RU2498928C1 - Aircraft antenna cowling - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to fuselage structural elements. Antenna cowling installed at aircraft comprises radiolucent front part and rear metallic part and skin reinforced by appropriate structural elements. Said cowling features streamlined torpedo-shape with stiff metal panel at top part extending over the entire length to make the bed for erection of external antennas and having hatches to be closed by covers. Plates strap is fitted atop radiolucent front part. Cowling is fitted at pylon above pilot cockpit canopy, elevated above fuselage and extended forward relative to canopy ledge. Besides, it has cutout made beneath in pylon outline and is secured at load belt with that of the pylon permanently attached to fuselage including rotary antenna attachment beam.

EFFECT: increased field of vision.

9 dwg

Description

The invention relates to aeronautical engineering, and in particular to radiolucent radome fairings of aircraft antennas.

Known radio-transparent (RP) radomes of various types of antennas mounted on aircraft. Most often these are panels integrated into the design of the RP, inscribed in the contours of the aircraft. Such a fairing is a fairing described in the invention SU 1646194 A1 "Nose compartment of the aircraft" B64C 1/36.

The closest technical solution adopted for the prototype of the proposed RP fairing is the A-50 aircraft antenna cowl mounted in front of the aircraft wing and secured along the contour to the fuselage structure (see a copy of the technical manual “Fuselage Diagram”).

All these fairings have a common drawback - the directivity of the antenna radiation, limited by the fuselage design, due to the “shadowing” of the fuselage structure.

The technical task of the invention are: improving the working conditions of the antenna, its effectiveness; an increase in the angles of radiation of the antenna, especially in the lower zone of influence when installing the antenna on the top of the fuselage; increasing the field of view, improving manufacturability in the manufacture and operation.

The technical result is achieved by the proposed design diagram of the RP of the fairing, its location above the lamp of the cockpit, where the fairing is raised above the surface of the fuselage and advanced forward relative to the ledge of the lamp so that shading of the fuselage structure is excluded.

The antenna cowl is made streamlined cigar-shaped with a rigid power panel in the upper part along the entire length, which is the basis for installing external antennas and having hatches. The antenna cowl is mounted on the pylon, which is attached to the lamp frame of the cockpit and further to the fuselage. A cowl with a cutout below the pylon contour is equipped with locks on the power belt for detachable docking with a reciprocal power belt on the pylon, the power circuit of which includes beams for fastening the rotary antenna.

This design scheme significantly improves the efficiency of the antenna, increases the field of view by increasing the limiting angles of radiation of the antenna.

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 the model of the RP fairing, similar to the fairing of the antenna mounted in front of the wing (modification);

figure 2 shows the proposed RP radome antenna mounted on an airplane above the light of the cockpit;

figure 3 shows the proposed fairing in a perspective view;

figure 4 shows a nasal fiberglass removable section of the fairing;

figure 5 shows the RP fairing side view in section in the direction of symmetry;

figure 6 shows the location of the mounts for rigging nodes;

in Fig. 7, view A shows the rigging units;

on Fig shows the location of the locks for detachable docking;

Fig.9 in a view B shows the locks for detachable docking.

The proposed RP fairing is a closed shell of an oval shape in cross section and a cigar shape in the top and side views.

The fairing design consists of two sections: a fiberglass nose section 1 and a metallic tail section 2, joined together by a detachable joint.

The fairing has cutouts: in the upper part under the metal stiffness - panel 3, and in the lower part - along the contour of the pylon.

Panel 3 consists of two parts: the front, mounted on a fiberglass section and the rear, connected to the tail of the fairing. For connection with the panel and the pylon, as well as for docking with the tail section in the fiberglass section along the contour of the cuts and along the end, a continuous fiberglass tape 4 is provided, which ensures the strength of the connection. On the upper surface of the fiberglass section, a metallizing patch 5 is installed on the adhesive, the front edge of which is directed at an angle of the maximum deviation of the antenna.

On the tail section along the contour of the cutout in the upper part, the skin is riveted to panel 3, and in the lower part of the fairing, the skin is reinforced along the contour of the pylon with docking belt 6.

