CN116222323A - A timing signal self-test system on launch vehicle - Google Patents

Abstract

The invention relates to a timing signal self-test system on a carrier rocket, comprising: a power supply module, a controller, an improved control mechanism and a timing tester; the improved control mechanism includes multiple control channels, and each control channel can The test state or the non-test state is switched, so that the improved control mechanism corresponds to the test state or the non-test state; the timing tester performs self-test on the arrow sequence when the improved control mechanism corresponds to the test state. The system and method for self-testing the timing signal on the carrier rocket of the present invention integrates the timing tester inside the carrier rocket, reduces ground testing equipment and process cables, simplifies the test process, realizes the self-testing of the timing signal on the arrow, and improves the automation level. By improving the control mechanism, integrating the short-circuit protection function of pyrotechnics and the test gating function of the tester, it meets the needs of self-testing on the arrow without adding other equipment on the arrow.

Description

A timing signal self-test system on launch vehicle

technical field

The invention belongs to the technical field of carrier rocket testing, and in particular relates to a self-testing system for timing signals on a carrier rocket.

Background technique

From before the official launch to the end of the flight, the launch vehicle will send out a large number of pyrotechnics signals and solenoid valve action signals. The pyrotechnic signal includes the ignition signal and the separation signal. According to the time sequence, it is specifically the first-level ignition, the first-level separation, the second-level ignition, the second-level separation, the third-level ignition, and the third-level separation. The solenoid valve action is the opening and closing signal. A signal that lasts for a certain length of time and can be sent repeatedly. In the various stages of testing of the launch vehicle before the official launch, the above-mentioned timing signals are generally checked to check whether they meet the design requirements. The key testing parameters are the signal sending time and signal duration. The common method is to set a hatch on the rocket body, or disconnect the controller on the rocket from the pyrotechnic device or solenoid valve when the rocket cabin is separated. Generally, the pyrotechnic device or solenoid valve needs to be short-circuited during the test. Use The adapter cable connects the interface on the arrow to the ground equipment (such as a timing equivalent device), and then uses a timing tester to test the timing signal on the arrow. There are many preparation steps and the process is cumbersome, which is no longer suitable for the rapid test launch of the launch vehicle. automation needs.

Contents of the invention

Aiming at the deficiencies of the prior art, in order to simplify the ground equipment and meet the needs of rapid testing of the launch vehicle timing signals (such as pyrotechnics signals, solenoid valve action signals, etc.), the present invention proposes a self-testing system for the launch vehicle timing signals.

In order to achieve the above object, the technical scheme provided by the invention is as follows:

A timing signal self-test system on a carrier rocket, said system is integrated on the rocket body, including a power supply module, a controller, an improved control mechanism and a timing tester;

The power supply module supplies power to other devices of the Arrow Sequence Self-Test System;

The controller includes a first communication module, a first main control module, and a timing signal output module, and the first communication module sends the command transmitted from the rocket communication bus to the first main control module. The first main control module parses the received command, and controls the timing signal output module to output the timing signal;

The improved control mechanism includes multiple control channels, and each control channel can be switched between a test state or a non-test state, so that the improved control mechanism corresponds to a test state or a non-test state;

The timing tester performs a self-test on the timing on the arrow when the improved control mechanism corresponds to the testing state.

Further, each control channel is switched between a test state or a non-test state, specifically including

Each of the control channels includes at least one group of connected channels and at least one group of short-circuit protection channels, and the group of connected channels and one group of short-circuit protection channels are switched according to the requirements of the test state or the non-test state, Thus, the improved regulatory mechanism corresponds to a testing state or a non-testing state.

Further, switching between the group of on-channels and a group of short-circuit protection channels specifically includes

Each control channel is provided with two pairs (groups) of reciprocating plugs, and the reciprocating motion of the plugs causes it to be mated or disconnected from the corresponding circuit board socket, so as to realize the corresponding test state or non-contact state of the improved control mechanism. Test state toggle.

Further, it also includes a tail section controller, which sends a test (entering the test state) command or a non-test (entering the non-test state) command to the improved control mechanism, so that the improved control mechanism switches correspondingly to test state or non-test state.

