RU22326U1 - CARRIER MISSILE DEFENSE DEVICE - Google Patents

Description

“CARRIER MISSILE DEFENSE DEVICE

The technical field to which the device relates - the device relates to means of protecting aircraft (aircraft) from guided missiles and missiles with homing heads.

As an analogue, the missile RVV-AE, including the missile defense of an aircraft, is proposed (1, p. 92).

Coinciding essential features: the analogue contains a warhead including an explosive and a radio fuse.

The achievement of the technical result is hindered: the analogue, unlike the claimed device, does not contain a brake parachute, but it additionally contains a homing head, an engine, power steering amplifiers, hydraulics, etc. This leads, firstly, to the complexity and cost of the prototype and, secondly, to an increase in its overall dimensions. The maximum weight of a device with a TNT warhead is about 130 kg, while an analog weighs 170 kg (7, p. 44). On average, a device is about 3 times lighter than an analogue, and when more powerful types of explosives are used, this ratio increases by several times.

As a prototype, the device described in 2 is proposed. Concurrent essential features: the prototype includes a warhead containing an explosive and a brake parachute. The achievement of the technical result is hindered by:

1) The weight of the explosive of the warhead of the prototype is not specified. With small amounts of explosive, it is impossible to destroy an attacking missile if it maneuvers in the final section to reduce the impact of the shock wave, circling the ejected device with a possible increase in miss within the radius of destruction of its warhead.

2) A parachute with a constant dome geometry does not provide sufficiently fast braking of the device needed to combat maneuvering missiles (the braking force drops in proportion to the square of the speed), therefore the device must experience large initial overloads, which places higher demands on the strength of the dome material. In addition, a parachute with a constant dome geometry can provide operation in a smaller speed range, otherwise

IPC F41 HI 1/02

it will either be torn apart by the air pressure or it will not ensure that the device is removed to a safe distance from the media.

3) Since the weight of the explosive of the warhead of the prototype is not specified, for small quantities of explosive, very accurate angular guidance is required on the attacking missile, which makes it impossible to orient the velocity vector “by eye from an unequipped carrier aircraft.

4) The prototype is reset either by the command of the pilot, or then automatically by the actuation of the valve in the container (similar to feeding cartridges in a machine gun when the trigger is pulled). The charge is detonated after a certain period of time after the reset. Since the latent reaction period of the human operator is 0.2 s, the number of products needed to destroy the rocket, depending on the charge power, is in the range from several to several dozen pieces. Thus, the requirement of small weight and low cost of the device (protective ammunition) is not fulfilled.

5) Undermining the protective charges of the prototype is carried out after a certain period of time after its discharge and therefore at a certain distance from the carrier aircraft. This makes it impossible to intercept one missile with two devices at different distances from the carrier, when the first product destroys the missile, and the second rejects fragments of the fuselage flying in the direction of the plane.

The claimed utility model solves the above-mentioned disadvantages of the prototype (the ability to destroy maneuvering missiles at the final section of the missile; reducing the requirements for the strength of the dome material and expanding the range of speeds of the carrier aircraft suitable for dropping the device; the ability to use it from non-equipped carrier; reducing the weight and cost of ammunition, reducing the probability of carrier damage by fragments of a destroyed rocket).

Distinctive features necessary to achieve this result: the weight of the warhead of the device is not arbitrary, but is 20-1 OOKG of explosive in TNT equivalent; the device further includes a radio fuse; The brake parachute is made with variable dome geometry. Other types of results achieved:

1) Decreasing the dimensions of airborne equipment: an old-type fighter equipped with a set of these short-range defense devices can be protected from a new-generation fighter armed with long-range air-to-air missiles. So the F-22 “Reptor, created in accordance with the concept of“ the first to see the first to launch a rocket - the first to hit a target, is able to detect a target such as a cruise missile at ranges up to 225 km and destroy it at ranges up to 180 km (3, p. 22 -24). If the fighter of the previous generation, for example the SU-27, also has super maneuverability and is equipped with a set

short-range missiles (R-73), then it can, reflecting the attack, impose a close combat, in which

advantage. Very small dimensions

a radar station that detects attacking missiles (the detection range is proportional to the root of degree 4 of the power, and the power is proportional to the mass and dimensions) are ensured by the fact that the maximum reaction time is determined by the time the aircraft’s speed drops (if necessary) to a predetermined value, for example, .7-1 and time of rotation of the velocity vector to the desired position. To do this, it is enough to detect an attacking rocket (s) at a distance of about 10-20 km.

