RU2492413C1 - Drop head fairing of aircraft (versions) - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: drop head fairing is made in the form of a solid of revolution of streamlined shape, sharpened in the front and having an open end at the back. The fairing comprises folds, an aerodynamic tip and a split plate. The aerodynamic tip connects folds, and is also equipped with a system of separation comprising a pyrocartridge. The plate is made of parts, the number of which matches the number of fairing folds. Each part of the plate is connected with one of the folds. Folds are equipped with facilities of tightness provision and are connected with the aircraft by means of hinged mechanisms. Hinged mechanisms are arranged in the rear part of each fold and are made as capable of folds separation from the aircraft. In the other version of realisation the fairing is made of plastic or composite materials. On the inner surface of the fairing there are transverse and longitudinal grooves. Grooves are arranged so that the fairing is divided by them into three parts. The transverse groove is arranged at the crossing of the inner surface of the fairing and the plane arranged at the angle of less than 90° to the longitudinal axis of the aircraft. Longitudinal grooves are arranged from the transverse groove to the fairing end. There are detonation extension charges placed in the transverse and longitudinal grooves.

EFFECT: increased distance of flight.

2 cl, 6 dwg

Description

The invention relates to the field of aviation and rocket technology, namely the head fairings of aircraft, for example, guided missiles.

From the prior art known resettable head fairing guided missile (application for US patent No. 2006169841 from 03.08.2006, IPC F41G 7/00), containing at least two separable parts that are connected by a tip equipped with a squib.

The disadvantages of dropping the head fairing of a guided missile are insufficient increase in flight range, insufficient rigidity, lack of tightness and the risk of damage to aerodynamic surfaces at the time of dumping the fairing, leading to a decrease in reliability and safety.

Also known from the prior art is a detachable fairing of an aircraft (patent of the European Patent Office No. 2354756 dated 08/10/2011, IPC F42B 15/36), which is closest to the proposed invention and selected as a prototype. A detachable fairing consists of at least four parts, two of which make up a shared tip equipped with a squib.

The disadvantages of a detachable fairing of an aircraft are an insufficient increase in flight range, insufficient structural rigidity, lack of tightness and the risk of damage to aerodynamic surfaces, leading to a decrease in the reliability of the structure and safety.

The objective of the invention is to increase flight range, increasing the reliability and safety of flight.

The problem is solved due to the fact that the discharged head fairing of the aircraft mounted on the bow is made in the form of a streamlined body of rotation, pointed in front and having an open end at the back, and contains at least two wings, an aerodynamic tip connecting the wings and equipped with a separation system, which includes a squib, a split plate, in shape close to the nose and in contact with it, made of parts, the number of which coincides with the number of wings a flower, wherein each part of the plate is connected to one of the wings; the flaps are provided with means of ensuring tightness and are connected to the aircraft using hinge mechanisms located at the rear of each wing and made with the possibility of separating the wings from the aircraft.

In an embodiment of the invention, the problem is solved due to the fact that the resettable head fairing of the aircraft, made in the form of a body of revolution of a streamlined shape made of plastic or composite materials, pointed at the front and having an open end face at the back, mounted on the nose, while the transverse is made on the inner surface of the fairing and longitudinal grooves with embedded detonation elongated charges, arranged so that the fairing is divided by them at least into three parts, a transverse groove located at the intersection of the inner surface of the radome and a plane positioned at an angle less than 90 ° to the longitudinal axis of the vehicle, the longitudinal grooves are arranged on the transverse groove to the end of the fairing.

The resettable head fairing of the aircraft allows you to increase the flight range of the aircraft by reducing drag, increase reliability by increasing the stiffness and tightness of the fairing, and increase the safety of dropping the fairing.

The essence of the invention is illustrated by drawings:

Figure 1 shows the first version of the resettable head fairing of the aircraft, a side view in section.

Figure 2 shows the tip for the first version of the resettable head fairing of the aircraft, a side view in section.

Figure 3 shows the hinge mechanism for the first variant of the resettable head fairing of the aircraft, a side view in section.

Figure 4 shows the hinge mechanism for the first variant of the resettable head fairing of the aircraft, a rear view in section.

Figure 5 shows the second variant of the resettable head fairing of the aircraft, a side view in section.

Figure 6 shows a second variant of the resettable head fairing of the aircraft with a sliding nose, side view.

Figure 1-6 shows the following positions:

1 - sash;

2 - tip;

3 - hinge mechanism;

4 - plate;

5 - pin;

6 - safety pin;

7 - a squib;

8 - the head part;

9 - weakening groove;

10 - axis;

11 - a bracket;

12 - mount;

13 - transverse groove;

14 is a longitudinal groove.

In the first version of the aircraft head fairing (hereinafter referred to as the fairing), the fairing consists of at least two, and in the considered, within the framework of this description, particular case of four leaves 1, aerodynamic tip 2, articulated mechanisms 3 (one per case) , split plates 4, seals (not shown in FIG.). The flaps 1 form a fairing, which is a body of rotation of a streamlined, for example, animated shape, made with a certain elongation. The streamlined shape and elongation of the fairing have a direct effect on reducing drag, with the greater the elongation, the lower the resistance and the higher the flight range as a result of using the invention. It was experimentally established that lengthening a cowl over three calibers of an aircraft is inefficient.

