EA038871B1 - Onboard system for missile simulator launch - Google Patents

Abstract

The onboard system for missile simulator launch contains a control unit, a primary power source connected to the control unit, an input unit designed to deliver a signal of launch to the control unit, a switching element connected to the outlet of the control unit and configured to receive a control signal from the control unit, an additional power source connected to the switching element, engine start device connected to the output of the switching element; at this time, the control unit is designed to deliver a control signal to the principal switching element after the first preset time interval, as soon as the start signal is received from the input unit; the switching element is designed to supply power from the additional power source to the engine start device, as soon as the control signal is received from the control unit.

Description

The technical field to which the invention relates

The present invention relates to a means of launching model missiles, and more specifically to an on-board launch system for a model missile, and can be used to create models of missiles with an integrated (on-board) launch system.

State of the art

A device for launching a rocket model is known from the prior art (P. Elshtein, Designer of rocket models, Moscow: MIR, 1978, p. 319, section 1. Electrical ignition systems, p. 150), containing a control unit and an electric igniter connected by a wire connection. The control unit is configured to supply a control signal, for example, supply voltage to the electric igniter when receiving input from the user, for example, when pressing the start button, or at a predetermined time interval after receiving input from the user. Since the known launching device is a separate element, it requires separate deployment and relatively complex preparation, performed immediately prior to launch, when the model rocket is mounted on the launch pad. In addition, the wires connecting the control unit and the electric igniter can be of considerable length, which is due to safety requirements during start-up, and therefore the known device, when assembled, takes up a relatively large amount of space. Thus, the disadvantages of the known model rocket launcher are the inconveniences of storage, transportation, deployment and preparation for launch.

The essence of the invention

The present invention is based on the task of creating an on-board system for launching a rocket model, which does not require complex preparation before launching.

The specified problem is solved by creating an on-board launch system for a rocket model containing a control unit, a main power source connected to the control unit, an input unit configured to send a start signal to the control unit, a switching element connected to the output of the control unit and configured to receive the signal control from the control unit, an additional power supply connected to the switching element, an engine starting device connected to the output of the switching element, while the control unit is configured to supply a control signal to the main switching element in the first predetermined time interval after receiving a start signal from the input unit , the switching element is configured to supply power from an additional power source to the engine starting device upon receiving a control signal from the control unit.

Preferably, the engine starting device is an electric igniter.

Preferably, the on-board system further comprises an additional switching element connected to the additional power source and to the output of the control unit, an actuator of the parachute release system of the rocket model connected to the additional switching element, while the control unit is configured to supply a control signal to the additional switching element through the second a predetermined time interval after the control signal is applied to the switching element.

Preferably, the on-board system further comprises a memory unit configured to read memory cards and connected to the control unit, a set of sensors containing a sensor selected from the group consisting of a pressure sensor, a gyro sensor, a GPS module, an accelerometer, a magnetic compass, an airspeed sensor, an additional an input unit configured to supply a check signal to the control unit, an indication unit connected to the control unit, the control unit configured to read data from at least one sensor of said set of sensors and write said data to the memory unit;

determine when receiving a check signal from the additional input unit, whether the memory unit is ready to write data; and, if it is determined that the memory unit is not ready to write data, outputting a control signal to the display unit instructing the display unit to indicate the presence of an error.

Preferably, the display unit is an RGB LED, whereby the presence of an error is signaled by the display unit by lighting up in red.

The achieved technical result is that the proposed onboard system for launching a rocket model does not require complex preparation before launching.

Brief Description of Drawings

The invention is further illustrated by the description of preferred embodiments with

- 1 038871 with reference to the accompanying drawings, in which: FIG. 1 is a structural diagram of an on-board launching system of a rocket model according to a first embodiment;

in fig. 2 is a structural diagram of an on-board launching system of a rocket model according to a second embodiment;

in fig. 3 is a block diagram of an airborne launching system of a model rocket according to a third embodiment;

in fig. 4 is a flowchart of a control algorithm of a control unit according to the first embodiment;

in fig. 5 is a flowchart of a control algorithm of a control unit according to a second embodiment;

in fig. 6 is a flowchart of a control flow of a control unit according to a third embodiment.

Description of preferred embodiments of the invention

The essence of the claimed invention is disclosed in detail in the following description of specific embodiments of the invention.

Embodiment 1

In a first embodiment, the on-board launching system of a model rocket, the diagram of which is shown in FIG. 1, contains a control unit 1, a main power supply 2, an additional power supply 3, a switching element 4, an engine starting device 5 and an input unit 6.

Control unit 1 is an Arduino Nano debug board containing a microcontroller on which the control program is written. The control unit 1 receives electrical power from the main power supply 2. The elements connected to the microcontroller are connected to it through the pins of the Arduino Nano debug board. The elements connected to the microcontroller are powered from the main power supply and can be connected to it through the pins of the Arduino Nano debug board.

