RU2591540C1 - Kinetic warhead (versions) - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to missile defense. Kinetic warhead is equipped with a guidance system and liquid-propellant engines (LPE) directed sidewards or side-backwards. LPEs are arranged in one transverse plane ahead or behind the warhead centre of mass. Warhead has a fuel components consumption synchroniser. Three or more end-to-end joined tanks of the same diameter with liquid-propellant engines fixed onto them are secured on the warhead parallel to its longitudinal axis and hingedly with the ability to turn into the plane of the centre of mass of remaining part of the warhead.

EFFECT: higher combat effectiveness of the warhead.

7 cl, 5 dwg

Description

The invention relates to missile defense and is intended to defeat enemy ballistic warheads and space satellites.

Known Standard-3M missiles with kinetic warhead, see Internet resource, Wikipedia, Kinetic warhead. Its serious drawback is the use of a multi-nozzle solid propellant rocket engine (TTRD). As a result of this, the kinetic warhead has a limited time of active operation (i.e., flight with the ability to taxi) and, since the performance of the turbojet engine is approximately constant, there is a relatively small available thrust.

The objective and technical result of the invention is to increase the combat readiness of the warhead by significantly increasing the time of active work and the maximum available thrust of the warhead, as well as by increasing its piercing properties.

OPTION 1. For this, like the prototype, the warhead has a guidance system and engine, but liquid-propellant rocket engines (LRE) are used, directed sideways or side-back and located so that the thrust vectors pass through the center of mass of the warhead. This immediately changes the matter - modern tanks for rocket fuel allow long-term storage of components of liquid rocket fuel with the ability to use them at any time. That is, the active period of the warhead to the top of its trajectory. And since in the LRE it is possible to organize the supply of components in a sufficiently large amount, it is possible to achieve a significantly higher maximum thrust than with a turbojet engine. That is, it is possible to intercept targets maneuvering with greater overload than this indicator in the prototype.

It is desirable to use self-igniting components of rocket fuel - fuel and oxidizer.

It is advisable to use a propellant system for supplying fuel components. True, it ensures that the fuel tank is filled only by about 50%, the rest is necessary for the supply of gas (the use of cylinders with a reducer will probably only make the design heavier). To compensate for the decreasing pressure of the displacing gas, which decreases as the fuel consumption, it is necessary to provide increased flow areas of pipelines, nozzles and valves.

It is advisable to use six rocket engines located at an angle of 60 degrees in the plane of the transverse projection. In this case, it is possible to immediately turn on 2 or 3 engines to get maximum thrust. The maximum achievable thrust in this case ranges from 173.2% to 200% of the thrust of one rocket engine.

You can arrange the engines in the transverse plane, and then the lateral thrust will be maximum, or you can orient the engines side to back (about 15-20 degrees), then they, having slightly lost in the lateral thrust, will also give forward thrust. This will require the introduction of instant correction in the guidance system, since the translational speed of the warhead will quickly change, but this will increase the height and range.

To maintain orientation in space, the warhead has 6 steering liquid rocket micromotors located in one transverse plane in front or behind (hereinafter all directions are given relative to the direction of flight of the warhead) of the center of mass of the warhead, 4 of which are parallel to each other for roll orientation. These engines can run on the same fuel, or on a more convenient one-component fuel. A single-component fuel tank may be located in the center of mass of the warhead or two tanks should be located on either side of the center of mass (see below).

But the use of liquid propellant rocket engines in a warhead requires a special arrangement of tanks with fuel and oxidizer, such that the center of mass of the warhead does not change when the fuel components are used up.

SUB-OPTION 1a. One of the options for this arrangement of tanks is the same - identical tanks with fuel and oxidizer are located in pairs in front and behind the center of mass of the warhead at the same distance from it.

In this case, to synchronize the flow of fuel components from the front and rear tanks, it is necessary to use a flow synchronizer. It consists of two volume displacement machines of the same capacity, located on the same shaft. Three such synchronizers are needed - for tanks with fuel, for tanks with oxidizing agent and for the ratio of fuel with oxidizing agent. You can combine them into one, it will be two volumetric displacement machines for fuel, and two volumetric displacement machines for the oxidizer, pairwise located on the same shaft with a gap between the pairs (so that the synchronizer does not explode).

It is advisable to make the rear ends of the tanks more durable than the front, since they experience a greater load during longitudinal overloads.

