Title:
Portable surface-to-air missile system
Kind Code:
A1


Abstract:
A portable surface-to-air missile system has a missile with a frequency-modulated infrared autonomous guidance head and a selector electrically and pneumatically connected to a launcher, said selector being formed as an infrared autonomous guidance head operable to use kinematic differences between a real target and a deception flare, and said launcher having an indicator changing an operating program of said selector.



Inventors:
Shumov, Sergeyi Alexandrovich (Kyiv, UA)
Buzanov, Viktor Ivanovich (Kyiv, UA)
Molodyk, Anatolyy Vladimirovich (Kyiv, UA)
Zabolotnyy, Ivan Ivanovich (Kyiv, UA)
Kuzmin, Lev Vasylyevich (Kyiv, UA)
Application Number:
10/881516
Publication Date:
08/18/2005
Filing Date:
06/30/2004
Assignee:
SHUMOV SERGEYI A.
BUZANOV VIKTOR I.
MOLODYK ANATOLYY V.
ZABOLOTNYY IVAN I.
KUZMIN LEV V.
Primary Class:
Other Classes:
244/3.15
International Classes:
F41G7/22; (IPC1-7): F41G7/00; F42B15/01
View Patent Images:
Related US Applications:



Primary Examiner:
GREGORY, BERNARR E
Attorney, Agent or Firm:
ILYA ZBOROVSKY (DIX HILLS, NY, US)
Claims:
1. A portable surface-to-air missile system, comprising a missile with a frequency-modulated infrared autonomous guidance head and a selector electrically and pneumatically connected to a launcher, said selector being formed as an infrared autonomous guidance head operable to use kinematic differences between a real target and a deception flare, and said launcher having an indicator changing an operating program of said selector.

2. A portable surface-to-air missile system as defined in claim 1, wherein said launcher includes a transform and launch container, a launch mechanism and a power supply unit.

3. A portable surface-to-air missile system as defined in claim 2, wherein said selector is formed as interconnected analyzer, logic unit and function circuit.

4. A portable surface-to-air missile system as defined in claim 3, wherein an input of said analyzer is electrically connected to an output of a light signal amplifier, an output of said analyzer is electrically connected to a first input of said logic unit, a second input of said logic unit is electrically connected to said launcher, a first input of said logic unit is electrically connected to a first in put of said function circuit, a second input of said function circuit is electrically connected to an output of a cage winding, and an output of said function circuit is electrically connected to one of inputs of a correction amplifier.

5. A portable surface-to-air missile system as defined in claim 4, wherein said analyzer is formed as an electrically interconnected amplifier, two comparitors and a timer, wherein an input of said amplifier are electrically connected to an output of a light signal amplifier, an output of said amplifier are electrically connected to inputs of comparitors, outputs of said comparitors are electrically connected to an input of said timer, and an output of said timer is electrically connected to a first input of said logic unit.

6. A portable surface-to-air missile system as defined in claim 1, wherein said logic unit is formed as a switch.

7. A portable surface-to-air missile system as defined in claim 1, wherein said function circuit is formed as electrically interconnected two switches, two function formers, a generator and an analog random-access memory, with a first input of said analog random-access memory electrically connected to an output of said correction amplifier, with a second input of said analog random-access memory electrically connected to an output of said generator, with an output of said analog random-access memory electrically connected to an input of a first function former, with an output of said first function former electrically connected to a first input of a first switch, with a second input of said first switch electrically connected to a first output of said logic unit, with an output of said first switch electrically connected to one of the inputs of said correction amplifier, with an input of said second function former electrically connected to an output of said cage winding with an output of said second function former electrically connected to said first input of said second switch, with a second input of said second switch electrically connected to a first input of said logic unit, with an output of said second switch electrically connected to one input of said correction amplifier.

Description:

BACKGROUND OF THE INVENTION

The present invention relates to a missile technology and particularly to portable surface-to-air missile systems (PSAMs).

Portable surface-to-missile systems are known, which have been designed to hit targets moving at low altitudes, as disclosed for example in the international patent application WO 98/16794 published on Apr. 23, 1998. The known portable surface-to-air missile system includes a guided missile with an optical autonomous guidance head and a launcher connected to it, which includes a transport-and-launch container, a power supply unit, and a device increasing the precision of hitting. However, the known system does not insure separation of deception targets from real ones and therefore its efficiency is low.