Further, the timing tester includes an isolated power supply module, a timing signal input module, a second main control module, and a communication module;

The isolated power module provides suitable power for other modules;

The second main control module includes peripheral circuits such as a main control chip and a storage circuit, and the second main control module receives information from the arrow communication bus through the communication module, and starts to collect timing signals or stops collecting timing signals; when timing When the signal is input, the input timing signal is measured and calculated, and the preliminary interpretation is performed according to the set parameters (including the timing and duration of the detected timing signal, as well as the deviation threshold), and the timing information parameters and interpretation results are coded according to the communication protocol. , sent to the rocket communication bus through the communication module, and finally sent back to the ground;

The timing signal input module includes an optocoupler, and the optocoupler plays an isolation role, and the voltage of the 28V voltage timing signal is shaped into a (3.3V) suitable voltage signal, which is input to the main control chip;

The communication module is driven by the second main control module to communicate with the rocket communication bus.

Further, the isolated power supply module includes an isolated DC/DC circuit and multiple voltage conversion circuits; the input, isolated DC/DC circuit is suitable for 9-36V input, and the output voltage of 12V can be converted to other voltages by multiple voltage conversion circuits. The input power supply of the module includes the 1.8V, 2.5V, 3.3V power supply of the main control module and the isolated power supply of the communication circuit.

Further, judgment logic is added to the tester software running on the main control module, and when the difference between the detected parameter and the set (measured) parameter exceeds a threshold, a warning message will be output.

On the other hand, the present invention provides a method for self-testing timing signals on a carrier rocket, which is characterized in that the self-testing system for timing signals on a carrier rocket according to claims 1-6 comprises the following steps:

When the rocket enters the timing self-test state process on the arrow, the tail section controller issues a timing self-test command, and the improved control mechanism performs short-circuit protection on the resistance circuit of the pyrotechnics, and conducts the output of the controller with the timing tester, so that the timing tester It can detect the controller output and record the timing status;

When the rocket enters the official launch process of the rocket, the tail section controller sends out the command of "entering the non-test state" for the official launch, and the improved control agency short-circuits the timing tester, and connects the output of the controller to the pyrotechnic device or solenoid valve. At this time The pyrotechnic device can ignite and detonate normally, and the solenoid valve can be opened normally.

Compared with the prior art, the above technical solutions conceived by the present invention can achieve the following beneficial effects:

The system and method for self-testing the timing signal on the carrier rocket of the present invention integrates the timing tester inside the carrier rocket, reduces ground testing equipment and process cables, simplifies the test process, realizes the self-testing of the timing signal on the arrow, and improves the automation level. By improving the control mechanism, integrating the short-circuit protection function of pyrotechnics and the test gating function of the tester, it meets the needs of self-testing on the arrow without adding other equipment on the arrow;

The input of the timing tester adopts the design of optocoupler multi-channel synchronous parallel input, which is rich in quantity, good in compatibility and versatility, and high in synchronization, and can synchronously collect multi-channel signals (for example, when the satellite and arrow are separated, multi-channel separated signals can be collected synchronously, etc.) , can be used as a modular device to meet the needs of different types of rockets and shorten the development time and cost.

Description of drawings

Fig. 1 is a schematic diagram of the system of the present invention;

Figure 2 is a schematic diagram of the test status and official launch status of the improved regulatory agency;

Fig. 3 is a schematic diagram of the structure of each control channel switching between the test state or the non-test state, that is, two sets of plug-in or disconnection channels are provided;

FIG. 4 is a schematic structural diagram of a timing tester;

FIG. 5 is a schematic diagram of an optocoupler input detection circuit.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

As shown in Figure 1, an embodiment of the present invention provides a self-test system for timing signals on a carrier rocket. The system is integrated on the rocket body, including a power supply module, at least one controller, and at least one improved control mechanism and timing The tester; the rocket in this example includes the first stage, the second stage, the third stage and the last stage, and each stage is equipped with a controller and an improved control mechanism correspondingly; it also includes the first, second stage, third stage and the last stage corresponding pyrotechnics or solenoid valves; when testing timing signals, it is necessary to short-circuit the pyrotechnics or solenoid valves, so that the timing signals can be tested in the timing tester after the improved control mechanism;

The power supply module supplies power to other devices of the on-arrow timing self-test system;

The power supply module uses the original power supply system of the rocket, which can provide energy for electrical equipment and pyrotechnics. It only adds power supply functions for new equipment in the timing self-test system on the rocket, such as timing testers and improved control agencies.

