RU2724198C1 - Method of preparing missiles for launching - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to equipment of aircraft with missiles. Proposed method consists in placing missiles in fuselage (2) armament compartment (1) closed by moving flaps (3). Each rocket (4) is individually suspended on the aircraft launching device (ALD) (5) one above the other, into at least one unit section (6), forming a vertical row. When control command arrives to feed rocket from section to preset position: open (7) movable flap of section (6), extend (8) lower rocket (9) section in-the-air position corresponding to firing position for each of missiles in section. After separation of rocket from ALD during start-up, closing (10) of flap is made or possibility of movement of next lower missile (9) of section is possible in prestart position.EFFECT: optimal use of internal space of in-fuselage compartment of weapons for fuselage of any shape, elimination of action of reactive power moment on aircraft airframe relative to longitudinal axis during transfer of missiles to prestart position, and also reduction of time cycle of this transfer.3 cl, 7 dwg

Description

The invention relates to aircraft manufacturing and can be used in the design of the fuselage equipment of aircraft (LA) with missiles of various types.

Guided (SD) and unguided missiles are a consumable part of aviation weapons of destruction (ASP) and, in the general case, are suspended on the structural elements of aircraft launching devices (APU). At the location on the aircraft, it is customary to allocate APU external and internal suspension. [Military aircraft: Aviation weapons. Under. ed. DI. Gladkova. - M .: Military Publishing House, 1987, p. 150].

Known methods: placement of guided missiles of UR on airplanes of 3 ÷ 4 generations under the fuselage and wing on an external sling , for example: under the wing of the Tu-22M3 UR X-22, [magazine "Arsenal of the Fatherland" No. 4 [18] for 2015]; under the fuselage and wing of the UR "Air-Air" long, medium and short range on all fighters of the Air Force and Air Defense of the USSR and the Russian Federation [Chechik DL, “Armament of aircraft”, M., MAI .; 2002]. The disadvantages of these methods is that, in connection with the additional loads from the APU on the wingspan, it is necessary to strengthen its structure and, accordingly, increase weight. External hangers significantly limit flight performance [LTX], including speed, maneuverability, operational overload, etc., and increase the EPR.

There is a known option of placing missiles under the fuselage of a carrier aircraft in a half-flooded position, for example, aviation UR X-22 [V. Markovsky, K. Petrov. “Aircraft cruise missiles”, “Aviation and astronautics. Yesterday, today, tomorrow ”, No. 9, 2005, p. 27, 28, R-33, .37, .39], RVV DB [R-33, R-37]. The disadvantages of this option are: a limited number of TSAs, incl. for placement in special single-tier niches.

Currently, to improve the aerodynamic characteristics of the airframe and flight dynamics, as well as to reduce the radar visibility of the aircraft, the tendency is to place missiles inside the fuselage, in the area of the weapons compartment. [P. Ivanov. B-1B bomber: some results of the first years of operation, the journal Foreign Military Review, No. 5, 1988. p. 37-38].

The Lockheed Martin F-35 Lightning II USA aircraft are equipped with two internal weapon compartments with two suspension points in each, which allows you to place up to four short / medium / long range air-to-air missiles on board without losing stealth, while arranged horizontally, in one row thereby limiting their number [Army Bulletin magazine, February 10, 2015].

The method of placing missiles in the structure under consideration negatively affects the number and type (especially in terms of weight and dimensions) of the deployed TSA; the plane “turns out” flatter, thinner, with a large “washed” area, which negatively affects some performance characteristics; to increase the number of TSA it is necessary to use most of the lower area of the aircraft to the detriment of other elements of the fuselage and the mechanization of the wing.

There is a method of tandem placement of single missiles in a supersonic aircraft in the fuselage armament compartments, consisting of two halves symmetrical about the plane of symmetry of the aircraft (patent document US 5522566 A; IPC B64C 1/00, B64D 7/08, published 04.06.1996) . Using the method implies an undesirable increase in the size of the mid-sectional section of the aircraft, or significant restrictions on the overall dimensions of missiles placed in cargo compartments

There is a method of preparing missiles for launch in an aircraft missile launcher installation of a storage and launch system for missiles on an aircraft, in which the missiles are placed in cone-shaped clusters, which, in turn, are embedded in each other with high density. The axis of the missiles are located along the angles of inclination of the generatrix of the cone. Missiles are fed into the pre-launch position by commands, due to the independent rotation of the cluster around the axis of the cone, (patent document US 4409880 A, IPC B64D 7/08, F41F 3/06, publ. 10/18/1983). The disadvantage of this method is: that when the missiles rotate, reactive moments of forces arise relative to the longitudinal axis of the aircraft, causing the roll of the aircraft; at the same time, the method assumes the same type of rockets in the cluster, which will not allow to quickly translate a rocket of a certain type into the starting position, as well as the complexity of the design of the feeding mechanisms.

