RU2502633C1 - Aircraft antenna rotary cowling support - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly to aircraft antenna rotary cowling. Proposed support comprises rotary mechanism and is composed of six beams arranged inside the cowling and integrated in a solid structure by interconnection of beam ends and their connection to pylon frames to make, by their top flanges, the plane of connection with cowling rotary drive while, by their bottom flanges, the surface inscribed in cowling contour. Beam bottom flanges are connected by angular knees that make servicing opening framing. Note here that stiffness ribs of inner and outer lateral beams are connected in pairs by straps while flanges of said beams extending beyond the cowling contour are connected to pylon structural panels. Cover board composed of four removable panels is fitted between beams and round opening with clearance from opening edges.

EFFECT: decreased sizes.

11 dwg

Description

The alleged invention relates to aeronautical engineering, namely to airborne early warning radar detection aircraft (AWACS).

In a number of countries, aircraft with rotating and non-rotating antenna fairings are being built and operated, and their options are different.

For information, inventions were used: US 2980909 “Fixed fairing on a pylon with an antenna rotating inside it” H01Q 1/28, US 3656164 “Retractable aircraft antenna with a radio-transparent fairing for scanning” H01Q 1/28,

US 3045236 "Rotating fairings for aircraft" NKI 343-705,

US 3026516 "Rotating fairing on an airplane pylon"

NKI 343-705, the journal "Results of science and technology." Aircraft Industry, Volume 1, “Modern Aircraft of the USA and Western European Countries,” Moscow 1973, p. 80, 3.1.2. Aircraft - Boeing AWACS US Air Defense Command and Volume 2 Part I, Moscow 1976, p. 99.

All of these antenna fairings, depending on the purpose, location, mobility (rotation) or immobility relative to the structure of the aircraft, have different support options.

So, for example, a cowl US 3656164 H01Q 1/28, retractable in the fuselage, relies on a support in the niche of the fuselage using the landing gear retraction mechanism. The fairing of US 3045236 NKI 343-705 is fixed motionless on the fuselage pylon behind the wings, and the vertical axis, which passes through the entire fuselage and is mounted in bearings on the fuselage structure, supports the rotating antenna in it. The rotating cowling US 3026516 NKI 343-705 is mounted with its two bearings on the annular plates on the pylon and in the skin.

All these fairings differ in purpose and design, and have their drawbacks in terminating bearings on plates (fuselage panels), on trusses (links) of the cleaning mechanism, etc., which are not reliable.

Close in purpose and design is the “Rotating Fairing for Aircraft” US No. 3045236 NKI 343-705, where the antenna is located inside the fairing motionless relative to the fairing. The fairing rotates with the antenna, mounted on a shaft that rotates in bearings mounted in the lower part of the fuselage on the floor, in the upper part of the fuselage (in the panel of the upper skin) and in the pylon.

The shaft, rigidly fixed in the fairing, is driven by the engine and transmission elements that ensure the rotation of the fairing together with the antenna fixed in it. This invention can be taken as an analogue, but in it the fairing rests on one pylon.

Since the proposed support of the fairing is attached to the fuselage on two pylons, it is most similar to the design described in the journal "Itogi Nauki i Tekhniki". Aircraft, Volume 1 Modern aircraft of the USA and Western Europe, Moscow, 1973, p. 80.

On a Boeing 707-320B aircraft, a rotating antenna cowl is mounted above the fuselage behind the wing on two pylons. The diameter of the fairing is 9.14 m, the thickness is 1.8 m with a rotation speed of 6 rpm.

This aircraft with a rotating antenna cowl resting on two pylons is taken as a prototype.

The specified fairing, as previously listed, has drawbacks in the design of the support of the fairing in terms of the transfer of significant forces (250-300 tons in our case) from the fairing through the rotation mechanism to the pylons.

The technical task of the invention is to increase the resource support and connections in the system "fairing-support-pylons", weight reduction with compactness and minimal dimensions of the design, manufacturability, assembly, ease of inspection and maintenance.

The technical result is achieved by the proposed integrated circuit design of the support of a rotating radome fairing mounted on two pylons on the fuselage of the aircraft.

The support of the rotating fairing, containing the rotation mechanism, is made of six beams located in the volume of the fairing and combined into a solid structure by connecting the ends of the beams to each other and simultaneously with the pylon spars, forming their upper shelves as a plane for connection with the fairing rotation mechanism, and the lower shelves as a surface inscribed in the contours of the fairing.

The lower shelves of the beams are connected by angular knits, forming the inner edges of the edging of the operating hatch. The stiffeners of the lateral outer and inner beams are connected in pairs between themselves by power plates. The flanges of these beams extended beyond the contour of the fairing are connected to structural elements of the pylon panels. Between the beams and the round hole in the fairing with a gap from its edges, a sewing is installed, consisting of four segment removable panels.

The proposed integrated design scheme combines all the elements into a single whole - a support with a uniform distribution of loads on the structural elements and on the connections with the rotation mechanism of the fairing with pylons.

A comparative analysis of the alleged invention with the identified analogues shows that it has novelty, inventive step and industrial applicability.

The essence of the invention is illustrated by a brief description and the accompanying drawings, where:

figure 1 shows a model of an aircraft with a cowl antenna fairing;

figure 2 shows a view of the flight on the supporting frame;

figure 3 shows a top view of the supporting frame;

figure 4 shows a top view of the support with a slit longitudinal horizontal plane (section aa);

figure 5 shows a model of a General view of the fairing on a support with a transverse section along the axis of symmetry of the fairing;

figure 6 shows a model of the support with a cross section and a view of the side members of the pylons;

Fig.7 shows a model of the support on the pylons with a transverse section along the axis of symmetry of the fairing;

on Fig shows a view of the shelves of the side beams;

figure 9 shows a model with a view of the support from above;

figure 10 shows a model with a view of the support mounted on pylons with sewing in a circle and the pylons of the pylons;

11 shows a model with a view of the support and the rotation mechanism.