The controller includes a first communication module, a first main control module, and a timing signal output module. The first communication module sends the information transmitted from the rocket communication bus to the first main control module. The first The main control module compiles the received information into a timing signal, and controls the timing signal output module to output the timing signal. In the test state, the output timing signal passes through the improved control mechanism or enters the timing tester to complete the test of the timing signal; in the non-test state, the output timing signal passes through the improved control mechanism or enters the explosive device to make the explosive Ignite, or enter the solenoid valve to make the solenoid valve act; there are multiple controllers on the arrow, and generally adopt the principle of nearby control to be set in the compartments of each level; the timing signal output module of the controller, it will be in the setting At the time point, the ignition signal, the solenoid valve actuation signal, or the separation signal are sent.

The improved control mechanism is arranged between the controller and the pyrotechnics, and the timing signal is transmitted along the order of the controller, the improved control mechanism and the pyrotechnics. As shown in Figure 2, the improved control mechanism includes multiple control channels, and each control channel can be switched between a test state or a non-test state, so that the improved control mechanism corresponds to a test state or a non-test state; in this example The non-test state refers to the official launch state of the rocket; there are multiple improved control agencies, as shown in Figure 1, there are four improved control agencies; there are multiple channels in the improved control agency, so multiple solenoid valves or pyrotechnic timing can be used The same improved control mechanism, the principle of improving the arrangement of the control mechanism on the rocket is to avoid or reduce the impact on the timing signal cable as much as possible. It is required that all the timing signals pass through the improved control mechanism. Generally, the improved control mechanism is arranged on the original timing signal cable. on the path. The improved control mechanism in this example is improved on the basis of patent CN201010231660. The pyrotechnics control device of this patent includes a box body, a motor assembly, a circuit board assembly, a guide rod and an external connector. The motor assembly, circuit board Components and guide rods are accommodated in the box, the motor assembly includes a motor reduction mechanism, a fixing clip, a plug fixing plate and two plugs, the fixing clip fixes the motor reducing mechanism on the plug fixing plate, and the two The plug is installed on the plug fixing plate symmetrically to the fixing clip; the circuit board assembly includes a circuit board, a micro switch and two sockets, the circuit board is fixed on the bottom surface of the box body, and the two sockets are respectively welded symmetrically to the fixing clip On both sides of the circuit board, each corresponds to the plug on the same side; the external connector is electrically connected to the two sockets through the circuit board; when working, the motor reduction mechanism drives the entire motor assembly to reciprocate under the guidance of the guide rod, so that The two plugs are respectively mated with their corresponding sockets, so that the state of the pyrotechnic control circuit is changed between on and off, and the control of the signal in the pyrotechnic control circuit is realized; for the convenience of description, it is called In this patent, each control channel realizes that two plugs are respectively mated or disconnected with their corresponding sockets, which is a group of mated or disconnected channel structures. Each control channel of the improved control mechanism of this example is switched between the test state or the non-test state, that is, there are two sets of plug-in or disconnection channel structures, one of which makes the state of the pyrotechnics control circuit in the connection state. The other group makes the state of the sequence tester control line change between on and off; the specific implementation method includes: each control channel includes at least one group of on-channels and at least one group of The short-circuit protection channel, according to the requirements of the test state or the non-test state, switches a group of connection channels and a group of short-circuit protection channels, so that the improved control mechanism corresponds to the test state or the non-test state (that is, the official launch state of the rocket) ). The specific implementation method for switching between a group of connection channels and a group of short-circuit protection channels includes: each control channel is provided with two sets of reciprocating plugs, and the reciprocating motion of the plugs makes it mated with or disconnected from the corresponding circuit board socket , so as to realize the switching of the corresponding test state or non-test state of the improved control mechanism, as shown in Figure 3, the circle in the figure represents the pin, and the semi-circular arc represents the socket, and the two are combined (same center state-in the dotted line frame state) is the on state, otherwise it is the off state. After switching to the test state, the pyrotechnic product is short-circuited, and the timing tester is connected to the channel, so that the timing tester can detect the timing signal output by the controller and record the timing signal to complete the automatic test of the timing signal. After switching to the official launch state, the timing tester is short-circuited, so that the pyrotechnic device or solenoid valve can receive the launch signal output by the controller, and complete the ignition of the pyrotechnic device or the opening and closing of the solenoid valve. Correspondingly, structures such as motor components, circuit board components, and guide rods also need to be matched with two sets of reciprocating plugs and two sets of sockets, which are prior art and will not be repeated here.

