RU96646U1 - DEVICE FOR SELF-ELIMINATION OF ROCKETS - Google Patents

Abstract

 A device for self-liquidating a rocket containing a switching device, an electric detonator of an elimination unit, an input bus, first, second and third trajectory sensors, the output of the switching device connected to the input of the first trajectory sensor, the output of which is connected to the input of the electric detonator, the second input of the switching device is connected to the output of the second trajectory sensor, characterized in that it is equipped with an energy storage device, a constant time delay device, a fourth time programming sensor, device The switching property is made in the form of a device for the formation of protection and switching stages, incoming signals to the elimination unit, the first input of which is connected to the output of the energy storage device, the third input - with the output of the third path sensor, and the fourth input - with the output of the fourth time programming sensor, the first path the sensor is a pressure signaling device, the second and third trajectory sensors are parallel to each other, the input of the device for forming the protection and switching stages, the incoming signal s to the elimination unit, connected to the input bus, a constant time delay device is located in the device for forming the protection and switching stages, incoming signals to the elimination unit.

Description

The utility model relates to rocket technology, namely to control systems and can be used for self-liquidation of missiles in critical situations, and is aimed at improving self-destruction systems. The utility model is designed to implement the stages of protection and the formation of a liquidation team for actuators and can find application in rocketry.

Currently known device for self-destruction of a rocket containing two power sources, two electric detonators, two sensors, a control unit, a state switching device, a control bus and an input bus. The sensors are made in the form of trajectory sensors, the inputs of which are connected to the first output of the state switching device and the output of the first power source. The outputs of the sensors are connected to the input of the first electric detonator and the first input of the state switching device, the control input of which is connected to the control bus. The second output of the state switching device is connected to the input of the second electric detonator. The second input of the state switching device is connected to the output of the control unit, the control input of which is connected to the input bus, and the input is connected to the output of the second power source (see Russian patent No. 2316722, F42C 9/00 07/11/2006). This technical solution has the following disadvantages. Limited functionality. The impossibility of self-destruction of a rocket in the event of an abnormal shutdown of the power source, since in this case the device for self-destruction is in an unused state.

The closest to the proposed utility model in terms of the set of essential features, in terms of technical nature and the achieved technical result are a device for self-liquidation of a rocket. The device contains a power source, an electric detonator, which is part of the elimination device, a first trajectory sensor, a control unit, a state switching device, a second and third trajectory sensors, an input bus and a control bus. The output of the power source is connected to the input of the control unit, to the control input of which an input bus is connected, and the output of which is connected to the first input of the state switching device. The control input of the state switching device is connected to the control bus, the second input through series-connected trajectory sensors to the output of the power source. The first output of the state switching device is connected to the input of the path sensor, the output of which is connected to the second output of the state switching device and the input of the electric detonator, which is part of the elimination device (see patent RU No. 2343399, F42C 9/00, 05/14/2007). This device has disadvantages. Limited functionality. The impossibility of self-destruction of a rocket in the event of an abnormal shutdown of the power source, since in this case the device for self-destruction is in an unused state. There is also no time limit for work and it is impossible to achieve a safe speed, which leads to a decrease in missile safety during elimination.

The utility model is aimed at achieving a technical result, namely, expanding the functionality and increasing safety during the self-destruction of a rocket, both during regular and abnormal launch. The presence of an energy storage device allows, without the use of an autonomous power source, to ensure the liquidation of a rocket in the event of an on-board power failure. The time programming sensor limits the time of work, which allows you to automatically limit the radius of the rocket when launching the rocket at a limited size range (the size of the range is much less than the range of the rocket). The device for the formation of protection and switching stages, incoming signals to the liquidation unit and the first sensor, which is a pressure signaling device, increase the reliability and safety of operation.

The specified technical result is achieved by the fact that the device for self-liquidation of the rocket containing the switching device, the electric detonator of the liquidation unit, the input bus, the first, second and third trajectory sensors, the output of the switching device is connected to the input of the first trajectory sensor, the output of which is connected to the input of the detonator, the second input the switching device is connected to the output of the second trajectory sensor, equipped with an energy storage device, a constant time delay device, and a fourth prog sensor ammirovaniya time. The switching device is made in the form of a device for the formation of protection and switching stages, incoming signals to the elimination unit, the first input of which is connected to the output of the energy storage device, the third input - with the output of the third path sensor, and the fourth input - with the output of the fourth time programming sensor. The first trajectory sensor is a pressure indicator, the second and third trajectory sensors are parallel to each other. The input of the device for the formation of protection and switching stages, incoming signals to the elimination unit, is connected to the input bus. A constant time delay device is located in the device for the formation of protection and switching stages, incoming signals to the elimination unit.

Thanks to this embodiment of the device, three levels of protection are provided:

- self-liquidation is impossible before the start in the absence of on-board power,

- the ability to achieve a safe speed, as there is a signal from the pressure switch,

- from the moment of start, the self-liquidation signal does not turn on as a result of the presence of a device with a constant time delay of 20 seconds.

In FIG. depicts a structural diagram of a device for self-destruction of a rocket.