The proposed design of the cowling support on an airplane is a power base, supported by two pylons and consisting of six main elements - beams: the front beam 1, the outer side beams 2 and 3, the inner beams 4 and 5 and the rear beam 6. The beams are interconnected by ends forming the corners of the frame, where they are connected to four pylon spars. Front spars: left 7 and right 8, rear 9 and 10.

The number of beams is determined by the appropriateness of the load distribution. So, the front beam 1, resting at the ends on the side members 7 and 8, is located between the pylons 11 and 12. The wall of the front beam 1 mates with the walls of the side members 7 and 8, is bolted to them, in addition, the stiffeners of the front beam 1 are connected to the shelves of these side members. Also, the rear beam 6 is connected to the rear side members 9 and 10. The side beams 2 and 3 with their ends enter the cavity between the shelves of the side members 7, 8, 9 and 10, their walls are connected to the shelves of the side members, and their shelves are connected: the lower ones to the rib on the side member wall, and the upper shelves with the upper shelf of the front beam 1. The walls of the side beams 2 and 3 in the direction are a continuation of the panels 13, 14, 15 and 16 of the pylons. The outer side beams 2 and 3 are joined with the outer panels of the pylons 13 and 16, and the inner side beams 4 and 5, respectively, with the inner panels of the pylons 14 and 15.

The walls and shelves of the side beams 2 and 3 are supported by stiffeners 17, which are located on the side beams 2 and 3 along the axes of the stringers of the pylon panels 13, 14, 15 and 16, thereby closing the vertical forces between the side members 7, 8, 9 and 10 to the elements pylon panel designs. Figure 6 clearly shows the pairing of the walls of the side members 7, 8, 9, 10 with the walls of the front beam 1. The inner shelves of the side members 7, 8 mate with the walls of the inner beams 4, 5 and with the ribs of the front 1 and rear 6 beams.

The upper shelves of the outer 2, 3 and inner 4, 5 side beams are milled and mated from the bottom to the inside with the shelves of the front 1 and rear 6 beams.

In the upper shelves of the front 1, rear 6 and inner side beams 4, 5, the upper surface of which is made as a plane of interface with the bearing of the cowling rotation mechanism (Fig. 11), there are holes 18 for bolts with the bearing of the cowling rotation mechanism.

The inner ribs of the side beams of the outer 2, 3 and inner 4, 5 are interconnected (in pairs) by power plates 19, capable of transferring part of the load falling on the inner beams 4, 5 from the bearing to the outer beams 2, 3. Then, through the connecting elements ( the beam shelves are connected to the panels, Fig. 8) to transfer this load to the outer panels 13 and 16 of the pylons.

The expansion of the upper shelves of the inner side beams 4 and 5, as well as the front beam 1 and the rear beam 6 in the corners, create rigidity that can prevent distortions of the entire frame.

On the lower surface of the support in the corners between the lower shelves of the beams 1, 4, 5, 6, power knives 20 are installed, which are fixed on the lower shelves of the beams and form a fringing of the access hatch, which is closed by a cover 21, which is locked by locks 22 (for example, OST 1 13723-80 )

Openings for the fairing ventilation air intake are made in the manhole cover.

The cowling support, having the minimum dimensions determined by the dimensions of the cowling rotation mechanism and strength, is designed as a rational integrated design, compact and able to withstand high alternating loads with minimal weight and at the same time provide the specified high resource of the aircraft.

The support is universal for installing similar fairings on it and even for transporting cargo, aircraft, rockets and other space technology fixed on it.

The design of the proposed support provides the convenience of inspection and maintenance of the rotation mechanism, its drive, waveguides and other communications, as well as the inspection and control of fasteners, bolted joints and the integrity of the structural elements. For this, detachable connections are provided for quick-detachable flashing panels 23 mounted on the locks 22. Flashing panels 23 are made along the lower circumference of the fairing and are installed with a gap between the fixed support and the edge (in a circle) of the rotating fairing.

The marked distinguishing features of the support ensure the effective operation of the rotating antenna cowl on an airplane, weight reduction with compactness and minimal design dimensions, and manufacturability, assembly and maintenance.

The connection of the support with the pylons, closed streamlined gaps 24 and 25, provides minimal aerodynamic loss.

The technical and economic efficiency of the proposed design of the support of the rotating antenna cowl is expressed in the rationality of the integrated circuit design, the dimensions of the elements and their distribution depending on the load provide guaranteed strength and high resource, reducing weight, simplicity and high adaptability of manufacturing of parts and assemblies included in it, in ease of use, compactness and ease of installation and dismantling of communications and the fairing itself.

Claims (1)

The support of a rotating antenna cowl mounted on two pylons on the aircraft fuselage, comprising a rotation mechanism, characterized in that it is made of six beams located in the cowl volume and combined into a one-piece structure by connecting the ends of the beams with each other and simultaneously with the pylon spars, forming with its upper shelves, a plane for connecting to the fairing rotation mechanism, and the lower shelves - a surface inscribed in the fairing contours, where the lower shelves of the beams are connected by angular knits, about the edges of the hatch beveling along the inner edges, while the stiffeners of the lateral beams, external and internal, are connected in pairs by power overlays, and the shelves of these beams extended beyond the fairing contour are connected to the structural elements of the pylon panels, in addition, between the beams and the round opening in the fairing with a gap from its edges, sewing is installed, consisting of four segment removable panels.

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