RU2786885C1 - An aircraft with a safe missile launching device - Google Patents

Abstract

FIELD: aviation technology.

SUBSTANCE: invention relates to aviation technology, namely to aircraft that use missiles with an active launch in the process of performing a combat mission. An aircraft with a missile launcher contains an aircraft body with a cargo compartment in which at least one missile launcher is installed. A missile engine flare gas jet deflection device is installed on the launcher, which is a bucket-shaped structure and consists of a metal frame and three inserts of carbon-carbon composite material impregnated with silicon, which are installed obliquely with respect to the axis of the launcher to form a channel for deflecting the rocket engine flare gas jet away from the cargo compartment of the aircraft. The inserts are fixed to the metal frame of the device for deflecting the gas jet of the rocket engine torch using bolts made of carbon-carbon composite material impregnated with silicon, stainless steel bolts and epoxy glue. Duralumin cladding is additionally installed in the cargo compartment, which reduce the volume of the cargo compartment and provide aerodynamic profiling, which reduces the level of vibro-acoustic loads on the structure of the aircraft itself.

EFFECT: invention enables to provide maximum protection against thermodynamic, vibroacoustic and erosive effects of the flare of the rocket engine of the structural elements of the aircraft.

5 cl, 4 dwg

Description

SUBSTANCE: invention relates to aircraft engineering, namely to aircrafts using rockets with active launch in the process of performing a combat mission.

Active launch rockets are currently used from rail launchers. The engine of such rockets is launched directly on the suspension and enters the operating mode even before leaving the rails, while the size of the zone covered by the rocket engine torch reaches 2/3 of the length of the carrier (aircraft) and moves during the movement of the rocket. Thus, it has a significant thermodynamic and erosive effect on most of the structural elements of the carrier. At the same time, it should be taken into account that the indicated impact is short-term during normal operation of the launcher and the rocket leaves the guides, and long-term in case of an emergency (launcher failure, resulting in the rocket not derailing).

When starting a rocket engine, the most aggressive effect on the aircraft units is exerted by the central part of the jet of gases of the engine flame, located along the axis of the engine (torch core).

There are technical solutions aimed at protecting structural elements or the environment from a rocket engine torch, for example:

- US Pat. No. 4,480,522 A, Nov. 06, 1984 describes a method for protecting the rail guides of a rocket launcher from the thermal effects of a rocket engine by blowing cooling air through holes in the launcher;

- JPH patent 04260797 A, 09/16/1992 describes the design of a deflector that changes the flow of gases from the engine of a launching rocket and thereby reduces the force on the launcher.

However, the known technical solutions do not provide sufficient protection of the structural elements of the aircraft from the thermodynamic, vibroacoustic and erosive effects of the rocket engine plume.

Closest to the claimed invention is an aircraft known from US patent 4545284 A, 10/08/1985. In the closest analogue, the rail guides of the launcher are protected from the thermal impact of the rocket engine by means of protective flaps that close at the start of the engine operation under the influence of a gas jet emitted from the engine nozzle.

The disadvantage of the closest analogue is that the implementation is aimed at protecting only the guide rails of the launcher, and does not take into account the negative impact of the torch of the launching rocket on the rest of the aircraft structure, and is also insufficient for protection in case of an emergency (disengagement).

Thus, the objective of the claimed invention is to eliminate the shortcomings of the prior art.

The technical result, to which the claimed invention is directed, is to provide maximum protection from the thermodynamic, vibroacoustic and erosive effects of the rocket engine plume of the structural elements of the aircraft.

The claimed technical result is fully achieved by a combination of features of an independent claim.

