RU2233420C2 - Method for provision of electric power supply for airborne equipment of guided missile and guided missile in transport-launching pack for its realization - Google Patents

Abstract

FIELD: flight vehicles, in particular, wire-controlled projectiles and missiles having no on-board DC power source of its own, launched from a transport-launching pack.

SUBSTANCE: the method for provision of electric power supply for the airborne equipment of the guided missile is divided into two phases. In the first phase electric power is accumulated from a DC power source of the ground equipment of missile control during a time period from the moment of missile launch to the break of the wire line between the missile and the DC power source of the ground equipment, and in the second phase the accumulated electric power is added from the pulses of emf of self-induction arising in the coils of the control electromagnets of the missile control actuator unit under the action of the control signals fed from the ground control equipment to the missile during its flight. The method is realized in the guided missile in the transport - launching pack with a battery for electric power supply of the ground equipment of missile control, having a wire line coil, control actuator unit with coils of the control electromagnets, safety-actuator mechanisms of the main and additional warheads and a time-delay device for provision of a delay of action of the main warhead relative to the additional one. The missile uses a converter, breakable wire line between the missile and the DC power source of the ground equipment, and accumulators of electric power of the safety-actuator mechanisms, and time-delay devices, the inputs of all accumulators of electric power are connected via the breakable wire line to the output of the voltage converter, whose input is connected to one of the coils of the control electromagnets of the control actuator unit, and the coils of the control electromagnets are interconnected and connected to the output of the wire line coil, whose input via the transport-launching pack is connected to the ground control equipment.

EFFECT: enhanced operating characteristics of guided missile due to enhanced reliability and reduced mass and overall dimensions of the missile.

2 cl, 1 dwg

Description

The present invention relates to aircraft, in particular to wire-guided missiles and missiles that do not have their own direct current source on board, fired from a transport and launch container, and can also be used in the development of aircraft automation.

Currently, on guided missiles, widespread use has found a way to provide power to the onboard equipment of a guided missile from its own direct current source.

A known method (it is also a prototype) of providing power to the onboard equipment of a guided missile and guided missile for its implementation [1]. The essence of the method is to provide power to the onboard equipment of a guided missile from its own direct current source installed on board the missile.

The specified method of providing power to the onboard equipment of a guided missile is implemented in a guided missile in a transport and launch container with a battery for powering the ground control equipment of the missile, containing two batteries for powering the onboard equipment, a coil of a wireline, a power drive of the control system that performs the functions of the steering drive unit, safety and executive mechanisms of the main and additional warheads and a time delay device to provide a delayed response the main warhead relative to the additional warhead.

The disadvantage of this method and guided missile for its implementation is the deterioration of the operational characteristics of a guided missile due to a decrease in reliability and an increase in the mass and dimensions of the missile due to the installation of batteries on board the missile.

The objective of the invention is to increase the operational characteristics of the rocket by increasing the reliability and reducing the mass and dimensions of the rocket by eliminating the on-board battery.

To achieve the task in the proposed method, the process of providing power to on-board equipment is divided into two phases:

- in the first phase, electric energy is accumulated from the direct current source of the ground-based missile control equipment for the length of time from the moment the rocket starts to the breakage of the communication line between the rocket and the direct current source of ground-based control equipment;

- in the second phase, the accumulated electrical energy from self-induction EMF pulses arising in the coils of the control electromagnets of the rocket’s steering gear unit is replenished under the influence of control signals supplied from the ground control equipment to the rocket during its flight.

The choice of such a technical solution to provide power to the onboard equipment of a guided missile is explained by the following. In the first phase, the accumulation of electrical energy occurs. However, the electric energy accumulated in the first phase due to its consumption of on-board equipment can decrease during the flight of the rocket to a value below the permissible level. To compensate for the loss of electric energy, a second phase was introduced - replenishment of the electric energy accumulated in the first phase from self-induction EMF pulses arising in the coils of the control electromagnets of the rocket steering drive unit. The accumulation of electrical energy only from EMF impulses of self-induction is impossible, because by the time rocket control begins, it is impossible to accumulate the necessary electric energy because of their low power and short time interval from the moment the rocket starts to the break of the communication line between the rocket and the transport launch container, in which the battery is located to power the ground-based rocket control equipment.