The prototype of the invention is a method of preparing missiles for launch in a rotary-rotational ("revolving") aircraft missile launcher. Each missile is individually suspended on an aircraft launcher installed in the armament compartment located inside the fuselage, closed by movable leaves, and automatically transported to the off-body prestart position by control commands, while the missiles are suspended radially on a rotating drum, and, when a control command is received: turn the drum , ensuring the position of the launched rocket over the sash; open the movable leaf and move the rocket to the off-body position corresponding to the starting position (patent document US 4637292 A, IPC B64D 7/08, publ. 01.20.1987). The disadvantage of this method is that for optimal use of the space of the weapons compartment at the location of the turret, a round intra-fuselage section must be provided, when the missiles rotate, reactive moments of forces arise relative to the longitudinal axis of the aircraft, causing the roll of the aircraft, and also the time cycle of the rocket transfer to the starting position is limited by the rotation time of the “drum”.

Also, it is not possible to launch several missiles simultaneously and, in addition, if aircraft are equipped with various types of missiles, it takes a long time to transfer a certain type of rocket to the prestart position, due to the need to rotate the drum to select the required missile.

The task set during the development of the invention was to create a method for preparing missiles for launch, which makes it possible to optimally use the internal space of the armament fuselage compartment of the internal fuselage of any shape, excluding the action of a reactive force moment on the airframe relative to the longitudinal axis when translating missiles into the starting position, and also shortening the time cycle of this translation.

The problem is solved by the method of preparing missiles for launch, in which each missile is individually suspended on an aircraft launch device in the armament compartment located inside the fuselage, closed by movable leaves, and automatically transported to the fuselage pre-launch position according to control commands,

the missiles are suspended in at least one unit section, one above the other, at the same time, when a control command is received to feed the section rocket to the pre-launch position: open the movable leaf, push the lower section rocket into the fuselage position corresponding to the starting position for each of the rockets sections, and after separating the rocket from the APU during the launch process, provide the ability to close the sash, or the ability to move to the starting position of the next lower rocket in the section.

The technical result achieved by the implementation of the invention is the optimal use of the internal space of the internal fuselage compartment of a weapon, when placing missiles, for fuselages of any shape, eliminating the action of a reactive force moment on the airframe relative to the longitudinal axis when translating missiles into the starting position, and also shortening the time cycle of this translation .

In particular cases of execution, to enable the simultaneous preparation of several missiles for launch and to provide the possibility of simultaneous launch, the missiles can be suspended in several single sections forming a single block, while the axis of the missiles in the block is placed parallel to each other. At the same time, to ensure a variety of missile types and reduce their selection time when used in various tactical situations, only one type of missile can be placed in each unit section of a single unit.

To clarify the invention, the following graphic materials are used.

FIG. 1 - Placement of missiles in the weapons compartment located inside the fuselage of the aircraft;

FIG. 2 - Section AA Fig. 1, for the case of suspension of missiles in several single sections, forming a single unit;

FIG. 3 - Placement of missiles in a single section in the General case of the invention;

FIG. 4 Diagram of actions in the process of supplying the lower rocket section 3 to the starting position;

FIG. 5 - Placement of a single section rocket in the prestart position;

FIG. 6 Scheme of possible actions after separation of the rocket from the APU during the launch process;

FIG. 7 Option mechanization scheme for implementing the invention

The placement of missiles on an aircraft is shown in FIG. 1, 2. Missiles are placed in the weapons compartment 1 of the fuselage 2, closed by movable wings 3.

Each rocket 4 is individually suspended on an aircraft launcher (APU) 5 on top of each other in at least one unit section 6, forming a vertical row (Fig. 3).

Upon receipt of a control command to supply the rocket from the section to the pre-launch position: open the 7 movable leaf of the section 6, push the lower 8 rocket of the 9 section to the off-body position corresponding to the starting position for each of the rockets in the section (Fig. 4, 5).

After separating the rocket from the APU FIG. 6 during the launch process, provide the ability to close 10 shutters, or the ability to move to the pre-launch position of the subsequent lower rocket 9 section.