Four flaps 1 are held together by a metal tip 2 by four pins 5. From longitudinal movement, the tip is fixed with a safety pin 6. The back of the tip 2 is the piston of the squib 7. Seals are located between the flaps 1, which ensure that the fairing is sealed in working condition. Sealers are made, for example, in the form of profiled elongated metal elements, in the form of repeating the contacting edges of the fairing flaps 1, provided in the contact points with the flaps 1 with additional rubber sealing elements. The cutting plate 4, consisting of the number of parts equal to the number of leaves 1, in this case four, is riveted to the protrusions made on the inside of the fairing wings 1 at a distance from the end and from the tip. The plate 4 is made of a convex shape, close to the head part 8 of the aircraft and enveloping it so that between them there was a sufficient number of reference points of contact to ensure stability.

Each leaf 1 has a rear wingtip in the end part of the fairing, smoothly interfaced with the aircraft body. To open the fairing on the inner surface of the sash 1 in the area of the ending, a weakening groove 9 is provided.

The hinge mechanism 3 is intended for fastening the fairing to the body and turning the wings 1 to the initial angle during separation. Each leaf 1 has its own hinge mechanism 3, attached to it by screws with recessed heads. It consists of a main axis 10, a bracket 11 and a fastening 12. The axis 10 is fixed in the aircraft body and can rotate around its axis. The fastener 12 is mounted on the fairing flap 1 with screws and inserted into a rectangular groove on the axis 10 of the hinge mechanism 3. To prevent the fastening from coming out of the groove, two brackets 11 are provided that are attached to the aircraft body.

In the second embodiment, the fairing is made of one-piece plastic or composite materials and has a general shape similar to the fairing described in the first embodiment. In this case, detonation elongated charges (DPS) are used as a means of separating the fairing. DUZ are laid in grooves 13 and 14 made on the inner surface of the fairing, namely the transverse groove 13 and at least two longitudinal grooves 14, from the transverse groove 13 to the end of the fairing. The transverse groove 13 is located at the intersection of the inner surface of the fairing and the plane intersecting the longitudinal axis of the aircraft at an angle less than 90 °. In the embodiment of the invention considered within the scope of this description, four longitudinal grooves are made 14. The fairing is fixed to the aircraft body using, for example, a crack joint.

In the second embodiment, the cowl material, plastic or composite materials, performs the same function as the hinge mechanisms 3 in the first cowl variant, and due to the low weight of the cowl, it is possible to ensure the safety of the cowling and to eliminate the possibility of damage to the aerodynamic surfaces of the aircraft. Also, the implementation of the fairing from these materials allows you to reduce the power of the remote sensing system and to eliminate damage when they undermine parts of the aircraft located in the head part, for example, GOS.

The second version of the fairing is more advantageous to use in cases where the GOS operates on most of the flight path of the aircraft, since such a fairing can be made transparent.

Resettable head fairing of the aircraft operates as follows.

In the first version of the fairing, after the signal for resetting the fairing, the igniter is triggered. Under the pressure of the gases formed, the safety pin 6 is cut off, and the tip 2 shoots forward in the direction of flight. In the housing of the squib 7 there are four openings in the radial direction (not shown in FIG.). Through these holes, an additional initial impulse is transmitted to the flaps 1 by the flow of formed gases, after which they fly apart under the influence of an incoming air flow. The hinge mechanisms 3 prevent premature separation of the fairing flaps 1, which may result in damage to the aircraft body. They provide separation when reaching a certain angle. The angle is regulated by the brackets 11 and is determined by the flight speed, the location of the aerodynamic surfaces and the aerodynamic characteristics of the fairing flaps 1 based on the safety requirements of the compartment. In each case, the angle is set experimentally. When the axis 10 is rotated by a certain angle, the fastener 12 disengages from the bracket 11 and the cowl flaps 1 are separated. For additional safety, the separation (in the case of close proximity of the aerodynamic surfaces to the head of the rocket), the plane of the cut fairing coincide with the planes of the aerodynamic surfaces.

In the second version of the fairing, after applying the signal to reset the fairing, the remote sensing devices located in the grooves 13 and 14 of the fairing are detonated. The charge located in the transverse groove 13 is fired first. Due to the inclination of the plane of the charge, the cut nose slides down, opening the central hole. After that, the DLD are activated in the longitudinal grooves 14, and the fairing is separated by a flow of incoming air.

The resettable head fairing of the aircraft is intended for use in the field of aviation and rocket technology for aircraft with a blunt nose, in particular aircraft equipped with devices such as homing heads and allows increasing the flight range of the aircraft.

Claims (2)

1. A resettable head fairing of the aircraft, made in the form of a streamlined body of rotation, pointed at the front and having an open end at the back, mounted on the nose of the aircraft, consisting of at least two wings, an aerodynamic tip connecting the wings and equipped with a separation system containing pyrocartridge, characterized in that the fairing contains a split plate, similar in shape to the nose of the aircraft and in contact with it, made of parts, the number of which coincides with the number of fairing flaps, with each part of the plate connected to one of the flaps, the flaps are provided with means of ensuring tightness and are connected to the aircraft using hinge mechanisms located at the rear of each flap and configured to separate the flaps from the aircraft. 2. A resettable head fairing of the aircraft, made in the form of a streamlined body of rotation, pointed at the front and having an open end at the back, mounted on the nose of the aircraft, characterized in that the fairing is made of plastic or composite materials, the transverse and longitudinal grooves arranged so that the fairing is divided by them into at least three parts, the transverse groove is located at the intersection of the inner surface STI and fairing plane disposed at an angle less than 90 ° to the longitudinal axis of the vehicle, the longitudinal grooves are arranged on the transverse groove to the end of the fairing; while in the transverse and longitudinal grooves are detonation elongated charges.

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