RU2790352C2 - Installation for launching aircraft missiles - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: installation for launching aircraft missiles contains a case with a power set, launching tubes for aircraft missiles, a gate for retention of aircraft missiles, suspension assemblies to an aircraft, an electric system for transmission of launch pulses from a carrier, an information exchange unit, a missile control unit, connected in a certain way.

EFFECT: increase in the efficiency of using a launching installation.

1 cl, 2 dwg

Description

The invention relates to the field of aviation armament, namely to multi-barreled launchers (PU) for placing in them and launching aircraft missiles from aircraft.

From the prior art, PU is known according to the patent of the Russian Federation RU 2 539 434, IPC F41F 3/065, publ. 01/20/2015, including a set of autonomous modules with housings with a power pack, with launch tubes of 5 or 10 pcs. in each, with shutters to hold missiles, with electrical systems for supplying starting pulses.

The main disadvantages of the known PU are:

- the inability to use programmable, corrected and guided missiles due to the lack of an information exchange system with the carrier;

- the inability to change the unloading scheme depending on the combat mission during its execution from the aircraft;

- autonomy of modular blocks, which leads to an increase in the weight of a separate module made from a body with a power set, and the cost, due to the need to manufacture an autonomous electrical system for each module, which negatively affects the flight characteristics of the aircraft;

Signs of a well-known launcher, coinciding with the essential features of the present invention, can be considered the possibility of modular build-up, the presence of a body with a power set, the presence of launch tubes, the presence of a shutter to hold missiles, the presence of suspension units for the aircraft and the presence of an electrical system for transmitting starting impulses, however:

1. The possibility of modular expansion is executed differently - suspended modules for a real launcher are not autonomous (independent), unlike autonomous modules of a well-known launcher, they are equipped with a simplified driven power housing and a driven part of the electrical system, dependent on the information exchange and projectile control units of the lead launcher; such a modular build-up design makes it possible to reduce the cost and weight of the modules, while not reducing the operational and tactical and technical characteristics of the entire modular design by combining the slave modules into a single power structure and a single electrical system with a master launcher, which is the present invention;

2. The body with the power set, launch tubes, shutter and suspension units for the aircraft are common features and do not have significant differences;

3. The electrical system for transmitting starting pulses, unlike the electrical system of the known launcher, includes a starting pulse distribution unit, which allows launching according to the unloading scheme programmed with the help of the aircraft equipment, in addition, the electrical system of the launcher of the present invention includes blocks of information exchange and projectile control, allowing you to work with guided missiles;

The task underlying the present invention is to create a launcher capable of operating with guided types of missiles, including programming NAR parameters, such as opening time; read and transmit information, such as the type of missile, from the missile to the aircraft equipment; change the unloading scheme, depending on changes in the combat mission and the availability of types of loaded missiles.

The technical result of using the proposed design is to increase the efficiency of using the launcher due to the possibility of quickly changing the combat mission in the course of its implementation and using, among other things, guided and programmable types of missiles, which increases the combat power of the complex as a whole. In addition, the ability to program missiles allows the use of projectiles for civilian applications, for example, it is possible to cover a large area of fires with fire extinguishing mixtures by programming the opening time of the projectiles.

The problem underlying the present invention is solved by the fact that the launcher includes an information exchange unit, which is electrically connected to the carrier equipment and carries out information exchange with it and controls the remaining units; the projectile control unit, electrically docked and controlled by the information exchange unit, is also connected to the contactless information exchange system with missiles installed on the launch tubes of the launcher, carries out information exchange with the missiles; the launch pulse distribution unit, connected to the electrical system for supplying launch pulses and controlled by the information exchange unit, also the distributor is connected to the missile launch circuits through the launch tube couplings, supplies launch pulses to the missile launch circuits under the control of the information exchange unit.

The introduction of an information exchange unit into the design of the launcher makes it possible to combine the electronic blocks of the launcher into a system and control them using the onboard equipment of the carrier.

The introduction of a missile control unit into the design of the launcher, together with a system for contactless information exchange with missiles, makes it possible to program the missile equipment to perform flight tasks and read the information embedded in the missile equipment.

The introduction of the launch pulse distributor into the design of the launcher allows you to change the unloading scheme using the onboard equipment of the carrier.

In FIG. 1 shows the Launcher for aircraft missiles, which consists of unified suspension units for aircraft pos. 1; body with a power set pos. 2, to which the remaining structural elements are attached; launch tubes for aircraft missiles pos. 3; transmitting devices for connecting to the control equipment of the rocket pos. 4, pos. 4a; the first information input-output of the information exchange unit connected to the carrier equipment pos. 5; lock for fixing the loaded products pos. 6. The weight of the launcher is 82 kg, loaded NAR S-8KOM - 242 kg.

In FIG. 2 shows a diagram of the electronic blocks of this launcher, which includes the information exchange unit pos. 7; connected to the carrier by the first information input-output of the information exchange block pos. 5; projectile control unit, combined with the starting pulse distribution unit pos. 8, connected to the transmitting devices for connecting to the control equipment of the rocket, located on the launch tubes pos. 4 and to the couplings for transmitting starting impulses to the missile launch circuit pos. 10, the entire electrical system is mated with harnesses pos. 9.

From the prior art, no solutions have been identified that would have features that coincide with the distinguishing features of the claimed PU, so the latter meets the condition of patentability "inventive step".

Preliminary tests of the pilot batch of the proposed invention were carried out, confirming that the above technical solutions provide the necessary characteristics and functionality.

Claims (1)

Installation for launching aircraft missiles, consisting of a body with a power set, launch tubes for aircraft missiles, a shutter for holding aircraft missiles, suspension units for an aircraft, an electrical system for transmitting launch pulses from a carrier, characterized in that the launcher includes an information block exchange and missile control unit, the first information input-output of the information exchange unit is connected to the carrier equipment, the second information input-output of the information exchange unit is connected to the first information input-output of the missile control unit, the second information input-output of the missile control unit is connected to the transmitting devices connection to the missile control equipment located on the launch tubes; in addition, between the electrical system for supplying starting impulses and the missile launch circuits, a starting impulse distribution unit is connected, the power input of which is connected to the electric system for transmitting starting impulses, the power output is connected to the missile launch circuits, the control input is connected to the third information output of the information exchange unit.

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