The above arrangement of the tanks is shown in FIG. 1. In the plane of the center of mass are six liquid propellant rocket engines 1, in front and behind them (left and right in the drawing) there are two cylindrical combined tanks for fuel 2, and for oxidizer 3 (the left tank is shown in section). On the side facing the engines, it has thermal insulation 4. For uniform distribution of the masses of the warhead, it has two compartments for equipment - front 5 and rear 6 (they can have an antenna, electronics, batteries, etc.). In the rear compartment, six steering micro-rocket engines 7 are shown.

The warhead works due to LRE and steering micro LRE, sharply moving perpendicular to the longitudinal orientation of the warhead.

To separate the fuel components from the displacing gas, tanks must have bellows, membranes, or pistons. However, pistons with such a ratio of diameter / length are unstable and can get stuck, and membranes and bellows do not tolerate lateral overloads.

SUB-OPTION 1b. To prevent this drawback, the mentioned diameter / length ratio should be reduced. Therefore, in this sub-variant, the warhead has the same fuel and oxidizer tanks, arranged in pairs, in parallel and with respect to point symmetry with respect to the center of mass in front and behind the center of mass of the warhead at the same distance from it.

This sub-option is shown in FIG. 2 is a side and rear view (only engines, tanks and side compartments 8 are shown, all other elements are similar to FIG. 1). The warhead contains, on the left and on the right, one cylindrical tank for fuel 2 located in compliance with point symmetry with respect to the center of mass of the CM, and one tank for oxidizer 3 located in the same way (crosswise in the drawing). To fill the empty space near the tanks, sector compartments with equipment 8 are located next to them in front and behind.

This sub-option works the same way.

SUB-OPTION 1c. But the previous sub-option has a poor fill factor for the cross section of the warhead. To improve this coefficient and to improve the diameter / length ratio of the tank in this sub-variant, the warhead has two fuel tanks in front and behind and two oxidizer tanks located in pairs in front and behind the center of mass of the warhead at the same distance from it.

It should be noted that in this option the total surface of the tanks increases, which theoretically can cause an increase in their mass. However, the smaller the diameter of the tank, the thinner its wall may be. Therefore, the increase in tank mass will be negligible.

This sub-option is shown in FIG. 3 is a side and rear view (only engines and tanks are shown, all other elements are similar to Fig. 1). The warhead contains front and rear two cylindrical fuel tanks 2 arranged in parallel, and two oxidizer tanks 3.

This sub-option works the same way.

SUB-OPTION 1g. But the tanks can be arranged asymmetrically. It is only necessary to comply with the condition of constancy of their common center of mass when consuming fuel. That is, a warhead has two tanks with fuel and an oxidizing agent located on opposite sides of the center of mass, but the equation should be observed regardless of fuel consumption:

K (L + A) = 1 + a,

where K is the ratio by volume of the larger component of the fuel to the smaller, for example, an oxidizing agent to fuel,

L is the distance from the inner end of the large tank to the center of mass of its fuel,

A is the distance to the inner end of the large tank from the center of mass of the warhead,

1 - the distance from the inner end of the small tank to the center of mass of its fuel,

and - the distance to the inner end of the large tank from the center of mass of the warhead.

Let us agree to consider the end face to be the end face facing the center of mass. Since the end of the tank usually takes the form of a part of a sphere or a semi-ellipsoid of revolution, we will agree to consider the distance to the “equivalent” end, that is, to the flat end of the tank with a flat end, which is equal in volume to the tank with a spherical or semi-elliptical end.

This equation can be observed regardless of flow rate only if L = K * 1.

This sub-option is shown in FIG. 4 is a side view (only engines and tanks are shown, all other elements are similar to Fig. 1). The warhead contains an oxidizer tank 3 in front of the center of mass (the oxidizer tank is usually larger than the fuel tank, with the exception of the hydrogen tank), and behind the fuel tank 2. To reduce the total length of the tank 2, its gas part looks like a glass 9 larger diameter than the diameter of the tank. For the separation of fuel and gas there is a piston 10 in the form of a glass.

Suppose that the distance L = 2 units (conditional), the distance A = 1 unit, and the coefficient of the oxidizer / fuel ratio is 2.5 (which approximately corresponds to the fuel “solution of nitrogen pentoxide in nitric acid + terpenes, that is, turpentine). Then the distance 1 = 5 units, and the distance a = 2.5 units. This ratio is shown in FIG. 4 in the bottom line of dimensions.