The specified method of providing power to the onboard equipment of a guided missile is implemented in a guided missile in a transport and launch container with a battery for powering the ground control equipment of a missile containing a coil of a wireline, a steering drive unit with coils of control electromagnets, safety-actuating mechanisms of the main and additional warheads, and a time delay device for providing a delay in the response of the main warhead relative to the additional one. Once again, an AC-to-DC converter is inserted into the rocket, a disconnected wire line between the rocket and the DC source of ground equipment and electrical energy storage devices of safety-actuating mechanisms and time delay devices, while the inputs of all electric energy storage devices are connected through a broken wire communication line with the battery transport and launch container, as well as with the output of the voltage converter, the input of which is connected to one of the control coils the electromagnets of the steering drive unit, and the coils of the control electromagnets are connected to each other and to the output of the coil of the wire line, the input of which is connected through the transport and launch container to ground equipment.

The proposed technical solution allows to increase the operational characteristics of a guided missile by increasing the reliability and reducing the mass and dimensions of the missile by eliminating the on-board battery from the missile and introducing instead of it electric energy storage devices, an AC / DC converter and a disconnected wire line between the missile and the transport - a launch container, the reliability of which is higher than the reliability of the battery, and the mass and dimensions and significantly less weight and battery size.

The drawing shows a structural diagram of a guided missile and its connection with ground-based missile control equipment (NAU), which allows the method proposed by the authors to provide power to the onboard equipment of a guided missile and includes:

1. Electric energy storage of the safety-executive mechanism (PIM) of the additional warhead.

2. The safety-executive mechanism (PIM) of the additional warhead.

3. Electric energy storage of the safety-executive mechanism (PIM) of the main warhead.

4. The safety-executive mechanism (PIM) of the main warhead.

5. The electrical energy storage device of the electronic device time delay.

6. Electronic time delay device.

7. An interrupted wire communication line.

8. Battery transport and launch container.

9. Transport and launch container.

10. The converter of alternating voltage to direct voltage.

11. Steering gear unit with coils of control electromagnets.

12. Coil wire line.

13. Ground control equipment (NAU).

Examples of implementation of newly introduced elements

The AC to DC voltage converter is a half-wave voltage rectifier, combined with a voltage pulse limiter, converting pulse signals into a constant voltage, necessary for powering the rocket's onboard equipment.

An example of a voltage rectifier: “Secondary power sources”, “Radio and communications” publishing house, 1983, figure 6.4.

An example of a voltage pulse limiter: “Power supplies on semiconductor devices”, Sovetskoe Radio Publishing House, 1969, Figure 11.8a.

An interrupted wire communication line between the rocket and the transport and launch container is made, for example, in the form of two wires connecting the rocket to the battery of the transport and launch container, the length of which to the point of their break is chosen based on the time required for the accumulation of electrical energy on-board electrical energy storage rocket equipment from the battery of the transport launch container at the launch of the rocket, but not exceeding the start time of rocket control after its launch.

The electrical energy storage device is, for example, a capacitor.

The electronic time delay device consists of a multivibrator for creating a delay time that is triggered when the safety-actuating mechanism of the additional warhead is triggered, and an electronic key to ensure the operation of the safety-actuating mechanism of the main warhead after the delay time, performed on semiconductor circuits.

An example of a multivibrator: “Calculation and design of pulsed devices on transistors”, Sovetskoe Radio Publishing House, 1964, Figure 5.2.

An example of the implementation of an electronic key: “Guide to the basics of electronic technology”, Kiev University Press, 1972, Figure 12-30.

Known elements indicated in the restrictive part of the claims are similar to the prototype.

The components in the rocket are connected as follows.

