RU2272981C1 - Aircraft launcher - Google Patents

Abstract

FIELD: aircraft launchers.

SUBSTANCE: the device has a body in the form of a load-bearing girder with points of attachment to the carrier aeroplane fastened outside it, and electrical units closed by light-duty U-shaped covers forming a no-load carrying superstructure are positioned over its entire length. The front fairing is made in the form a strengthened, developed part adjoining the load-carrying girder, hinge-joined on which are doors opening relative to the longitudinal axis of the aircraft launcher, the doors are provided with a closed-position lock. The mechanism of unmating from the rocket is made in the form of a double-arm lever hinge-joined to the strengthened part of the front fairing, its one arm has a gripper with a spring-loaded latch, the other arm is spring-loaded for longitudinal motion. Made in the lower part of the doors of the front fairing is an opening for free motion of the arm with the gripper in it, and a slot for the wrench used at mating-unmating of the break-away coupling is made in the hinge-joint. The clip of the pneumatic system bottle has enveloping, narrowing up and developed parts, the latter of which is positioned outside the load-carrying girder that is provided with a cover closed by the rear bracket of the clip fastening. The device is provided with front and rear anti-vibrators. An additional point of attachment to the carrier aeroplane is installed outside the load-carrying girder. Made on the inner side of the doors of the front fairing are spring-loaded rotary components engageable with the mating stops made on the gripper of the unmating mechanism.

EFFECT: improved operating characteristics.

8 cl, 9 dwg

Description

The invention relates to aircraft, to the field of devices intended for suspension, transportation and combat use on missile aircraft, in particular, to aircraft launchers (APU).

Aircraft rail-mounted launcher APU-13MT for suspension and rocket launch is known (see "Devices for equipping modern aircraft". Album catalog. Publisher - State Machine-Building Design Bureau "Vympel", p. 67, 68, 70, 72 and 73). This device is selected as a prototype for this application.

The APU contains a power housing with front and rear nodes of the suspension to the aircraft, which provides power communication between the APU and the suspended rocket, front and opening rear fairings that cover the housing on both sides, and a guide for suspension and launch of the rocket. Inside the case in one row are placed: a locking block, fixing and holding the rocket, a rocket undocking mechanism, which ensures separation of the tear-off connector at start-up and removal of the undocked part of the connector inside the APU, as well as electrical units and a pneumatic system.

The disadvantages of the known APU include the limitation of the possibilities of its use on various types of modern, high-speed carrier aircraft. This is due to the fact that the main components and electrical units are located inside the power beam in one row. At the same time, an increase in the equipment of modern carrier aircraft has led to the need for the placement of separate power units that communicate through the APU carrier aircraft with a rocket inside the APU. In the well-known APU, these requirements entail a significant increase in the length of the APU and a decrease in strength characteristics, which is unacceptable for the safe interaction of the entire complex: the aircraft-APU-rocket.

The present invention is aimed at solving the technical problem of creating an APU that ensures the satisfaction of the requirements for modern aircraft-APU-rocket complexes, namely, the creation of such an APU in which the necessary mechanisms and electrical units are located within the allowable dimensions of the power building, and at the same time, reliable suspension, transportation and rocket launch.

The problem is solved in that in an APU containing a power housing with front and rear suspension nodes to the carrier aircraft, front and rear fairings and a guide for the descent of the rocket, the missile holding the rocket on the guide block, as well as a pneumatic system located in the body, including a cylinder with nitrogen, which is held in the rear part by a clamp covering it, as well as electrical units combined with a pneumatic system by a single electric pneumatic connector, connected by means of a bundle placed inside the front fairing with a tear-off connector ohms of the docking - undocking with the rocket, and the undocking mechanism, while the APU is equipped with front and rear anti-vibrators, the last of which is located in the rear of the guide, the difference is that the case is made in the form of a power beam of a rectangular profile, on the outside of which suspension nodes are fixed to the carrier aircraft and placed along its entire length electrical units closed by lightweight removable U-shaped covers forming a non-force superstructure, which is a continuation of a single power profile, and the front fairing ying a reinforced developed and the adjacent portion of the power beam on which are hinged drop relative to the longitudinal axis of AAP flap provided with a lock closed position, wherein decoupling mechanism rocket fixed on a reinforced part of the fairing.