2) Increased efficiency in the absence of information on the range to the carrier on the other side: if there is no information on the range to the carrier, for example, when interfering with it, simultaneous synchronous attack from different angles is difficult. In addition, it is not possible to effectively maneuver an attacking missile enveloping an ejected device in a final section

Achievable result in private versions: a) A variant with the use of ammunition for a volume explosion significantly reduces the mass dimensions of the device compared to the version containing trotyl.

b) The option with a tow rope - due to the fixed length of the rope, increases the permissible angular error of pointing at the rocket. There is no need to determine the moment of reset of the device with an accuracy of tenths of a second. This enhances usability with non-equipped media.

c) Option with wings - reduces the failure of the device after a reset. This makes it easier to aim at a rocket from an unequipped vehicle, especially in combination with a tow rope.

LIST OF DRAWINGS FIGURES:

Figure 1. The device and its components.

Figure 2. Parachute release unit.

Fig.Z. Scheme of application of the device.

Figure 4. The device at the time of operation. Scatter chart

fragments.

Fig.Z. Brake parachute with variable dome geometry. INFORMATION CONFIRMING THE OPPORTUNITY

IMPLEMENTATION OF THE DEVICE.

A possible appearance of the device is shown in FIG. 1. The main components are shown schematically: the warhead 1, the radio fuse 2, and the brake parachute ejection unit 3. An embodiment of the brake parachute ejection unit is shown in detail in FIG. 2. The brake parachute 10, connected to the piston 11, is located inside the body of the device 8 until the spring is compressed 6. The spring abuts at one end against the wall 7 rigidly connected to the body and the other against the piston held by the pin 5. The piston is limited in movement nut 9. The parachute is covered by a cover 4, which is held by friction and is thrown out when the piston moves. A variant is possible when the cover is screwed into the nut during storage and removed during operation of the product. The mechanism works when, after the device is reset, the check is pulled out, the brake parachute with slings is thrown out and opens under the influence of the oncoming air flow.

The application diagram of the simplest embodiment of the device is shown in Fig.Z. If there is a threat of a missile attack, the pilot, if necessary, extinguishes the aircraft’s speed to a predetermined speed range (say. 7-1), for example, by performing the cobra maneuver, since the parachute’s braking force is proportional to the square of the incoming flow velocity and cannot be used effectively in the entire range . Next, the aircraft turns so that its velocity vector is directed at the attacking missile at an angle of 180 degrees and constantly supports this direction. In this case, the rocket moves towards the aircraft along the line of sight. When the attacking rocket approaches, a device 14 is reset, which can be attached to the aircraft using a tow rope 12 (shown by a dotted line). The vector of the speed of the device at the time of reset coincides with the vector of speed of the aircraft. A brake parachute 10 is attached to the rear of the hull, and the product begins to quickly lose speed, falling behind the retreating aircraft. Initial acceleration of braking should be the maximum possible (50-80 units), since a flying missile attacking almost rectilinearly can maneuver in the final section, circling the ejected device. Due to its static stability (the center of pressure is located behind the center of mass) streamlined by the incoming air stream, the device is kept from rotating around the center of mass under the action of disturbing moments, which makes it easy to calculate its trajectory and gives the desired orientation

-5 radio fuse. When the attacking rocket 13 flies near the device (the approximate distance to the aircraft is 50-150 m), its radio fuse is triggered and explosive is detonated (the estimated weight is 20-100 kg in TNT equivalent). When using more powerful explosives instead of TNT, for example A-IX-2, the weight of the warhead and the weight of the device can be reduced several times. This figure (20-100 kg) is selected from the calculation of creating a universal short-range defense device that would protect against kinetic weapons, taking into account the possible maneuver of an attacking missile in the final section, and could be used also from an unequipped carrier, where aiming is “by eye” and great errors in aiming. Kinetic weapons are understood as a new generation of anti-aircraft missiles capable, thanks to active homing and gas-dynamic rudders, of hitting a target with a direct hit (5, p. 9). When the attacking rocket is destroyed by a shock wave, unlike its fragmentation damage, there is practically no chance of a missile fuselage getting into the carrier.