The timing tester receives the timing signal sent by the controller and self-tests the timing signal on the arrow when improving the corresponding test state of the control agency.

As shown in Figure 4, the timing tester is a modular general-purpose device, including an isolated power supply module, a timing signal input module, a second main control module, and a communication module; the isolated power supply module includes an isolated DC/DC circuit and multiple A voltage conversion circuit, in which the isolated DC/DC circuit adapts to 9~36V input (for external power supply), and outputs 12V; the output 12V power supplies power to other modules through multiple voltage conversion circuits, for example, the main control module provides 1.8V, 2.5 V, 3.3V power supply and isolated power supply for communication circuits. The second main control module includes peripheral circuits such as the main control chip and storage circuit. The second main control module receives commands from the Arrow communication bus through the communication module, according to the set logic, such as timing: primary ignition, primary separation, secondary ignition , two-stage separation, three-stage ignition, three-stage separation, final stage ignition, final stage separation, etc., start or stop collecting timing signals; when timing signals are input, measure and calculate the collected timing signals, and The timing moment is compared with the duration length to preliminarily judge whether the error exceeds the set threshold, and the timing parameter information and interpretation results are encoded according to the communication protocol, sent to the rocket communication bus through the communication module, and then transmitted back to the ground control system. The timing signal input module includes an optocoupler. The optocoupler plays an isolation role and transforms the voltage of the 28V timing signal into a suitable voltage signal and sends it to the main control chip. It depends on the parameters of the main control chip. In this example, it is 3.3V. ; As shown in Figure 5, it is an optocoupler input detection circuit. The optocoupler itself has an isolation function and does not need an isolated power supply, which can greatly simplify the number and types of electronic components; the output signal of the optocoupler only depends on whether there is current flowing through the pre-circuit, and no uncertain signal will be generated when the input terminal is suspended. It can effectively adapt to the situation where the input terminal is suspended or the level difference of the input terminal is low level, and it can adapt to the situation of positive terminal control, negative terminal control and two-terminal control of the signal output circuit; the input terminals between optocouplers can be isolated from each other, which can effectively adapt to the input The signal common positive or the input signal common negative.

The communication module is driven by the second main control module to communicate with the rocket communication bus.

For example, when the time difference between the actual sending time of the time sequence and the preset sending time exceeds the threshold 1s, or when the difference between the actual holding time of the time sequence and the preset holding time exceeds the threshold 1s, it is judged that the time sequence is wrong and an alarm message is output; the original ground test scheme Without binding this judgment logic, only manual interpretation can be performed.

As an example, the system of the present invention further includes a tail section controller, which sends a test signal or a non-test signal to the improved control mechanism, so that the improved control mechanism corresponds to the test state or the non-test state. In the example, the non-test signal is the official launch signal of the rocket.

On the other hand, the present invention provides a method for self-testing timing signals on a carrier rocket, using the aforementioned self-testing system for timing signals on a carrier rocket, comprising the following steps:

When the rocket enters the timing self-test process on the rocket, the tail section controller issues a timing self-test command to short-circuit the resistance circuit of the pyrotechnics, and conducts the controller output with the timing tester, so that the timing tester can test the controller Output, record timing status;

When the rocket enters the official launch process of the rocket, the tail section controller sends out a formal launch, that is, a non-test signal command, short-circuits the timing tester, and connects the output of the controller to the pyrotechnic device or solenoid valve. At this time, the pyrotechnic device can ignite normally. Detonation, solenoid valve can be opened normally.