This design of the APU made it possible to place the main mechanisms and the pneumatic system inside the power beam, and a larger number of electrical units in the non-power superstructure, which allows the use of a shortened power beam with safety requirements and strength characteristics, and at the same time provide free access to the APU mechanisms.

In addition, in the present invention, the lock block is made in the form of a housing in which the front holding and additional levers are pivotally connected, the second ends of which are pivotally mounted on the housing and the spring-loaded rod, respectively, and the spring-loaded rear holding lever, while in the joint of the front holding and additional a roller is mounted on the levers, and a bevel is made on the rear lever to interact with the front and rear inclined surfaces of the rocket yoke, respectively.

Due to this, when the rocket converges from the interaction of the roller and the front inclined surface of the yoke, rolling friction is created, which is preferable, since the wear of the material and the heating of the contacting elements of the APU and the rocket are reduced.

In addition, in the APU, the undocking mechanism with the missile is made in the form of a two-arm lever pivotally mounted on the reinforced part of the front fairing of the front fairing, one shoulder of which has a grip with a spring-loaded latch, the second is spring-loaded with the possibility of longitudinal movement, while a window for free moving the shoulder in it with a grip, and in the hinge a turn-key slot is made when docking-undocking the tear-off connector.

Also, in the automatic control system, the electric pneumatic connector is made in the form of a rectangular cut-in connector and is equipped with a preload mechanism located externally in the front of the power beam, while the latter is equipped with a front bracket on which there is its own preload mechanism housing with a lever pivotally mounted on it, interacting with one when the fairing is closed a shoulder with a leaf spring fixed on its leaf, and the other shoulder with spring-loaded sliders pivotally connected to it, interacting with the protrusions and elektropnevmorazeme.

Such implementation of these mechanisms is dictated by their placement and provides ease of maintenance in operation.

At the same time, the clamp of the cylinder of the pneumatic system has covering, tapering upward and developed parts, the last of which is located outside the power beam, which is equipped with a lockable rear bracket for fastening the clamp.

This made it possible to exclude the direct effect of vibrations arising on the guide during the launch of missiles and thereby reduce the loads transmitted to the nitrogen tank.

In addition, in the APU, the rear anti-vibrator is made in the form of a horseshoe-shaped plate fixed on the upper plane of the guide parallel to its longitudinal axis.

This provides ease of suspension of the rocket, does not create unnecessary friction during launches and provides anti-vibration effect.

In addition, an additional rear suspension unit for the carrier aircraft is installed outside the power beam in the APU.

This allowed us to expand the use of APU on various types of carrier aircraft with different suspension bases.

Even on the inner side of the front cowl flaps, spring-loaded stops are made, interacting with mating stops made to capture the undocking mechanism when mismatched with the rocket.

This provides guaranteed docking missiles with APU.

In general, the proposed APU allows to improve its operational characteristics while ensuring reliable launch of missiles from modern high-speed carrier aircraft.

The essence of the invention is illustrated by drawings, where

figure 1 shows a General view of an aircraft launcher;

figure 2 shows a cross section "aa" (figure 1) for fastening with a hose clamp of a container with nitrogen;

figure 3 shows a General view of the block castle;

figure 4 shows the lock block (figure 3) in the "suspension" position;

figure 5 shows the block lock (figure 3) in the closed position;

in Fig.6 shows the lock block (Fig.3) in the "open" position;

figure 7 shows the front fairing with the uncoupling mechanism, located in the lower position in cooperation with the tear-off connector;

on Fig shows the mechanism of preload electro-pneumatic connector;

figure 9 shows a view of B (figure 1) - rear antivibrator.