In an explosion, according to (4, p. 177), for traditional explosives, the propagation radius of detonation products is Kd 10R, where R is the radius of a spherical charge of equivalent weight. The radius of the high-explosive destruction of the target (destruction by a shock wave) Kf (25-100) R. For a 30-kilogram charge, the radius of propagation of detonation products will be about 2 m, and the radius of high-explosive destruction with a minimum value of the coefficient is about 5-7 m.For a 100-kilogram (TNT) charge, the values of Kd and Kf increase by about 1.5 times.

The destruction of the attacking missile in the CD zone is accompanied by the detonation of its warhead, the release of fragments and the chaotic expansion of fragments of the hull. For a typical high-explosive fragmentation warhead, the diagram of fragment expansion is a thick-walled funnel whose axis coincides with

(4, p. 164-167), (7, p. 60.61). Figure 4 shows the device 14 at the moment of operation of its radio fuse and detonating attack rocket 13. The diagram of the expansion of fragments 15 is shown in section. Thus, the probability of hitting a carrier aircraft with fragments of a destroyed rocket is zero, and the probability of hitting fragments of the hull, inversely proportional to the square of the distance, is negligible. In the zone of high-explosive destruction of Kf there is no detonation of warhead missiles; fuselage fragments are discarded by the shock wave in the direction perpendicular

speed vector and fly past the target. The pressure and speed of the shock wave acting on the carrier are proportional to the cube of the distance and even at the near intercept boundary (50 m) they decrease by more than two orders of magnitude compared to their values at the boundary of the zone of high explosive damage.

To reduce the likelihood of a carrier aircraft being struck by fragments of the fuselage, a missile interception in a burst of two products can be used. For example, the first device meets a rocket at the turn of 70-80m. The second device at the moment of interception is 15-20m behind, and if the rocket fragments move in the direction of the plane (that is, fly near the device), a radio fuse is triggered and the shock wave discards the debris in the direction perpendicular to the velocity vector.

A parachute with a variable dome geometry is depicted in FIG. 5. The dome 10 is shown in section. Slings 16 are attached along its edges, and a cable 17 is connected to the central point. When, after some time after the ejection, the product speed drops, for example, by half, a miniature squib 18 fires and cuts the cable. The dome is fully opened, and its area is increased four times (the position of the opened dome and sling is shown by a dotted line). The igniter can be controlled, for example, from an accelerometer tuned to a specific overload value.

The guidance system in the rear hemisphere supports the required orientation of the aircraft's velocity vector relative to the attacking rocket and determines the moment of reset of the device. The permissible angular error of guidance is determined as the ratio of the radius of the high-explosive destruction of the rocket to the interception range. At the speed of the aircraft and the rocket, the approach speed is (here M is the speed of sound). Given the above values of the interception range (50-150m), the dynamic characteristics of the guidance system are characterized by values of the order of 10 Hz. Therefore, it is desirable to automate the guidance process, since the pilot has to follow the readings of other instruments; In addition, the option of firing a burst of missiles is possible. For a fully automatic system, it is necessary to install a radar station (radar) in the rear hemisphere. The minimum requirements for such a radar are low. It should detect a target like an AIM-9X rocket at such a distance that it would be possible to catch the speed of the aircraft if necessary and orient its vector relative to the attacking rocket. For a fighter, this is about 10-20 km. For example, radar "Mosquito-23

(7, p. 27). It is desirable to ensure not just destruction by a shock wave, but guaranteed detonation of the warhead of the attacking missile, since in this case its fragments fly over a long distance from the carrier. To this end, it is necessary to ensure the accuracy of the automatic guidance system so that the miss radius at the point where the device meets the missile is comparable to the Cd radius if the attacking missile moves along the classical trajectories of the proportional approach method.