The inputs of the electric energy storage device 1 of the additional warhead, the electric energy storage device 3 of the main warhead, the electric energy storage device 5 of the electronic delay device are connected via a broken wire communication line 7 to the battery 8 of the transport-launch container 9, as well as to the output of the AC / DC converter voltage 10, the input of which is connected to one of the coils of the control electromagnets of the steering unit 11, while the coils of the control electromagnets are connected s with each other and with the output of the coil wire link 12 having its input connected with the transport and launch container 9.

Providing power to the on-board equipment during launch and flight of a guided missile is as follows.

At launch, a guided missile flies out of the transport and launch container 9. Through a disconnected wire communication line 7, voltage from the battery 8 is supplied to electric energy storage devices 1, 3, 5 of the safety-actuating mechanisms of the main and additional warheads 2, 4 and the electronic time delay device 6 rockets. From the moment of the launch of the rocket and to the breakdown of the wireline 7, electric energy accumulates in electric energy storage devices 1, 3, 5 from battery 8 of the transport-launch container 9.

During the flight of the rocket from the ground-based rocket control equipment (NAU) 13, relay control signals are sent to the control coil electromagnets of the steering drive unit 11 through a transport and launch container 9 and a coil of a wireline 12 connected to it. A pulse current flows in the control coil electromagnets. When current flows in the coils of the control electromagnets, EMF pulses of self-induction occur, exceeding the magnitude of the voltage of the control signals. From one of the coils of the control electromagnets of the steering unit, the control signals and impulses of the self-induction EMF are fed to the input of the voltage transformer 10, where they are converted to constant voltage. From the output of the converter 10, a constant voltage is supplied to the inputs of the electric energy storage devices 1, 3, 5 to replenish the electric energy accumulated from the battery 8 of the transport and launch container 9 from them.

The electrical resistance of the coil of the wireline 12 and the coils of the control electromagnets of the steering unit 11 are selected so that the magnitude of the control signals taken from the coil of the control electromagnets and supplied to the input of the voltage converter 10 is equal to or less than the voltage stored on the drives 1, 3, 5 from battery 8 of the transport and launch container 9.

Therefore, the replenishment of electric energy on electric energy storage devices 1, 3, 5 occurs only from self-induction EMF pulses that occur when current flows in the coils of the control electromagnets of the steering unit 11, which does not affect the decrease in the energy of the control signals and, therefore, does not affect the control of the rocket .

The electric energy accumulated in drives 1, 3, 5 is supplied to the safety-actuating mechanisms 2, 4 of the main and additional warheads and the electronic time delay device 6 for their power supply during the flight of the guided missile

Sourse of information

1. “Equipment and weapons of the ground forces of the capitalist states”, publishing house “Central Research Institute of Information and Technical and Economic Research”, issue 20, 1988, pp. 3 ... 5.

Claims (2)

1. A method of providing power to an onboard equipment of a guided missile, characterized in that the process of providing power to an onboard equipment is divided into two phases, while in the first phase, electric energy is accumulated from the direct current source of the ground-based missile control equipment for the period from the moment the rocket starts to the wire break communication lines between the rocket and the direct current source of ground equipment, and in the second phase replenish the accumulated electric energy from the EMF pulses of self-induction Occurring in the coils of electromagnets control the missile steering drive unit under the influence of control signals applied from a ground control equipment for a missile during its flight. 2. Guided missile in a transport-launch container with a battery for powering ground-based missile control equipment, containing a coil of a wireline, a steering unit with coils of control electromagnets, safety-actuating mechanisms of the main and additional warheads, and a time delay device to ensure the main delay the warhead is relatively additional, characterized in that an AC to DC converter is introduced into it, breaking off a wired communication line between the rocket and a direct current source of ground equipment and electrical energy storage of safety-actuating mechanisms and time delay devices, while the inputs of all electric energy storage devices are connected through a broken wire communication line to the battery of the transport-launch container, as well as to the output of the voltage converter the input of which is connected to one of the coils of the control electromagnets of the steering unit, and the coils of the control electromagnets are connected ezhdu an output coil and a wireline input of which is connected via a transport and launch container with ground control equipment.