A timing signal self-test system on a launch vehicle

Abstract

The present invention relates to a self-test system for timing signals on a carrier rocket, comprising: a power module, a controller, an improved control mechanism and a timing tester; the improved control mechanism comprises multiple control channels, each of which 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 onboard timing when the improved control mechanism corresponds to the test state. The self-test system and method for timing signals on a carrier rocket of the present invention integrates the timing tester inside the carrier rocket, reduces ground test equipment and process cables, simplifies the test process, realizes onboard self-test of timing signals, and improves the level of automation. By improving the control mechanism, integrating the short-circuit protection function of pyrotechnics and the test gating function of the tester, the demand for onboard self-test is met while ensuring safety and without adding other onboard equipment.

Description

Technical Field

[0001] The invention belongs to the technical field of launch vehicle testing, and in particular relates to a timing signal self-test system on a launch vehicle. Background Art

[0002] From before the official launch to the end of the flight, the launch vehicle will send out a large number of pyrotechnic signals and solenoid valve action signals. Pyrotechnic signals include ignition signals and separation signals, which are specifically first-stage ignition, first-stage separation, second-stage ignition, second-stage separation, third-stage ignition, third-stage separation, etc. in chronological order; the solenoid valve action, that is, the opening and closing signal, is a signal that lasts for a certain length of time and can be sent repeatedly. In the various stage tests before the official launch of the launch vehicle, the above-mentioned timing signals are generally checked to detect whether they meet the design requirements, and the key detection parameters are the signal issuance time and signal duration. The common method is to set a hatch on the rocket body, or disconnect the connection between the on-rocket controller and the pyrotechnic or solenoid valve when the rocket compartment is separated. Generally, the pyrotechnic or solenoid valve needs to be short-circuited during the test, and the on-rocket interface and the ground equipment (such as the timing equivalent device) are tested and connected using an adapter cable, and then the on-rocket timing signal is tested using a timing tester. There are many preparation steps and the process is cumbersome, which no longer meets the automation requirements of the rapid test launch of the launch vehicle. Summary of the invention

[0003] In view of the shortcomings of the prior art, in order to simplify ground equipment and meet the needs of rapid testing of launch vehicle timing signals (such as pyrotechnic signals, solenoid valve action signals, etc.), the present invention proposes a launch vehicle onboard timing signal self-test system.

[0004] To achieve the above purpose, the technical solution provided by the present invention is as follows:

[0005] A timing signal self-test system on a carrier rocket, the system is integrated on the rocket body, and includes a power module, a controller, an improved control mechanism, and a timing tester;

[0006] The power supply module supplies power to other devices of the on-arrow timing self-test system;

[0007] The controller includes a first communication module, a first main control module, and a timing signal output module. The first communication module receives a command transmitted from the rocket communication bus and sends it to the first main control module. The first main control module parses the received command and controls the timing signal output module to output a timing signal.

[0008] The improved control mechanism includes multiple control channels, each of which can be switched between a test state and a non-test state, so that the improved control mechanism corresponds to a test state or a non-test state;

[0009] The timing tester performs a self-test on the timing on the arrow when the improved control mechanism corresponds to the test state.

[0010] Furthermore, each control channel is switched between a test state and a non-test state, specifically including:

[0011] Each of the control channels includes at least one group of connection channels and at least one group of short-circuit protection channels. According to the requirements for the test state or the non-test state, the group of connection channels and the group of short-circuit protection channels are switched, so that the improved control mechanism corresponds to the test state or the non-test state.

[0012] Furthermore, the switching of the set of connection channels and the set of short-circuit protection channels specifically includes:

[0013] Each control channel is provided with two pairs (groups) of reciprocating plugs, and the reciprocating movement of the plugs enables them to be plugged in or disconnected with the corresponding circuit board sockets, thereby realizing the switching of the improved control mechanism to the corresponding test state or non-test state.

[0014] Furthermore, it also includes a tail section controller, which issues a test (entering a test state) command or a non-test (entering a non-test state) command to the improved control mechanism, so that the improved control mechanism switches to a test state or a non-test state accordingly.

[0015] Further, the timing tester includes an isolation power supply module, a timing signal input module, a second main control module, and a communication module;

[0016] The isolated power supply module provides suitable power for other modules;

[0017] The second main control module includes peripheral circuits such as a main control chip and a storage circuit. The second main control module receives information from the rocket communication bus through the communication module and starts collecting timing signals or stops collecting timing signals. When a timing signal is input, the input timing signal is measured and calculated, and a preliminary interpretation is performed according to the set parameters (including the emission time and duration of the detected timing signal, and the deviation threshold). The timing information parameters and the interpretation results are encoded according to the communication protocol, sent to the rocket communication bus through the communication module, and finally transmitted back to the ground.