The switching element 4 is, for example, a normally open relay controlled by a microcontroller. Upon receiving a control signal from the microcontroller, the relay supplies voltage from an additional power source to the engine starting device 5. Since the electromagnet of a conventional relay consumes a significant amount of current and cannot be controlled using the logic output signal of the microcontroller directly, the actuation control of the relay can be carried out using an intermediate transistor. It is preferable to use a relay module for the Arduino platform, ready to be connected to the power pins and logic pin of the Arduino Nano debug board. Alternatively, a transistor such as a field effect transistor can be used as the switching element.

The engine starting device 5 provides ignition of the engine fuel charge and can be made, for example, in the form of an electric igniter, which is located on the model rocket so that it contacts the engine wick, or directly with the pyrotechnic composition of the engine fuel of the rocket model. When voltage is applied to the electric igniter, the latter ignites and starts the engine of the rocket model. The electric igniter is connected with wires to the circuit formed by the electric igniter, an additional power source and a relay, so that when the relay contacts are closed, when it is triggered, voltage is supplied from the additional power source 3 to the electric igniter.

As the main and additional power sources 2, 3, conventional chemical batteries, for example, rechargeable batteries, can be used. In this case, as an additional power source 3, a power source is selected that provides sufficient power (current) for the engine starting device to operate. During storage and transportation of the rocket model equipped with the proposed onboard launch system, power sources 2, 3 are disconnected from the onboard launch system and are preferably stored separately. The power supplies are connected to the onboard launch system using connectors (not shown) in advance of or just prior to launch. In this case, the power sources can be connected to the onboard launch system through one (two-channel) or two (one for the main and additional power source) power supply switches (not shown), which provide the ability to easily turn on / off the power supply to the onboard launch system of the rocket model ...

The use of two separate power supplies 2, 3 is due to the need to provide, on the one hand, a stable supply voltage for the control unit 1 and, on the other hand, power supply with a large maximum current, but not necessarily with a stable voltage, for the engine starting device 5 and others. executive devices.

The input unit 6 can be a button (start button) connected to the microcontroller and providing a start signal to the logic input of the microcontroller when pressed.

The starting system according to the first embodiment operates as follows.

The rocket model is installed on the launch pad. Then power supplies 2, 3 are connected to

- 2 038871 onboard starting system by connecting them using connectors or by turning on one or more power supply switches.

When power is applied to the control unit 1, the control unit turns on and, according to the specified control program, goes to the stage of waiting for a signal (start signal) to be received from the input unit 6 (Fig. 4, unit Is there a signal from the start button?).

Upon receipt of a signal from the input unit 6, namely when the user presses the start button, the start process is initiated, and the control unit 1 proceeds to the step of counting a predetermined time interval (the first predetermined time interval); for example 60 s (Fig. 4, block Start of a given time interval).

After the expiration of a predetermined time interval (Fig. 4, has the Specified time interval passed?), The control unit 1 proceeds to the starting stage (Fig. 4, the Start command issuing block), in which the control unit 1 supplies a control signal to the main switching element, as a result of which the voltage from the additional power source is supplied to the engine starting device 5. Upon activation of the engine launcher, the pyrotechnic fuel composition of the model rocket engine is ignited and the model rocket is launched.

Thus, to launch a rocket model using the proposed on-board launch system, only installation on the launch pad, connection of power supplies and pressing of the launch button is required. This will eliminate the stages of deployment and preparation of a separate external device for launching a rocket model.

Embodiment 2

One of the key structural elements of most rocket models is the model rocket rescue system, which ensures the accident-free return (descent) of the rocket model after launch. As such a system, a parachute release system is often used, which contains at least a control unit, a parachute release actuator and a parachute. The parachute release system provides the release of the parachute under specified conditions after the launch of the rocket model, for example, after a specified time interval after launch, upon reaching the maximum flight altitude, etc. The parachute is placed in the body of the rocket model (as a rule, in the upper part of the rocket model under the nose fairing). The parachute release actuator can be, for example, an expelling charge with an electric igniter, a worm-gear parachute ejection mechanism driven by an electric motor, a spring mechanism driven by a servo drive.

In the second embodiment of the on-board launching system of the model rocket (Fig. 2), the control unit 1 of the launching system of the model rocket is configured to activate the actuator 7 of the parachute release system. In this case, the launch system contains an additional switching element 8, similar to the already mentioned main switching element 4. The additional switching element 8 provides voltage supply from an additional power source to the actuator 7 of the parachute release system upon receipt of a control signal from the control unit.

According to the second embodiment, after the launch of the rocket model (Fig. 5, block Launch command), the control unit of the launch system goes to the step of counting a predetermined interval of time for releasing the parachute (second predetermined interval of time; Fig. 5, block Starting the count of the second predetermined interval of time ), and upon the expiration of the mentioned time interval (Fig. 5, the block The second predetermined time interval has passed?) issues a control signal to the additional switching element (Fig. 5, the Issue command to release the parachute block).

The additional switching element 8 is triggered and provides power supply from the additional power source 3 to the actuator 7 of the parachute release system. In this case, the mentioned time interval can be, for example, equal to the estimated time for the rocket model to reach its maximum flight altitude. The parachute release system actuator is triggered and provides the release of the parachute and the safe return (descent) of the rocket model.

Thus, in the second embodiment, the launch system additionally performs the function of controlling the rescue system of the rocket model.

