RU2659436C1 - Anti-aircraft missile - 2 - Google Patents

Abstract

FIELD: military equipment.

SUBSTANCE: invention relates to the anti-aircraft and aviation air-to-air missiles. Anti-aircraft missile has two or more fuselages with jet engines. Between the fuselages there is a wing. On the wing sides the fuselages are made and placed so, that at supersonic speeds they act as the aerodynamic baffle plates. At that, the fuselages have approximately perpendicular to the wing tail fins. They enable the device stabilization in the transverse to the wing direction. There is a system with two wing surfaces, separated from the mid-wing by 120–150 degrees. One of them reduces the air overflow possibility from the increased pressure zone, and the second is the air suction into the rarefaction zone.

EFFECT: improvement in the missiles maneuverability.

1 cl, 5 dwg

Description

The invention relates to anti-aircraft and aircraft missiles of the air-to-air class.

Such rockets are known, see, for example, patent No. RU 2439476, consisting of a round fuselage of a cylindrical section, a rocket or jet engine, rudders and plumage.

A disadvantage of the known missiles is the low aerodynamic quality of the plumage, which is why their capabilities for overload achieved in flight (i.e., maneuverability) are limited. Modern unmanned aircraft and cruise missiles, in which there is no man and, therefore, their permissible overload in flight can reach 20 or more g, will soon "learn" to make an anti-ballistic maneuver, and their defeat with existing anti-aircraft missiles will become impossible.

The objective and technical result of the invention is to improve the maneuverability of anti-aircraft missiles. In addition, the proposed rocket will be able to shoot backwards during the flight of the aircraft, since due to good aerodynamic quality it will be able to turn 180 degrees in the air immediately after launch.

OPTION 1. For this, this missile contains the aforementioned elements, but has two or more fuselages with jet engines, between which there is a wing. The aerodynamic quality of such a wing is quite large, since the fuselages on the sides of the wing play the role of aerodynamic washers. The bearing capacity of the fuselages themselves also increases, see FIG. 2.

It is possible that the aerodynamic quality of the wing improves (purges in the entire speed range are necessary), if two consoles on the sides of the fuselages lying in the plane of the middle part of the wing are added to its middle part between the fuselages, see FIG. 1, 3. Or, perhaps, the best aerodynamic quality at supersonic speeds will be shown by a system with two wing surfaces that are 120-150 degrees apart from the middle part of the wing, see FIG. 4. At the same time, one such surface limits the flow of air from the zone of high pressure, and the second limits the intake of ambient air into the rarefaction zone.

To stabilize in the transverse direction to the wing, the fuselages have small keels, approximately perpendicular to the wing.

Such a missile has increased maneuverability only in the direction perpendicular to the wing plane, therefore such a missile is controlled “in an airplane way”, that is, to rotate the missile first rolls and then increases the lift on the wing. To enable the rocket to roll, its front “duck” rudders have the ability to make “scissors” (like the MIG-23 rudders), and the rudders can only be located on one side of each fuselage — on the “outside”. This arrangement of the rudders also reduces their interference with the wing.

For good controllability, the center of gravity of the rocket should be between the fuselages with equal accuracy at an equal distance from both. This can be achieved, in particular, by varying within certain limits the mass of the warhead of the rocket, which can be located only in one fuselage of the rocket. In another fuselage, a homing head, power supply, control system can be located. But it’s possible that warheads will be in each fuselage, but possibly of different masses.

Compared to a single rocket of the same diameter, the rocket will have a larger specific impulse, since the same payload will be supplied with not one but two rocket engines.

OPTION 2. You can apply two or more fuselages, connected closely without a wing between them. That is, the rocket contains an engine and rudders, but has two or more fuselages connected side by side with the gaps at the joint.

It makes sense to connect so no more than three fuselages, see Fig. 5.

The missile in the second embodiment, as well as in the first, may have side consoles or wing surfaces.

In FIG. 1 in a plan view, and in FIG. 3 in a section along the midship (that is, along the largest wing section) 3 shows the first variant of the rocket with two fuselages and with two side consoles. In FIG. 2 shows a first embodiment of a missile without side arms. In FIG. 4 shows a first variant of a rocket with two wing surfaces from each side, located at angles of ± 135 degrees. In FIG. 5 shows a second embodiment of a rocket with three fuselages.

On each of the figures are marked: 1 - fuselage, 2 - wing, 3 - side arms, 4 - side wing surfaces, 5 - rudders of the “regressive weathervane duck” type (patent No. 2410286), 6 - keels.

The rocket works as follows: if necessary, maneuver the rocket due to the “scissors” (i.e., multidirectional deviation of the rudders) of the rudders 5 is rotated along the roll so that the plane of the wing 2 is perpendicular to the direction of the required maneuver, and due to the unidirectional deviation of the rudders 5 performs a maneuver with the required overload (this method of missile flight was considered earlier). The rest of the rocket works like a regular anti-aircraft missile.

Claims (2)

1. An anti-aircraft rocket containing rudders, plumage and engine / engines, characterized in that it has two or more fuselages with jet engines between which there is a wing, the fuselages on the sides of the wing are made and placed in such a way that they act as aerodynamic washers on supersonic speeds, while the fuselages have keels approximately perpendicular to the wing, providing stabilization of the device in the direction transverse to the wing, and a system with two wing surfaces spaced 120- from the middle of the wing 150 degrees, one of which reduces the possibility of air flow from the high pressure zone, and the second - the suction of air into the rarefaction zone. 2. The rocket under item 1, characterized in that the front rudders "duck" have the ability to make "scissors", and the rudders are located only on one side of each fuselage.

Images