Aircraft launcher (Fig. 1) consists of a housing 1 with suspension units to the carrier aircraft: front 2, rear 3 and additional rear 4; guide 5 for the descent of the rocket, as well as the front 6 and rear 7 fairings.

The housing 1 is made in the form of a power beam of a rectangular profile. Over the entire length of the housing 1, electrical units are placed on top, closed by removable U-shaped covers 8, 9, 10, forming a non-force superstructure, which is a continuation of a single power profile. Inside the housing 1 there are: a locking block 11 and a pneumatic system including a cylinder with nitrogen 12.

Electrical units include: a power supply system 13, which is an autonomous device, a start-up power supply 14, a switching plug 15, an electric harness 16, and an electric pneumatic connector 17.

The front fairing 6 is made in the form of a reinforced and developed part, on which two flaps 19 are opened hinged on the hinges 18 and are fixed relative to the longitudinal axis of the APU. The locking of the closed flaps 19 is provided by a captive locking screw 20. On the inner sides of the flaps 19 there are spring-loaded swing elements-stops 21 . On one of the wings 19 has a leaf spring 22.

Inside the front fairing 6 is the uncoupling mechanism 23 (Fig. 7) of the tear-off connector 24, which consists of a grip 25 with a spring-loaded latch 26 and stops 27, a spring-loaded lever 28, pivotally mounted on the reinforced part of the front fairing 5. A slot 29 is made under the hinge key.

In the lower part of the flaps 19 of the front fairing 6, a window is made for free movement of the gripper 25 of the undocking mechanism 23 of the tear-off connector 24 (see Fig. 7).

The locking block 11 (Fig. 3) consists of its own housing 30, on which the front holding 31 and additional 32 levers are arranged pivotally for holding the front yoke 33 of the rocket 34. The additional lever 32 is connected to the spring-loaded rod 35 for moving it. In the articulation of the levers 31 and 32 there is a roller 36 for interacting with the front inclined surface of the front yoke 33 of the rocket 34, while on the rear holding lever 37 in its lower part there is a bevel for interacting with the rear inclined surface of the front yoke 33. There is an opening in the housing 30 under the check 38. The system of levers 39, 40 by means of a rod 41, which is mounted on the axis 42, connected with the rear holding lever 37.

In the rear part of the housing 30 on its own bracket 43 is fixed a pneumatic solenoid valve 44, designed to screw a cylinder with nitrogen 12 and supply nitrogen to the pneumatic system.

In the upper part of the housing 30 is an electromagnet 45 on which a latch 46 is fastened to lock or open the spring-loaded stem 35.

The electro-pneumatic connector 17 is made of a rectangular cut-in type connector. Docking of the electric pneumatic connector 17 of the rocket 34 with the counterpart of the electric pneumatic connector of the APU occurs using the preload mechanism 47 (Fig. 8), which is mounted on the front bracket 48 of the housing 1 and consists of its own housing 49 with catchers 50, into which the protrusions 51 of the electric pneumatic connector 17 are inserted, and the lever 52 pivotally connected to the sliders 53.

In the rear part of the APU, outside the housing 1 on the rear bracket 54 there is a clamp 55, tightened by a screw 56. With this clamp 55, a nitrogen tank 12 is attached (figure 2). The back of the APU is closed by a cover 57.

The rear fairing 6 is also made in the form of two flaps 58 opening relative to the longitudinal axis of the APU, pivotally with hinges 59 fixed to the housing 1. When the flaps 58 are opened, an approach to the nitrogen cylinder 12 is provided. Locking of the closed flaps 58 is ensured by a similar front screw lock 20.

The aircraft launcher is equipped with two anti-vibrators: front (not shown) and rear, made in the form of a horseshoe-shaped plate 60 (Fig.9), which is attached to the upper plane of the guide 5 by screws 61. This plate 60 is located along the longitudinal axis of the guide 5.

Aircraft launcher operates as follows.