Another known solution is disclosed in U.S. Pat. No. 6,565,036 published on May 20, 2003 which claims an enhanced precision of hitting of high-speed air targets. However, this system is mainly designed for artillery and includes a piecing body-long rod-as a hitting element. In addition, both the placement of light sensors inside such a rod and the use of optical lens substantially complicate this known system.

A further high-precision optical guidance missile is disclosed in U.S. Pat. No. 6,142,412 published on Nov. 7, 2000. This missile consists of an optical autonomous guidance head, a launcher and a power supply unit. However, while in flight the missile course needs to be corrected which requires the reception of a relevant signal from a ground installation. This substantially complicates both the missile design (Kalman filters need to be installed) and its launch. In addition, it requires additional substantial expenses.

A further solution is a portable surface-to-air missile system IgIa-1-9K310, which includes a missile with a frequency modulated autonomous guidance infrared head with a selector, and a launcher connected to it which includes a transport and launch container, a launcher, and a power supply unit (IgIa-1) Portable Surface-to-Air Missile system (9K310). Technical Description and Operations Manual for 9K310/TO, Moscow, Voyennoye Izdatelstvo Publishing House, 1983). This device is considered as a prototype.

The main disadvantage of this known solution is a not sufficiently high flare resistance of the surface-to-air missile system, whereas the anti-flare requirements are among the decisive ones.

To fight surface-to-air missiles using infrared guiding systems, up-to-the date combat aircraft utilize thermal deception targets as infrared deception flares (IRDF), which are ejected by the carrier aircraft. The energy parameters of an IRDF are in excess of energy parameters of its carrier aircraft. The infrared guidance system of the missile that was tracking the radiation of the combat aircraft switches over to track a more powerful radiation source, which is an IRDF. The IRDF moves in space with regard to the combat aircraft. At a time the target that has aimed at and the IRDF do not fit into the sight of the missile guiding system, and since the guidance system is tracking a more powerful IRDF, the target that has been aimed at goes out of the missile guidance system, which results in missing it.

SUMMARY OF THE INVENTION

It is therefore an object of the present invention to provide a portable surface-to-air missile system, in which vulnerability to flares is minimized by equipping autonomous guidance head of the system with a system distinguishing the target from an IRDF.

In keeping with these objects and with others which will become apparent hereinafter, one feature of the present invention resides, briefly stated, in a portable surface-to-air missile system which has a a missile with a frequency-modulated infrared autonomous guidance head and a selector electrically and pneumatically connected to a launcher, said selector being formed as an infrared autonomous guidance head operable to use kinematic differences between a real target and a deception flare, and said launcher having an indicator changing an operating program of said selector.

In accordance with another feature of the present invention, the analyzer is formed as an electrically interconnected amplifier, two comparitors and a timer, with the input of the amplifier is electrically connected to the output of the light signal amplifier, where the output of the amplifier is electrically connected with the inputs of the comparitor, the outputs of the comparitors are electrically connected to an input of the timer, and the output of the timer is electrically connected to the first input of the logic input.

In accordance with a further feature of the present invention, the logic unit is formed as a switch, while the function circuit is formed as electrically interconnected two switches, two function formers, a generator and an analog random-access memory, with the first input of the analog random-access memory being electrically connected to the output of the correction amplifier, with a second input of the analog random-access memory electrically connected to the output of the generator, with the output of the analog-random-access memory electrically connected to the input of the first function former, with the output of the first function former electrically connected to the first input of the first switch, with the second input of the first switch electrically connected to the first output of the logic unit, with the output of the first switch electrically connected to one of the inputs of the correction amplifier, with the input of the second function former electrically connected to the output of the cage winding, with the output of the second function former electrically connected to the first input of the second switch, with the second input of the second switch electrically connected to the first output of the logic unit, and with the output of the second switch electrically connected to one of the inputs of the correction amplifier.