To ensure the possibility of simultaneous preparation of several missiles for launch and the possibility of simultaneous launch, missiles can be suspended in several single sections 6, 10, 11, 12, forming a single block (Fig. 2), the axis of the missiles in the block are placed parallel to each other. To ensure the choice of missile type during their use in various tactical situations, each unit section 6, 10, 11, 12 of a single unit can accommodate missiles of only one type 4 or 13 or 14 or 15, respectively, of the dimensions and equipment of the section.

Implementation of the invention is possible by means and methods known from the prior art, including technical mechanics [Erded A.A., Erdedi N.A., Technical mechanics, M., "Academy", 2014. 528 p.], As well as from drive theory [Kovchin S.A., Sabinin Yu.A. Fundamentals of electric drive. S-P .: Energoatomizdat, 1994. 496], etc.

The invention can be implemented through the construction of a power bridge system 16, which carries the entire calculated load and moves vertically along the guides 17 placed on the walls of the section under the influence of, for example, screw mechanisms, and carries an aircraft launcher 5 with a rocket 9 (Fig. 7 )

Screw mechanisms using electric motors move the power bridge system (CMC) at the command of an arms control system (SUV);

APU 5 is suspended under CMC 16 and is equipped with mechanisms with the functions of: intermediate power fastening of the rocket on guides (locks); transfers from aircraft to the missile, via quick disconnect connections, power supply, high pressure gases; target designation commands and signals of performing teams, including commands for transporting the rocket to the starting position. At the command "start" occur: the opening of locks locks, and the disconnection of communications.

Closing the shutter, or the ability to move to the pre-launch position of the next lower missile in the section, will be ensured by the folding structure of the combined missile suspension (SMS + APU) using a mechanism with an electric translational action mechanism and fixing it in a predetermined position on the side wall of the compartment;

Sashes can close each single section in flight individually or can use single sashes for the entire weapon edema, in accordance with the conceptual design features of the aircraft.

When the command "move the rocket to the starting position" is issued, the following sequence of actions is implemented: the shutters open, the transmission (screw) mechanisms move the CMC of the lower rocket of the section under the action of electric motors, vertically down to the prestart position, in the extreme lower position the CMC stops, while the APU supplies the rocket energy, gases, commands, signals through a quick coupler.

Upon receipt of the “start” command, the locks of the APU open, the communications are disconnected and the launch takes place (the rocket “starts”); CMC with APU is disconnected from the power system and SUV, moves to a structurally fixed position and is folded into a niche of the section wall (not shown in Fig. 7). There is a release of space for moving to the starting position of the subsequent lower rocket 9 of the section of FIG. 6 or to close the shutter 7 when deciding to stop the cycle of combat use.

Since the missiles will be located in a vertical section one above the other, it is obvious that optimization of their placement will be achieved, allowing you to select the vertical dimensions of the sections to fill in the internal space of the fuselage of any section shape.

The implementation of the supply of missiles to the starting position by means of their linear movement instead of rotating the inertial drum excludes the action of reactive force moment on the aircraft glider relative to the longitudinal axis when translating the missiles into the starting position, and also reduces the time cycle of this transfer.

In the case of suspension of missiles in several single sections, forming a single block, simultaneous independent transfer to the starting position of the rocket of each section is possible, which reduces the time to prepare for the use of TSA, and also provides the possibility of simultaneous launch.

If only one type of missiles is placed in each unit section, the time required to select the required missiles of a certain type is reduced, since this only requires a team to prepare for launching the missile in a specific section.

Claims (3)

1. A method of preparing missiles for launch, in which each missile is individually suspended on an aircraft launcher (APU), in the weapons compartment located inside the fuselage, closed by movable leaves, and automatically transported to the fuselage starting position according to control commands, characterized in that the missiles suspended in at least one unit section, one above the other, while upon receipt of a control command to supply the section rocket to the pre-launch position: open the movable leaf, push the lower section rocket to the off-body position corresponding to the starting position for each of the section rockets, and after separation of the rocket from the APU during the launch process provides the ability to close the sash or the ability to move to the starting position of the next lower rocket in the section. 2. The method of preparing the missiles for launch according to claim 1, in which the missiles are suspended in several single sections forming a single unit, while the axis of the missiles in the block is placed parallel to each other. 3. The method of preparing missiles for launch according to claim 2, in which only one type of missile is placed in each unit section of a single unit.

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