A device for attaching an optical-electronic system to an aircraft

Abstract

This utility model relates to aircraft engineering, specifically to mounting and fastening devices for optical-electronic systems. It can be used to retrofit aircraft to accommodate various target equipment without modifying the fuselage's supporting structure. The device for fastening an optical-electronic system to an aircraft comprises a flange with a first set of holes for fastening to standard locations on the aircraft and a second set of mounting holes for installing a dovetail mount. The relative positions of the first and second sets of holes ensure that the optical-electronic system is secured in a predetermined position relative to the aircraft's structural horizontal. The flange may also contain an opening for routing the optical-electronic system's cables.The technical result consists in ensuring a constant working (combat) position of the optical-electronic system without the need for manual translation in flight.

Description

[0001] Technical field

[0002] The utility model relates to the field of aircraft engineering, in particular to installation and fastening devices for placing optoelectronic systems on aircraft (helicopters), and can be used in equipping or upgrading aircraft for installing modern target equipment without changing the supporting structure of the fuselage.

[0003] A device for mounting equipment on helicopters is known, according to Russian Patent No. 2191719 C2, comprising a rotating frame installed in the external sling hatch. A disadvantage of this solution is its low vibration resistance, as well as the presence of a "blind spot" in the forward hemisphere due to the landing gear strut and the manual transition of the frame from the stowed to the combat position.

[0004] A payload attachment device is also known, according to Russian Patent No. 36096 U1, which consists of a transition platform attached to the fuselage. A disadvantage is the need for mechanical modification of the fuselage, as well as the impossibility of standardized installation of various types of optical-electronic systems.

[0005] The closest analog (prototype) is a mounting device containing a mounting flange installed in the nose of a helicopter. A disadvantage of the prototype is its focus on only one type of mounting, which does not allow for the installation of modern optoelectronic systems without modifying the standard mounting locations and leads to high installation labor intensity. Disclosure of the essence of the utility model

[0006] The objective of this utility model is to enable the installation of various types of optoelectronic systems on a standard mounting location without altering the aircraft's design. The technical result is to ensure a constant operational (combat) position of the optoelectronic system without the need for manual adjustments in flight.

[0007] The specified technical result is achieved in that the device for fastening the optical-electronic system to the aircraft contains a flange on which a first group of holes are made for fastening to the standard places of the aircraft and a second group of mounting holes for installing a dovetail type fastener, wherein the relative position of the first and second groups of holes ensures the fixation of the optical-electronic system in a given position relative to the structural horizontal of the aircraft.

[0008] In addition, a hole can be made in the flange for laying the cable part of the optical-electronic system. Brief description of the drawings

[0009] Fig. 1 shows a general view of the device for attaching an optical-electronic system to an aircraft.

[0010] In Fig. 1 the following are indicated:

[0011] 1 - flange;

[0012] 2 - hole for laying the cable part;

[0013] 3 - the first group of mounting holes;

[0014] 4 - the second group of mounting holes.

[0015] Implementation of a utility model

[0016] The device is a rigid mounting flange 1, designed for installation on an aircraft.

[0017] The first group of mounting holes 3 is made on the flange 1. The first group of holes is located in such a way as to ensure alignment with the standard mounting locations provided on the aircraft structure.

[0018] Flange 1 also features a second set of mounting holes 4, located in the central portion of the flange. This second set of holes is designed for installing a dovetail mount, which secures the optoelectronic system.

[0019] An important design feature of the device is the relative position of the first group of holes 3 and the second group of holes 4.

[0020] The specified relative position is selected in such a way that after installing the flange on the standard mounting locations of the aircraft and subsequent installation of the optical-electronic system using a dovetail mount, the required position of the optical-electronic system relative to the structural horizontal of the aircraft is ensured.

[0021] In one embodiment, the first group of holes is made in accordance with the layout of the standard mounting points in the aircraft's nose, and the second group of holes is positioned relative to the first group so that the longitudinal axis of the installed optoelectronic system occupies a predetermined position relative to the aircraft's structural horizontal. The device is mounted as follows.

[0022] Flange 1 is secured to the aircraft through the first set of holes 3. A dovetail mount is then installed through the second set of holes 4, securing the optoelectronic system. The system's cable is passed through hole 2. Due to the predetermined relative position of the first and second sets of holes, the installed optoelectronic system immediately assumes the required operating position relative to the aircraft and maintains it during operation without the need for manual adjustments in flight.

[0023] This achieves a technical result that consists of ensuring a constant working (combat) position of the optical-electronic system without the need for manual translation in flight.

Claims

1. A device for attaching an optical-electronic system to an aircraft, comprising a flange [1], characterized in that the flange is provided with: - the first group of holes [3], located with the possibility of alignment with the standard mounting holes on the fuselage of the aircraft; - the second group of mounting holes [4] located in the central part of the flange with the possibility of installing a dovetail type fastener; - in this case, the relative position of the first and second groups of holes ensures the fixation of the optical-electronic system in a given position relative to the structural horizontal of the aircraft.

2. The device according to paragraph 1, characterized in that it additionally contains an opening [2] for laying the cable part of the optical-electronic system.

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