The cause and effect link between the new features of the present invention and the technical solution achieved by it, resides in introduction a programmed selector into the missile guidance system, which utilizes kinematic distances between the real target and deceptive flares, while the launcher has an indicator which changes selector operation of the selector.

The novel features which are considered as characteristic for the present invention are set forth in particular in the appended claims. The invention itself, however, both as to its construction and its method of operation, together with additional objects and advantages thereof, will be best understood from the following description of specific embodiments when read in connection with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a view showing an overall block diagram of a portable surface-to-air missile system;

FIG. 2 is a view showing a block diagram of a program selector of the inventive portable surface-to-air missile system;

FIG. 3 is a view showing a block diagram of an analyzer selector of the inventive portable surface-to-air missile system;

FIG. 4 is a view showing a block diagram of function circuits of the inventive portable surface-to-air missile system.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

A portable surface-to-air missile system in accordance with the present invention includes a missile which is identified with reference numeral 1 in FIG. 1.

The system further is provided with an infrared autonomous guidance head identified with reference numeral 2. An optical and mechanical unit is identified with reference numeral 3, an electronic compartment is identified with reference numeral 4, a program selector is identified with reference numeral 5, a launcher is identified with reference numeral 6, a transport and launch container is identified with reference numeral 7, a launch mechanism is identified with reference numeral 8 and a ground power supply is identified with reference numeral 9 in FIG. 1.

The system is further provided with an analyzer 10, a logic unit 11, and a function circuit 12 shown in FIG. 2.

The inventive system further has an amplifier 13, a first comparitor 14, a second comparitor 15, shown in FIG. 3.

Finally, the system includes an analog random-access memory 17, a generator 18, a first function former 19, a first switch 20, a second function former 21, and a second switch 22 shown in FIG. 4.

The portable surface-to-air missile system in accordance with the present invention operates as follows.

The first input of the missile 1 is electrically connected to the first output of the infrared autonomous guidance head 2. The output of the optical and mechanical unit 3 is electrically connected to the input of the electronic component 4, with the programmed selector 5 which forms a component of it. The output of the electronic component 4 is electrically connected to the input of the optical and mechanical unit 3. The launcher 6 is composed of the transport and launch container 7, the launch mechanism 8, and the ground power supply 9. The first output of the transport and launch container 7 is electrically connected to the second input of the missile 1. The second output of the transport and launch container 7 is electrically and pneumatically connected to the input of the infrared autonomous guidance head 2. The second output of the infrared autonomous guidance head 2 is electrically connected to the first input of the transport and launch container 7. The third input of the transport and launch container 7 is electrically connected to the input of the launch mechanism 8. The output of the launch mechanism 8 is electrically connected to the second input of the transport and launch container 7. The fourth output of the transport and launch container 7 is kinematically connected to the input of the ground power supply 9. The output of the ground power supply 9 is electrically and pneumatically connected to the third input of the transport and launch container 7.

The electric signal is supplied from the light signal amplifier to the input of the analyzer, which contains data on sources of input light signals, on targets and infrared autonomous guidance heads. The output of the analyzer is electrically connected to the first input of the logic unit (switch) 11. The electric signal from the transport and launch container goes into the second input of the logic unit 11. The electric signal from the first output of the logic unit 11 goes to the first input of the function circuit 12. The electric signal from the output of the cage winding (which is part of the optical and mechanical unit 3 goes into the second input of the function circuit 12. An electric signal from the output of the function circuit 12 goes to one of the inputs of the correction amplifier (which is a part of the electronic compartment 4).

The electric signal from the outlet of the light signal amplifier (which is a part of the electronic compartment 4) goes to the input of the amplifier 13. The electric signal from the first output of the amplifier 13 goes to the input of the first comparitor 14. The electric signal from the second output of the amplifier 13 goes to the input of the second comparitor 15. The outputs of the comparitors 14 and 15 are electrically connected to the first and second inputs of the timer 16, respectively. The output of the timer 16 is electrically connected to the first input of the logic unit 11.