When suspending it on a carrier aircraft, front 2 and rear 3 (or additional rear 4, depending on the basic dimensions of the carrier aircraft), the suspension units are inserted into the counterparts of the aircraft units and secured by bolted connections of the aircraft (not shown). There is also an electrical docking of the APU and the aircraft with electrical units 13, 14, 15, 16 and 17, located in a non-force, closed by covers 8, 9, 10, superstructure of building 1. The self-contained device is powered by one type of standard supply voltage and supplies the rocket with nitrogen and five types different power supply at all stages of the rocket in conjunction with the carrier aircraft.

With the rear fairing 7 open, the nitrogen cylinder 12 is screwed at one end into a pneumatic solenoid valve 44 mounted on its own bracket 43 in the locking block 11, and the other is fixed with a female clamp 55, which is connected by a screw 56. The rear bracket 54, the clamp 55 and the nitrogen cylinder 12 from above close the lid 57. This fastening of the cylinder with nitrogen 12 does not transfer the load on it arising on the guide 5 when starting the rocket 34. After installing the cylinder 12, close the shutter 58 of the rear fairing 7 with a retaining screw 20.

Before the suspension of the rocket 34 on the APU, the rear holding lever 37 of the locking block 11 is mechanically unlocked using the check 38. When the check 38 is inserted, the levers 39 and 40 move upward, unlocking the rear holding lever 37.

The rocket 34 is smoothly advanced forward along the guide 5 to the stop of the front yoke 33 of the rocket 34 in the rear holding lever 37 (figure 4). The lever 37 with a rod 41 mounted on the axis 42, moves up and the front yoke 33, moving forward, abuts against the roller 36 until a characteristic click. The lever 37 is lowered to its original position, fixing the rocket 34 from moving backward (figure 5). The rocket 34 is mounted on the guide 5 using three yokes (Figures 4-6 show only the front yoke 33, and the middle and rear are not shown).

When de-energized, electromagnet 45, the front holding 31, additional 32 levers and roller 36, pivotally connected to each other, are in the lower position, and the second ends of the levers 31, 32, pivotally connected to the spring rod 35 and the own housing 30 of the block 11 of the lock, provide together with rear holding lever 37 closed position of the front yoke 33 of the rocket 34.

With the front fairing 6 open, the key is installed in the slot 29, the gripper 25 together with the spring-loaded lever 28 is rotated to the lower position, while the spring-loaded swing elements-stops 21 are released from interaction with the counter stops made on the gripper 25 of the undocking mechanism 23 of the detachable connector 24 of the rocket 34 The pins of the tear-off connector 24 snap into the grip 25 with a spring-loaded latch 26.

In the preload mechanism 47, the lever 52 is manually moved to the upper position, releasing one end of it from being fixed by a leaf spring 22. The other end of the lever 52, connected with two spring-loaded sliders 53 and catchers 50, holds the electro-pneumatic connector 17 by its protrusions 51. The electro-pneumatic connector 17 of the rocket is manually advanced 34 before entering the response part of the electric air connector APU. The lever 52 is pressed down to the docking of the electro-pneumatic system with the electrical units (13, 14, 15, 16 and 17) of the APU. The leaf spring 22 of the fairing 6 pushes the lever 52 downward, fixing it. Close the sash 19 of the front fairing 6 manually using the hinges 18 and wrap captive retainer-screw 20. Remove the pin 38 from the block lock 11.

Before launching the rocket 34, the command in the form of an electric signal is supplied to the electromagnet 45 of the lock 11. The latch 46 releases the spring-loaded rod 35 and under the action of the front yoke 33 when it moves, the front inclined surface of the front yoke 33 presses the roller 36, as a result of which the front holding 31 and an additional 32 levers, overcoming the force of the spring-loaded stem 35, are added. The roller 36 rises, providing free passage of the yokes of the rocket 34 (Fig.6). In this case, the horseshoe-shaped plate 60 of the rear anti-vibrator is installed with a minimum guaranteed clearance and thereby reduces the amplitude of vibration of the rocket and does not create excessive friction during launches, that is, it provides an anti-vibration effect. After tearing off the tear-off connector 24, the gripper 25, together with the undocked part thereof, leans upward through the window of the front fairing 6 until it stops.