The skin of the rear part of the fairing is supported by stringers 7 and frames 8. The numbers of the frames of the fairing correspond to the numbers of the frames of the fuselage (from No. 8 to No. 11). At the end of the tail part of the fairing, a coc 9 is installed, which is joined with the main part of the fairing on the diaphragm 10.

For docking the nose of the RP with the metal tail part of the fairing, a reinforced belt 11 along the contour is installed on the frame No. 8. The nose and tail of the fairing are mounted on it with bolts with anchor nuts.

Panel 3 is the basis for installing outdoor antennas. For the installation of antennas on the panel, the corresponding platforms and openings for the passage of communications from the fuselage are made.

Panel 3 has two round hatches, which are closed by covers 12 and 13, on which antennas are also mounted. The covers are attached to the panel with locks 1-4 OST 1 13723-80. Hatches simultaneously serve for approach to the rotary antenna (hatch on the frame No. 6) and for the approach to communications.

The fairing is mounted above the cockpit lantern on a pylon having a symmetrical shape of the wing profile in the longitudinal section of the horizontal plane. The pylon, in turn, is attached to the lamp frame of the cockpit and further to the fuselage frames. This shape of the fairing and the pylon and their relative position provide the best option for flowing around the air flow in flight.

The cowl pylon 14 consists of a casing 15, supported by frames 16 and uprights 17. The frames of the pylon are aligned with the frames of the metal part of the cowl (No. 8 to 11) in the upper part and the fuselage frames (No. 6 to No. 11) in the lower part. The pylon frames through the casing are riveted to the fuselage frames. To install a rotary antenna in the pylon, there are two beams 18 that are attached to the power struts 19 in the bow of the pylon and on the frames No. 6 and No. 7 of the pylon. Along the contour of the pylon edge conjugated with a fairing, a docking power belt 20 of a duralumin extruded profile is installed. On the lower contour of the pylon, paired with the surface of the fuselage, a power belt 21 of a duralumin profile is also installed, by which the pylon is connected using rivets with the fuselage (one-piece joint). For mounting - dismantling of the fairing, four lifting units 22 are provided.

A cowl located above the lamp of the cockpit provides the possibility of efficient operation of the rotary antenna, eliminating the shading of the fuselage and reducing the angles of radiation of the antenna, which increases the field of view.

The fairing is universal and can be mounted on other aircraft with a slight change in the pylon at the interface with the fuselage surface.

The fairing is also universal because it can be installed on other parts of the surface of the aircraft. The flange joint along the line connecting the fairing with the pylon when docking with power locks 23 provides easy removability of the fairing for installation - dismantling, prevention and repair.

If it is necessary to repair the fiberglass section, the design also provides for the dismantling of the separate fiberglass section (at the junction with the pylon power locks and at the junction with the tail part of the fairing along frame No. 8, bolts and anchor nuts). In operation, during technical routine and preventive maintenance, an inspection is carried out through hatches closed with covers on power locks. The panel, being the ridge of the fairing in terms of strength, is made at the same time as the basis for installing outdoor antennas.

The marked distinguishing features of the fairing ensure the effective operation of the rotary antenna, increase the field of view, and improve the manufacturability of the assembly, installation and operation of the fairing. The streamlined cowl and pylon reduce aerodynamic losses, while the rational design provides rigidity and strength with the least weight. The alleged invention is feasible according to existing technology from the materials used in aircraft construction.

The technical and economic efficiency of RP radomes is expressed in an increase in the antenna field of view, in the versatility of the radome, in the manufacturability and manufacture.

The proposed invention produced working drawings. A fairing is under construction.

Claims (1)

Aircraft fairing mounted on the aircraft, comprising a radiotransparent front and metal back, casing supported by a power pack, characterized in that it is made streamlined cigar-shaped with a rigid metal panel in the upper part along the entire length, which is the basis for installing external antennas and having hatches covered by covers, and on the upper surface of the radiotransparent front part a metallizing cover is installed, while the antenna cowl is mounted on the pylon above the lamp Ikov, elevated above the surface of the fuselage, pushed forward with respect to said projection lamp, has an opening at the bottom of the contour of the pylon and is secured locks easily removable to the belt force on a return belt power pylon stationarily mounted on the fuselage and including a power circuit for fastening the beam rotating antenna.

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