The electric signal from the output of the correction amplifier (which is a part of the electronic compartment 4) goes into the first input of the analog random-access memory 17. The signal from the generator 18 goes to the second input of the analog random-access memory. The electrical signal from the output of the analog random-access memory 17 goes to the input of the first function former 19. The electric signal from the first function former 19 goes into the first input of the first switch 20. The electric signal from the output of the logic unit 11 goes into the second input of the first switch 20. The electric signal from the output of the first switch 20 goes into the input of the correction amplifier (which is a part of the electronic compartment 4). The electric signal from the output of the cage winding (which is a part of the optical and mechanical unit 3) goes into the input of the second function former 21. The electric signal from the output of the function former 21 goes into the first input of the second switch 22. The electric signal from the output of the logic unit 11 goes into the second input of the switch 22. The electric signal from the output of the switch 22 goes into the input of the correction amplifier (which is a part of the electronic compartment 4).

In the above described device, the first function former 19 is forming an electric signal at its output which is a function of the angular velocity ω of the target, for example K1*ω wherein K1=const. The second function former 21 is forming an electric signal at its output, which is a function of the target bearing φ, for example, K2*φ, where K2=const.

The trajectory and kinematic difference between the target being attacked and the infrared deception flares is based on the difference between the masses on the infrared deception flares and high-speed targets. Because of a substantial speed of the target and a swift spacial deceleration of the infrared deception flares, regardless of the direction of its dropping, at the end of the day the infrared deception flares will always be behind the target in space and the infrared autonomous guidance head coordinate system.

The optical system of the missile infrared autonomous guidance head receives an infrared signal about the targets in its side and delivers an electric signal about the targets to the electronic compartment of the infrared autonomous guidance head. The electronic compartment forms and delivers electrical commands both to the executing mechanism of the infrared autonomous guidance head control system (correction winding), which corrects the position of the infrared autonomous guidance head optical system axis, and to the actuating mechanism for the missile rudders (not shown in the drawings) during the flight.

The programmed selector forms commands for the actuating mechanism for the infrared autonomous guidance head control system (correction winding) which corrects the position of the infrared autonomous guidance head optical system axis, with the infrared deception flares going out of the missile guidance sight, and the target it has been aimed at remaining in the sight. This is the way ensuring that the target the missile has been aimed at has been hit.

The principle of the operation of the infrared deception flares trajectory and kinematic selector is in selecting from among the sources located in the sight those who have moved in space along the vector of angular velocity ω or along the bearing φ, in proportion to the signal in the cage winding, which has been set during infrared autonomous guidance head operation following the “launch” command (“LC”).

Upon arriving of an electric signal from the light signal amplifier to the analyzer, the signal is amplified and compared in the first comparitor with the value set beforehand. If the given value has been exceeded, the first comparitor 14 will send an electric signal about the appearance of an infrared deception flare to the logic unit 11 through the timer 16. The output signal from the logic unit 11 opens the first switch 20 and closes the second switch 22. Upon receipt of a correction signal and a signal from the generator 18 by the inputs of the analog random-access memory 17, the analog random-access memory with the given frequency of updating the correction signal and delivers it to the first function former 19 and further through the open switch 20 to the correction amplifier, to which an electric signal which is a function of the angular velocity ω comes. This signal corrects the gyroscope axis position.

Having sent the launch command LC (after the missile launch), the logic unit with a pre-selected delay time gives the command to close the first switch 20 and open the second switch 22. As a result, a signal from the second function former 21, which depends upon the bearing φ, will come to the input of the correction amplifier (in the electronic compartment 4). As the signal from the amplifier 13 decreases, the second comparitor 15 will work and switch off the timer 16 (or the timer will be off following the operation time set). When the signal from the analyzer 10 disappears, the logic unit 11 will block the signal from the outputs of the switches 20 and 22.

It will be understood that each of the elements described above, or two or more together, may also find a useful application in other types of constructions differing from the types described above.

While the invention has been illustrated and described as embodied in portable surface-to-air-missile system, it is not intended to be limited to the details shown, since various modifications and structural changes may be made without departing in any way from the spirit of the present invention.

Without further analysis, the foregoing will so fully reveal the gist of the present invention that others can, by applying current knowledge, readily adapt it for various applications without omitting features that, from the standpoint of prior art, fairly constitute essential characteristics of the generic or specific aspects of this invention.