After the descent of the rocket 34, the spring-loaded rod 35 returns the front holding 31 and the additional 32 levers to their original position. When the electromagnet 45 is turned off, the latch 46 lowers and re-locks the spring-loaded stem 35.

The proposed design of the APU, in comparison with the prototype, allows you to use a shortened power beam with safety requirements and strength characteristics. At the same time, free access to the mechanisms and ease of maintenance of the APU in operation are ensured. In addition, this design expands the application of APU on various types of carrier aircraft with different suspension bases.

Claims (8)

1. Aircraft launcher, comprising a power housing with front and rear suspension components for the carrier aircraft, front and rear fairings and a guide for the descent of the rocket, holding the rocket on the guide block lock, placed in the body of the pneumatic system, including a nitrogen tank, held in the rear parts of the clamp covering it, as well as electrical units, combined with the pneumatic system as a single electric pneumatic connector, connected by means of a bundle placed inside the front fairing with a tear-off connector the docking with the rocket, and the undocking mechanism, front and rear anti-vibrators, the last of which is located in the rear of the guide, characterized in that the power housing is made in the form of a power beam of rectangular profile, on the outside of which the suspension units to the carrier aircraft are fixed and placed throughout the length of electrical units closed by lightweight removable U-shaped covers that form a non-force superstructure, which is a continuation of the unified profile of the power beam, and the front fairing is made in the form of reinforced, developed and the part adjacent to the power beam, on which the flaps are provided that are hinged and open that are relative to the longitudinal axis of the power beam and are equipped with a closed position lock, while the rocket undocking mechanism is fixed to the reinforced part of this cowl. 2. The aviation launcher according to claim 1, characterized in that the lock block is made in the form of its own housing, in which the front holding and additional levers are pivotally connected, the second ends of which are pivotally mounted on the housing and the spring-loaded stem, respectively, and the spring-loaded rear holding lever while a roller is installed in the joint hinge of the front holding and additional levers, and a bevel is made on the rear lever to interact with the front and rear inclined surfaces of the yoke missiles, respectively. 3. Aircraft launcher according to claim 1 or 2, characterized in that the mechanism for undocking with the rocket is made in the form of a two-arm lever pivotally mounted on the reinforced part of the front fairing, one shoulder of which has a grip with a spring-loaded latch, the second is spring-loaded with the possibility of longitudinal movement, with at the bottom of the front fairing cusps, a window is made for free movement of a shoulder with a grip in it, and a turnkey slot is made in the hinge when docking / undocking the tear-off connector. 4. The aviation launcher according to claim 1, characterized in that the electro-pneumatic connector is of the type of a rectangular cut-in connector and is equipped with a preload mechanism located externally in front of the power beam, the latter being equipped with a front bracket on which its own preload mechanism housing is mounted pivotally mounted on it with a lever interacting with the closed position of the fairing with one shoulder with a leaf spring located on the wing of the fairing, and with the other shoulder with pivotally connected to it spring-loaded sliders interacting with the protrusions made on the electric pneumatic connector. 5. Aircraft launching device according to claim 1 or 4, characterized in that the clamp of the pneumatic system cylinder mounting has covering, tapering upward and developed parts, the last of which is located outside the power beam, which is equipped with a rear bracket for fixing the clamp to be closed by a cover. 6. Aircraft launcher according to claim 1, characterized in that the rear anti-vibrator is made in the form of a horseshoe-shaped plate mounted on the upper plane of the guide parallel to its longitudinal axis. 7. Aircraft launching device according to claim 1 or 6, characterized in that an additional rear suspension unit to the carrier aircraft is installed outside the power beam. 8. Aircraft launcher according to claim 1, characterized in that on the inner side of the front fairing flaps are spring-loaded rotary elements interacting when mismatched with the rocket with mating stops made to capture the undocking mechanism.

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