A device for self-liquidation of a rocket contains a switching device 1, an electric detonator 2, which is part of the liquidation unit 3, an input bus 4. It also contains the first 5, second 6, and third 7 trajectory sensors. Switching device 1 is made in the form of a device for forming the protection and switching stages, incoming signals to the elimination unit 3. Also, the device for self-liquidation of the rocket is equipped with an energy storage device 8, a constant time delay device 9, and a fourth time programming sensor 10. The output of the device for forming the protection and switching stages of the incoming signals 1 to the elimination unit 3 is connected to the input of the first 5 trajectory sensor, the output of which is connected to the input of the electric detonator 2 of the elimination unit 3. Pe The first trajectory sensor 5 is a pressure indicator. The first input of the device for forming the protection and switching stages, the incoming signals 1 to the elimination unit 3 is connected to the output of the energy storage device 8, the second input to the output of the second trajectory sensor 6, the third input to the output of the third trajectory sensor 7, and the fourth input to the output fourth time programming sensor 10. Second 6 and third 7 path sensors are parallel to each other. The input of the device for forming the stages of protection and switching, incoming signals 1 to the elimination unit 3 is connected to the input bus 4. The device for the constant time delay 9 is located in the device for forming the stages of protection and switching, incoming signals 1 to the elimination unit 3.

As an electric detonator 2 of the liquidation unit 3, an electric detonator ED-1-U can be used.

As a device for forming the stages of protection and switching, the incoming signals 1 to the elimination unit 3, the memory and switching element can be used, made on polarized relays of the RPS type and time relay of the RVE type.

As the first trajectory sensor 5, a pressure switch of type 2CC can be used.

As the second trajectory sensor 6, a gyroscopic course limiter of the OKG type can be used.

As a third trajectory sensor 7, a gyroscope of the GSI type can be used.

As a device for storing energy 8 can be used capacitive storage based on capacitors.

As a device for a constant time delay 9, an electronic relay of the RVE type can be used.

As the fourth time programming sensor 10, a device of the UVMP1 type can be used.

The proposed device for self-destruction of a rocket works as follows. A stabilized autonomous flight of a target rocket follows a predetermined path. The device begins to work at the moment of rocket launch. At the same time, in the device for forming the protection and switching stages of incoming signals 1, the constant time delay device 9 is turned on, the fourth time programming sensor 10 starts working and the energy storage device 8 is charged, which provides one of the protection stages. In the process of operation of the constant time delay device 9, signals from the second trajectory sensor 6 and the third trajectory sensor 7 and commands from an external source on the input bus 4 are not fixed. The triggering of the first path sensor 5 is remembered and this ensures the second stage of protection against premature elimination.

After the end of the device, the constant time delay 9, which provides the third stage of protection, the input bus 4 of the device forming the stages of protection and switching of incoming signals 1 is connected to the electric detonator 2 of the elimination unit 3.

After that, in a regular launch, the rocket is eliminated when the fourth time programming sensor 10 is triggered or when an external command (for example, via a radio line) arrives at the input bus 4.

During an abnormal start-up after the formation of all protection stages by the device for forming the protection and switching stages, incoming signals 1 when a signal is received from the second trajectory sensor 6 or from the third trajectory sensor 7 or when an external command is received on the input bus 4 of the device for forming the protection and switching stages, incoming signals 1, the electric detonator 2 of the elimination unit 3 is triggered.

The same thing happens when the on-board power supply fails, while the energy storage device 8 is connected to the electric detonator 2 of the liquidation unit 3.

Thanks to this embodiment of the device provides:

- expanding the functionality and increasing safety during the self-liquidation of a rocket, both during regular and abnormal launch. The presence of an energy storage device 8 allows for the liquidation of a rocket in the event of a loss of on-board power. The fourth time programming sensor 10 limits the time operation. The device for the formation of protection and switching stages, the incoming signals 1 to the elimination unit 3 is combined with a constant time delay device 9.

This provides:

- the impossibility of self-liquidation before the start, since there is no on-board food,

- the ability to achieve a safe speed, as there is a signal from the pressure switch,

- there is no inclusion of the self-destruction signal as a result of the presence of a constant time delay of 20 seconds.

Claims (1)

A device for self-liquidating a rocket containing a switching device, an electric detonator of an elimination unit, an input bus, first, second and third trajectory sensors, the output of the switching device connected to the input of the first trajectory sensor, the output of which is connected to the input of the electric detonator, the second input of the switching device is connected to the output of the second trajectory sensor, characterized in that it is equipped with an energy storage device, a constant time delay device, a fourth time programming sensor, device The switching property is made in the form of a device for the formation of protection and switching stages, incoming signals to the elimination unit, the first input of which is connected to the output of the energy storage device, the third input - with the output of the third path sensor, and the fourth input - with the output of the fourth time programming sensor, the first path the sensor is a pressure signaling device, the second and third trajectory sensors are parallel to each other, the input of the device for forming the protection and switching stages, the incoming signal s to the elimination unit, connected to the input bus, a constant time delay device is located in the device for forming the protection and switching stages, incoming signals to the elimination unit.