the missile's original mass and center of gravity, the assembled camera housing is balanced using internal counterweights. The start and end times, as well as the recording type, are programmed on the camera before launch.In order to be able to use a camera container according to the invention in highly different and rapidly changing altitude bands, the container is equipped with a pressure equalization valve.

[0025] It shows Fig. 1. A side view of a camera container according to the invention. The following are shown: Fig. 2 and Fig. 3 each make a cut through the camera container according to the invention at the in Fig. 1 designated places.

[0026] It shows Fig. 1. A camera container 1. The casing 2 is a former guided missile from which the explosives, detonators, and electronic components have been removed, or which was already inert due to its use for training and exercise purposes. At the front end 3 of the camera container 1 is the sensor dome 4 of the former guided missile. A first self-contained camera system 5 is mounted in the sensor dome 4, parallel to the longitudinal axis of the camera container 1. The optics of the first self-contained camera system 5 are aligned in the direction of flight 6. A second and a third self-contained camera system 9, 10 are mounted in the middle and rear sections 7, 8 of the camera container 1. Balancing masses 11 are mounted between the self-contained camera systems 5, 9, 10. The ballasting masses 11 simulate the original mass of the former guided missile and its center of gravity.A pressure equalization valve 12 is located in the rear section 8 of the former guided missile in the area of ​​the former engine.

[0027] It shows Fig. 2 a cut AA of the Fig. 1. The interior of the hull 2 ​​has frames 13 to which a camera table 14 is mounted via a perforated metal plate 15. The camera table 14 carries the first self-contained camera system 5. Perforated plates 15 are used to freely adjust the angle of the camera tables 14 to the vertical. These plates are first mounted to the frames 13. The camera tables 14 are then screwed to the perforated plates 15 at any desired angle.

[0028] It shows Fig. 3 a cut BB the Fig.1. The interior of the shell 2 has further frames 13 along the longitudinal axis of the camera container 1. Camera tables 14 are mounted between the frames 13. A second and third independent camera system 9, 10 are mounted on the camera tables. The second camera system 9 is mounted at an angle of 90° to the vertical. The third camera system 10 is mounted at an angle of 135° to the vertical. The shell 1 has an optically transparent material 17 in the optical field 16. Reference symbol list 1 camera container 2 cases 3 Front end 4 Sensor Dome 5 first self-sufficient camera system 6 Flight direction 7 middle range 8 rear area 9 second self-contained camera system 10. Third self-contained camera system 11 leveling compound 12 Pressure equalization valve 13 frames 14 camera table 15 perforated discs 16 Recording area 17 optically transparent material

Claims

[1] Camera container (1) for military aircraft, wherein the camera container (1) is designed as a detachable external container, characterized by , that the camera container (1) comprises a casing (2) of an inserted guided missile, wherein the camera container (1) includes: - Electronics for the detection of the camera container (1) by the aircraft; - at least one self-contained camera system (5, 9, 10); - Enclosure elements made of optically transparent material (17); - Balancing masses (11) for simulating the mass and center of gravity of a guided missile; and - a pressure equalization valve (12); wherein the camera container (1) is inert; and wherein at least one self-contained camera system (5, 9, 10) is configured to record the departure behavior of guided missiles attached adjacent to the aircraft. [2] Camera container (1) according to claim 1, characterized by, that at least two self-contained camera systems (5, 9, 10) are mounted along the longitudinal axis of the camera container (1) at at least two different angles to the vertical. [3] Camera container (1) according to one of claims 1 and 2, characterized by , that an autonomous camera system (5, 9, 10) is mounted in a sensor dome (4) parallel to the longitudinal axis with the lens direction in the direction of flight (6). [4] Method for manufacturing a camera container (1) for military aircraft according to any one of the preceding claims, the method comprising: - Providing a guided missile having a casing (2); - Removal of all explosives, detonators and associated electronics, except for electronics used for aircraft detection of the guided missile, from the guided missile; - Determining positions of at least one self-contained camera system (5, 9, 10) within the casing (2) of the guided missile, so that the at least one camera system (5, 9, 10) can record the launch behavior of guided missiles attached to the aircraft adjacent to it; - Cutting openings at the specified positions for the at least one self-contained camera system (5, 9, 10) into the shell (2) of the guided missile; - Closing the openings with transparent material (17); - Mounting the at least one self-contained camera system (5, 9, 10) into the casing (2) at the specified positions; and - Introducing internal counterweights (11) into the shell (2) to restore the original mass and center of gravity of the guided missile.

Images