Claims (8)

1. The system is characterized by being integrated on a rocket body, comprising a power supply module, a controller and an improved control mechanism and a timing tester;

the power supply module supplies power to other devices of the on-arrow time sequence self-test system;

the controller comprises a first communication module, a first main control module and a time sequence signal output module, wherein the first communication module receives a command transmitted by a rocket communication bus and then sends the command to the first main control module, and the first main control module analyzes the received command and controls the time sequence signal output module to output a time sequence signal;

the improved control mechanism comprises a plurality of control channels, and each control channel can be switched between a test state and a non-test state, so that the improved control mechanism corresponds to the test state or the non-test state;

the time sequence tester performs self-test on the time sequence on the arrow when the improved control mechanism corresponds to the test state.

2. The system of claim 1, wherein each of the plurality of control channels is configured to switch between a test state and a non-test state, and comprises

Each path of control channel comprises at least one group of connection channels and at least one group of short-circuit protection channels, and the group of connection channels and the group of short-circuit protection channels are switched according to the requirements of the test state or the non-test state, so that the improved control mechanism corresponds to the test state or the non-test state.

3. The system for self-testing time sequence signals on rocket of claim 2, wherein said switching between said set of on-channels and said set of short-circuit protection channels comprises

Each path of control channel is provided with two groups of plugs capable of reciprocating, and the plugs can be connected with or disconnected from the corresponding circuit board sockets in a reciprocating mode, so that the switching of the corresponding test state or the non-test state of the improved control mechanism is realized.

4. The system of claim 1 or 2, further comprising a tail section controller, wherein the tail section controller issues a command to enter a test state or a command to enter a non-test state to be input to the improved regulatory agency, such that the improved regulatory agency switches to a test state or a non-test state, respectively.

5. The self-test system for the time sequence signal on the rocket of claim 3, wherein the time sequence tester comprises an isolated power supply module, a time sequence signal input module, a second main control module and a communication module;

the isolated power supply module provides proper power supply for other modules;

the second main control module comprises a main control chip and a peripheral circuit, and receives information from an arrow communication bus through the communication module to start or stop collecting time sequence signals; when a time sequence signal is input, measuring and calculating the input time sequence signal, performing preliminary interpretation according to set parameters, encoding time sequence information parameters and interpretation results according to a communication protocol, and transmitting the time sequence information parameters and interpretation results to a rocket communication bus through a communication module;

the time sequence signal input module comprises an optical coupler which plays an isolating role, and the voltage of the 28V voltage time sequence signal is shaped into a proper voltage signal and is input to the main control chip;

and the communication module is driven by the second main control module to communicate with the rocket communication bus.

6. The on-rocket timing signal self-test system according to claim 1, wherein the isolated power module comprises an isolated DC/DC circuit and a plurality of voltage conversion circuits; the input and isolation DC/DC circuit is suitable for 9-36V input, and the output 12V voltage can be converted into the input power supply of other modules through a plurality of voltage conversion circuits, and the input power supply comprises 1.8V, 2.5V and 3.3V power supply of the main control module and isolation power supply of the communication circuit.

7. The system of claim 1, wherein the test logic is configured to add a decision logic to the tester software running on the main control module, and to output a warning message when the difference between the detected parameter and the set parameter exceeds a threshold.

8. A method for self-testing time sequence on a carrier rocket, characterized in that the method for self-testing time sequence signals on a carrier rocket according to claims 1-6 comprises the following steps:

when the rocket enters the rocket-mounted time sequence self-test state flow, the tail section controller sends a time sequence self-test instruction, the control mechanism is improved to perform short-circuit protection on the initiating explosive device resistance loop, the controller output is conducted with the time sequence tester, the time sequence tester can detect the controller output, and the time sequence state is recorded;

when the rocket enters a rocket formal launching process, the tail section controller sends out a formal launching, namely a command of 'entering a non-test state', the improved control mechanism shorts the time sequence tester, the output of the controller is communicated with an initiating explosive device or an electromagnetic valve, and at the moment, the initiating explosive device can be normally ignited to detonate and the electromagnetic valve can be normally opened.

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