An aircraft with a safe missile launch device comprises an aircraft body with a cargo compartment, in which at least one missile launcher is installed. The launcher is equipped with a device for deflecting the gas jet of the rocket engine torch, which is a bucket-shaped structure and consists of a metal frame and three inserts made of carbon-carbon composite material impregnated with silicon, which are installed obliquely with respect to the axis of the launcher to form a channel for deflecting the gas jet rocket engine torch away from the cargo compartment of the aircraft. The inserts are attached to the metal frame of the rocket engine jet deflector with silicon-impregnated carbon-carbon composite bolts, stainless steel bolts, and epoxy adhesive. In the cargo compartment, duralumin linings are additionally installed, which reduce the volume of the cargo compartment and provide aerodynamic profiling, which reduces the level of vibroacoustic loads on the structure of the aircraft itself.

The metal frame of the device for deflecting the jet of gases of the jet of the rocket engine is a welded structure made of stainless steel, consisting of two scarves and a lodgment, on which inserts are installed.

In places exposed to the jet of gases from the jet of a rocket engine, a heat-shielding coating is applied on the outer surface of the aircraft and linings.

The device for deflecting the gas jet of the jet of the rocket engine is made removable.

The metal frame has transverse stiffeners.

Further, the claimed invention is explained in more detail by the drawings, in which:

Fig. 1 is a view of the cargo compartment of the aircraft.

Fig. 2 - the principle of operation of the device for deflecting the jet of gases of the jet of a rocket engine.

Fig. 3 - a device for deflecting a jet of gases from a rocket engine torch installed on a launcher.

Fig. 4 - a device for deflecting a jet of gases from a rocket engine torch.

The claimed aircraft with a device for the safe launch of missiles contains an aircraft body with a cargo compartment (1), in which a launcher (2) is installed, on which, in turn, a device (3) is installed for deflecting a jet of gases from a rocket engine torch (hereinafter referred to as the jet) . At the same time, duralumin linings (4) are installed in the cargo compartment (1) over its entire surface, which reduce the volume of the cargo compartment (1) and isolate the structure of the compartment itself and the equipment installed in the compartment from the jet stream, and also provides aerodynamic profiling, which reduces the level of vibroacoustic loads on the structure of the aircraft itself. In addition, the linings (4) reduce the volume of the cargo compartment (1) blown by the high-speed flow and ensure a smooth flow in the rear and front of the cargo compartment (1). By reducing the volume of the cargo compartment (1), the volume of air flowing through the compartment is reduced and, as a result, the intensity of vibroacoustic phenomena is reduced. A smooth descent in the rear part of the cargo compartment (1) ensures a uniform outflow of air from the compartment without the formation of vortices and stagnant zones, which also reduces the impact of vibroacoustic phenomena on the structure, units in the compartment and the rocket until the launch.

The jet deflection device (3) is a bucket-shaped structure and consists of a metal frame (5) and three inserts (6, 7, 8) made of carbon-carbon composite material impregnated with silicon. The metal frame (5) is a welded stainless steel structure, consisting of two scarves (9) and a lodgement (10), on which carbon-carbon inserts (6-8) are placed. To stiffen the structure, the metal frame (5) has transverse stiffening ribs (11) welded to the cradle (10) and scarves (9). The gussets (9) have flanges with holes (12) for attaching the device (3) to the launcher (2).

Since the temperature in the core of the rocket engine flame is very high, and among the combustion products of the fuel there are incandescent particles, as well as acid vapors, and at the same time the combustion products fly out of the engine nozzle at supersonic speed, the material of the inserts (6-8) is of particular importance, directly in contact with the flame. Inserts (6-8) are plates of carbon-carbon composite material impregnated with silicon. Such a composition makes it possible to withstand the full cycle of operation of a rocket engine without through penetration, burnout, or erosive entrainment. Inserts (6-8) are rectangular in shape to simplify the technological cycle of their manufacture. The central insert (7) is attached to the metal frame (5) by 6 bolts - four bolts (13) of the same carbon-carbon material as the inserts (6-8) and two bolts (14) of stainless steel.