OPTION 2. However, another way is possible to maintain the constancy of the center of mass of the warhead during fuel consumption - to place the tanks transversely in the plane of the center of mass. In this embodiment, three or more combined (that is, joined by ends of the same diameter) tanks with liquid propellant rocket engines mounted on them are mounted on the warhead parallel to its longitudinal axis with the possibility of rotation into the plane of the center of mass of the rest of the warhead (see Fig. 5). The "rest" is a warhead without tanks and main rocket engines.

This option is good because the tanks with engines turned to the working position increase the midship of the warhead (therefore, it is good if there are six of them), and in case of a small miss on the well-maneuvering target, the warhead can touch the target with a tank or engine. Since in the event of a counter defeat, the total counter speed is approximately 6-7 km / s, even a slight touch of the target by the engine of the warhead is equivalent to a strong explosion.

True, this option also has a certain drawback - its engines cannot be positioned in the side-to-back direction, otherwise the center of mass will not be constant during fuel consumption.

This embodiment is shown in FIG. 5 is a side view (one combined tank with the engine is shown in a parallel position (upper in the drawing), and the second in the tilted position (lower in the drawing). The warhead consists of the same parts as in FIG. 1, but has tanks not in front and behind the center of mass, and has rotary blocks 11 in the form of combined tanks for fuel 2 and for oxidizer 3 with engines 1. The front 5 and rear 6 compartments for equipment are also available in the rear compartment. 5 and 6 are connected by a compartment 12, which may be, for example, an explosion hydrous substance.

This option works like this: after going beyond the atmosphere, the skin and fairing are reset, blocks 11 are rotated to the plane of the center of mass, and the operation of the rocket engine blocks can change the trajectory of the warhead.

OPTION 3. The prototype has a tungsten kinetic damaging element. But its functions can be combined with a gyroscope of precise roll orientation. This warhead has a gyroscope in the form of a segment of a cylinder with a sharp front edge and has the spokes of this gyroscope in the form of sharp front plates.

To enhance the damaging effect, the front axis of the gyroscope has slots on which the gyro wheel is fitted with an interference fit, and the wheel is centered by two thrust bearings. That is, the axis has the ability to fly forward and, separately from the gyroscope, inflict a deeply penetrating lesion on the target.

This embodiment is shown in FIG. 1. In the front compartment for equipment 5 there is a gyroscope wheel 13 in the form of a segment of a cylinder located on the axis 14.

This option works like this: during the extra-atmospheric warhead guidance section, precise roll control is performed using a gyroscope. When impacted with a target, the pointed wheel of the gyroscope in the form of a segment of the cylinder 13, its spokes (shown by a dotted line) and the pointed axis 14 cause a deep penetrating damage to the target.

Claims (7)

1. A kinetic warhead containing a guidance system and liquid rocket engines directed sideways or sideways-back, characterized in that it also has 6 steering liquid rocket micromotors located in one transverse plane in front of or behind the center of mass of the warhead, 4 of which are parallel to each other for roll orientation. 2. A kinetic warhead containing a guidance system and liquid-propellant rocket engines directed sideways or side-back, characterized in that for synchronizing the flow of fuel components from the front and rear tanks there is a flow synchronizer, which is two volumetric displacement vehicles for fuel, and two volumetric displacement machines for the oxidizing agent, located in pairs on the same shaft with a gap between the pairs. 3. The warhead according to claim 2, characterized in that it has two tanks with fuel and an oxidizing agent located on opposite sides of the center of mass, but the equation is observed regardless of fuel consumption:
K (L + A) = l + a,
where K is the ratio by volume of a larger component of the fuel to a smaller one, for example, an oxidizing agent to fuel,
L is the distance from the inner end of the large tank to the center of mass of its fuel,
A is the distance to the inner end of the large tank from the center of mass of the warhead,
l is the distance from the inner end of the small tank to the center of mass of its fuel,
and - the distance to the inner end of the large tank from the center of mass of the warhead. 4. A kinetic warhead containing a guidance system and an engine, characterized in that three or more tank ends joined by the same diameter of the tank with liquid rocket engines fixed to them are mounted on the warhead parallel to its longitudinal axis and pivotally with the possibility of rotation into the plane of the center of mass of the rest of the warhead. 5. A kinetic warhead containing a guidance system and an engine, characterized in that it has a gyroscope in the form of a segment of a cylinder with a sharp front edge and has the spokes of this gyroscope in the form of sharp front plates. 6. Warhead according to claim 5, characterized in that the axis of the gyroscope, which is pointed in front, has slots on which the gyroscope wheel is fitted with an interference fit. 7. Warhead according to claim 5, characterized in that the gyro wheel is centered by two thrust bearings.

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