However, this kind of reaction is possible when a rocket begins to maneuver around a slightly curved approach path, for example, according to a pseudo-random law. In this case, the ejection of the device can be performed 0.6-0.8 s before the carrier aircraft is hit by an attacking rocket. Initial braking acceleration of 50-80 units. Interception takes place at a safe distance - more than 50m from the carrier. Suppose an automatic guidance system ideally tracks the angular position of a rocket. If, after a device is reset, a rocket flying at a speed begins to maneuver around a classical approach trajectory with a normal acceleration of 15 units, then over a period of time dt it will deviate by an angle d0 -, where N is normal overload, V speed (8, p. 354). Thus, in 0.5-0.7 s (the period of time from the ejection to interception), the deviation will be about 8-11 m, that is, the attacking rocket will not leave the zone of high-explosive damage of 100 kilograms of TNT charge. The destroyed missile fuselage flies at least 8-11 m from the carrier, and if after the maneuver of the attacking missile the aircraft guidance system generates a deflecting effect in the opposite direction, this miss will increase by another 1-2 m. The angular velocities monitored by the guidance system and, accordingly, the normal overloads of the carrier aircraft increase as they approach. If the rocket begins to maneuver just before the moment of ejection of the device with an overload of 20 units, then the maximum overload of the carrier tracking this maneuver 0.4s before the meeting will be approximately 2.5 units. The use of powerful explosives, such as A-IX-2, can significantly reduce the dimensions of the device. In this case, the aircraft can carry several sets, each of which is equipped with parachutes of various sizes. Thus, the range of speeds at which the device is reset from the carrier aircraft is expanded and the reaction time to a missile attack is reduced.

maneuvering with an amplitude greater than the radius of destruction of a warhead missile is impossible.

In the final approach section, the aircraft carrier velocity vector can be directed at an angle of 180 degrees to the instantaneous meeting point (the point at which the rocket and the device reset at the given moment would collide if the rocket velocity vector did not further change in magnitude and direction), adjusted for failure of the product by gravity. In addition, an allowance for maneuvering the attacking rocket may be added.

A possible implementation of an automated guidance system involves the installation of an optical sight, rigidly connected with the axis of the aircraft, in its tail. The image is transmitted to the indicator installed in the cab. During the guidance process, the pilot continuously combines the missile mark with the mark deviated from the crosshairs by the angle of attack and the angle of the carrier’s slip. For the method of proportional approach, implemented in the head of an attacking missile, the approach paths differ little from the straight-line ones and the angular velocity of the line of sight is small, which allows you to maintain the desired carrier orientation manually.

When using the tow rope option, the device after the discharge follows the aircraft at a distance equal to the length of the cable. The cable can be elastic or attached to the aircraft through a spring to damp the jerk under tension. If, for example, the cable length is 80 m, and the device is thrown out at a distance of 600 m from the carrier, then for a radius of high explosive destruction of 6 m, the admissible angular pointing error will be of the order of ± 4.5 degrees. With such a large tolerance at low angles of attack of the carrier aircraft, the pilot can orient the aircraft “by eye.” The device is reset 1-2 seconds before meeting the rocket. The use of the cable option is effective only when attacking with a single missile that does not maneuver in the final segment, or with a missile with a small miss radius, for example, with a Stinger, in clear weather, when the inverse trace and torch of the attacking missile are visible at a great distance.

In order to ensure the use of a carrier moving at a lower speed (plane or helicopter), the device may further comprise wings creating additional lifting force, mounted at a non-zero angle to its center line. It is also advisable to use this option when working with a cable on non-equipped media, when the device’s flight time is 1-2 seconds. Wings reduce device dropping

 after resetting it. It can be equipped with interchangeable parachutes for different speed ranges. A universal option with removable wings is possible: a device with removed wings is used from specially equipped media, a device with installed ones - from non-equipped.

To miniaturize the device as an explosive in the warhead of the device, liquid pyrotechnic mixture can be used, as well as other components of the volume explosion ammunition: auxiliary charge, spraying the mixture into an aerosol cloud, and so on. secondary detonator, performing its detonation after a given period of time. This ammunition is about an order of magnitude superior in power to a classic ammunition of equal weight. In a volume explosion, for example, in a thermobaric mixture, according to (6, p. 59), a detonation wave is formed, which is more extended in space and time than for traditional explosives.

Large overloads arising during braking make high demands on the strength of the parachute. So its slings can be made of synthetic material, and the dome is made of Kevlar-type fabric, etc.

Claims (4)

1. A missile defense device of the carrier, including a brake parachute and an explosive containing warhead located inside the housing, characterized in that the device further comprises a radio fuse, the amount of explosive is 20-100 kg in TNT, and the brake parachute has a variable dome geometry.  2. The device according to claim 1, characterized in that the warhead contains as an explosive liquid pyrotechnic mixture, and also additionally contains components of the ammunition of a volumetric explosion.  3. The device according to any one of claims 1 and 2, characterized in that it further comprises a tow rope attached to the bow of the hull. 4. The device according to any one of claims 1 to 3, characterized in that it further comprises wings in the central part of the body.