Embodiment 3

The purpose of launching model rockets is often to collect flight data from onboard sensors of the model rocket, which is written to a data recording and storage medium (memory unit), such as an SD card, using a memory card reader. In this case, the launch of the rocket model is undesirable if the data recording and storage facility is not ready for operation, for example, due to a connection error, an error in the file system of the memory card, no memory card, lack of free space on the memory card, and there is a need for the possibility checking the readiness for operation of the data recording and storage facility by restarting.

In the third embodiment, the on-board launch system of the rocket model further comprises a set of 9 sensors, a memory unit 10, a second input unit 11 and an indication unit 12 connected to the control unit 1. The input unit 6 is similar to the input unit of the first and second embodiments.

A set of 9 sensors represents one or more sensors connected to block 1

- 3 038871 management. An example of sensors can be: pressure sensor, gyro sensor, accelerometer, GPS module, magnetic compass, airspeed sensor, etc. FIG. 3 is a diagram illustrating an on-board launch system of a model rocket according to the present embodiment, by way of example, the sensor array contains only a gyro sensor.

The memory unit 10 may be, for example, a memory card reader with a memory card inserted therein.

The additional input unit 11 can be a button connected to the microcontroller and providing a check signal to the logic input of the microcontroller when pressed.

The display unit 12 in the third embodiment is intended to indicate, in one way or another, the state of the memory unit. The display unit 12 may be, for example, an LED, in particular an RGB LED, a sound emitter, a display, or the like.

Next, a case is considered where the additional input unit 11 is a button (test button), the memory unit 10 is a memory card reader, and the display unit 12 is an RGB LED.

The system according to the third embodiment operates as follows.

When power is connected to the control unit 1 of the starting system, the control unit goes to the stage of waiting for a signal from the input unit 6 (start signal) or from the additional input unit 11 (check signal; Fig. 6, blocks Is there a signal from the check button ?, Is there signal from the start button?).

Upon receipt of the input signal from the input unit 6 (when the start button is pressed), the triggering system executes a triggering algorithm similar to the triggering algorithm according to the first or second embodiment. The launch algorithm according to the third embodiment may comprise additional steps of obtaining data (flight data) from sensors and writing this data to a memory unit.

When a signal is received from the additional input unit 11 (when the test button is pressed), the control unit proceeds to the stage of checking the readiness of the memory unit for data recording (Fig. 6, the unit Checking the readiness for operation of the memory unit).

Further, in the event that it is determined that the memory unit 10 is not ready to write data, for example, if an error occurs when trying to access the memory unit, the control unit 1 instructs the display unit 12 to carry out the corresponding indication (Fig. 6, command issuing unit error indication). For example, it sends a command to illuminate in red to a controlled RBG LED. Next, the control unit 1 returns to the input waiting stage.

If, at the stage of checking the readiness of the memory unit 10 for data recording, it is determined that the recording unit is ready to write data, the control unit 1 instructs the display unit 12 to carry out the corresponding indication (Fig. 6, unit for issuing a readiness indication command). For example, it sends a green light command to a controlled RBG LED. Next, the control unit 1 returns to the input waiting stage.

Thus, the launch system according to the present embodiment provides an additional opportunity to check the state of the data recording unit before launching the rocket model, and the user can refuse to launch the rocket model in order to avoid the loss of flight data if the check reveals that the recording unit is not ready for operation.

Claims (5)

CLAIM 1. On-board launch system of the rocket model, containing a control unit, a main power source connected to the control unit, an input unit configured to send a start signal to the control unit, a switching element connected to the output of the control unit and configured to receive a control signal from the unit control, an additional power supply connected to the switching element, an engine starting device connected to the output of the switching element, while the control unit is configured to supply a control signal to the main switching element at a first predetermined time interval after receiving a start signal from the input unit, the switching element is configured to supply power from an additional power source to the engine starting device upon receipt of a control signal from the control unit. 2. The on-board system of claim 1, wherein the engine starting device is an electric igniter. 3. The on-board system according to claim 1, further comprising an additional switching element connected to an additional power source and to the output of the control unit, an actuator of the parachute release system of the rocket model, connected to an additional switching element, while - 4 038871 the control unit is configured to supply a control signal to the additional switching element at a second predetermined time interval after the control signal is supplied to the switching element. 4. The on-board system according to claim 1, further comprising a memory unit configured for reading memory cards and connected to the control unit, a set of sensors containing a sensor selected from the group consisting of a pressure sensor, a gyro sensor, a GPS module, an accelerometer, a magnetic compass , an air speed sensor, an additional input unit configured to send a check signal to the control unit, an indication unit connected to the control unit, while the control unit is configured to read data from at least one sensor of the specified set of sensors and write said data to the unit memory; determine when receiving a check signal from the additional input unit, whether the memory unit is ready to write data; and, if it is determined that the memory unit is not ready to write data, outputting a control signal to the display unit instructing the display unit to indicate the presence of an error. 5. The on-board system according to claim 4, in which the display unit is an RGB LED, and the presence of an error is signaled by the display unit by lighting up in red.