Bolts (13) are installed in the area of the rocket engine plume core. The installation of ordinary metal bolts in this zone is unacceptable, since the erosive effect of the smallest hot particles of aluminum oxide will cut off the metal heads of the bolts, which will lead to the removal of the insert and the termination of the structure.

Two stainless steel bolts (14) are installed in the area below the impact zone of the rocket engine plume core.

They are designed to more securely hold the insert (7) in the cradle (10) because carbon-carbon bolts have low shear and tensile strength.

The side inserts (6, 8) are held in the cradle (10) each by five bolts - three (15) carbon-carbon and two metal (16). The distribution of bolts (15, 16) is similar to the distribution of bolts (13, 14) of the central insert (7).

Additionally, inserts (6-8) in the cradle (10) are installed on epoxy glue to hold them more securely and ensure that they cannot be torn off and get into the structural elements of the aircraft.

In places exposed to the jet on the outer surface of the aircraft and linings, a heat-shielding coating was applied according to a certain coating scheme, which was made taking into account the heat capacity of the units protected from temperature exposure, their thickness, the time of exposure to the jet during rocket movement and, as a result, thermal heating elements and their operating temperatures. The heat-shielding coating is made by any known material that has a reduced thermal conductivity, as well as an increased maximum operating temperature compared to the operating temperature of the structural materials of the aircraft and its units. Due to its low thermal conductivity, the heat-shielding coating reduces the level of heating of the aircraft structure to the level of operating temperatures, and due to the high maximum operating temperature, reliable fastening of the coatings to the aircraft units and a high service life of the entire structure are ensured.

The claimed design was practically implemented and tested on a firing stand with a positive result. A launcher, a jet deflection device and a standard rocket engine were installed on it, as well as an environment imitating the fuselage, wing and horizontal tail of the aircraft. At the same time, both regular launches and non-descent of the rocket were simulated (the engine was held in place by a locking device after the start of work). According to the materials of photo and video recording, it was established that the rocket engine jet reliably deviates to the side both at launch and at the initial stage of the trajectory, as well as during the entire time of engine operation during non-derailment. The results of temperature measurements by sensors installed on the fuselage, wing and horizontal tail simulators confirm that the temperature in these areas did not exceed the operating temperature for the materials from which the structural elements are made. Also, after testing, no visual changes or deformations of the structure were detected.

Thus, in the design of the claimed aircraft, the maximum protection of the structural elements of the aircraft from thermodynamic, vibroacoustic and erosive effects of the rocket engine torch is carried out.

Claims (5)

1. An aircraft with a missile launcher, containing an aircraft body with a cargo compartment, in which at least one missile launcher is installed, characterized in that the launcher has a device for deflecting the gas jet of the rocket engine torch, which is a bucket-shaped structure and consists of a metal frame and three inserts made of a carbon-carbon composite material impregnated with silicon, which are installed obliquely with respect to the axis of the launcher to form a channel for deflecting the jet of gases from the rocket engine flame, while the inserts are fixed on the metal frame of the device for deflecting the jet of gases from the rocket engine flame using carbon-carbon composite material impregnated with silicon, stainless steel bolts and epoxy glue, and additionally installed duralumin linings in the cargo compartment, which reduce the volume of the cargo compartment and provide aerodynamic profiling, which reduces the level of vibroacoustic loads on the structure of the aircraft itself. 2. An aircraft with a rocket launcher according to claim 1, characterized in that the metal frame of the device for deflecting the gas jet of the rocket engine torch is a welded stainless steel structure, consisting of two scarves and a lodgment, on which inserts are installed. 3. An aircraft with a rocket launcher according to claim 1, characterized in that in places exposed to the jet of gases of the rocket engine torch on the outer surface of the aircraft and linings, a heat-shielding coating is applied. 4. An aircraft with a rocket launcher according to claim 1, characterized in that the device for deflecting the gas jet of the rocket engine flame is made removable. 5. An aircraft with a missile launcher according to claim 1, characterized in that the metal frame has transverse stiffeners.

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