[0018] The timing signal input module includes an optical coupler, which plays an isolation role and shapes the 28V voltage timing signal into a suitable voltage signal (3.3V) and inputs it to the main control chip;

[0019] The communication module is driven by the second main control module to communicate with the rocket communication bus.

[0020] Furthermore, the isolated power supply module includes an isolated DC / DC circuit and multiple voltage conversion circuits; the input, isolated DC / DC circuit adapts to 9-36V input, and the output 12V voltage can be converted into input power for other modules through multiple voltage conversion circuits, including 1.8V, 2.5V, 3.3V power supplies for the main control module and isolated power supplies for the communication circuit.

[0021] Furthermore, a 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 (calculated) parameter exceeds a threshold, a warning message is output.

[0022] On the other hand, the present invention provides a method for self-testing timing signals on a launch vehicle, characterized in that the method uses the self-testing system for timing signals on a launch vehicle according to claims 1 to 6, comprising the following steps:

[0023] When the rocket enters the onboard timing self-test state process, the tail stage controller issues a timing self-test instruction, the improved control mechanism performs short-circuit protection on the pyrotechnic resistance circuit, and connects the controller output and the timing tester, so that the timing tester can detect the controller output and record the timing state;

[0024] When the rocket enters the formal launch process, the tail stage controller issues a formal launch command, that is, "entering non-test state". The improved control agency short-circuits the timing tester and connects the controller output to the pyrotechnics or solenoid valves. At this time, the pyrotechnics can ignite and detonate normally, and the solenoid valves can open normally.

[0025] Compared with the prior art, the above technical solution conceived by the present invention can achieve the following beneficial effects:

[0026] The launch vehicle onboard timing signal self-test system and method of the present invention integrates the timing tester inside the launch vehicle, reduces ground test equipment and process cables, simplifies the test process, realizes onboard timing signal self-test, and improves the automation level. By improving the control mechanism, integrating the short-circuit protection function of the pyrotechnics and the test gating function of the tester, the requirements for onboard self-test are met while ensuring safety and without adding other onboard equipment;

[0027] The input of the timing tester adopts an optocoupler multi-channel synchronous parallel input design, which is abundant in quantity, has good compatibility and versatility, high synchronization, and can synchronously collect multiple signals (for example, it can synchronously collect multiple separated signals during satellite-rocket separation, etc.). It can be used as a modular device to meet the needs of different types of rockets and shorten development time and cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the system of the present invention;

[0029] Figure 2 To improve the schematic diagram of the test status and official launch status of the regulatory agency;

[0030] Figure 3 For each control channel to switch between the test state and the non-test state, two sets of plug-in or disconnect-connect channel structure schematic diagrams are provided;

[0031] Figure 4 It is a schematic diagram of the structure of the timing tester;

[0032] Figure 5 This is the schematic diagram of the optocoupler input detection circuit. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] like Figure 1 As shown, an embodiment of the present invention provides a timing signal self-test system on a carrier rocket. The system is integrated on the rocket body, and includes a power module, at least one controller, and at least one improved control mechanism and a timing tester. In this example, the rocket includes a first stage, a second stage, a third stage and a final stage, and each stage is provided with a controller and an improved control mechanism accordingly. It also includes pyrotechnics or solenoid valves corresponding to the first stage, the second stage, the third stage and the final stage. When testing the timing signal, it is necessary to short-circuit the pyrotechnics or the solenoid valve, so that the timing signal passes through the improved control mechanism and reaches the timing tester for testing.

[0035] The power module supplies power to other devices of the arrow timing self-test system;

[0036] The power module utilizes the original power supply system of the rocket, which can provide energy for electrical equipment and pyrotechnics. It only adds the power supply function for new equipment in the onboard timing self-test system, such as a timing tester, improved control mechanism, etc.

[0037] The controller includes a first communication module, a first main control module, and a timing signal output module. The first communication module receives information transmitted by the rocket communication bus and sends it to the first main control module. The first 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 pyrotechnics to ignite the pyrotechnics, or enters the solenoid valve to actuate the solenoid valve; there are multiple controllers on the rocket, which are generally set in the compartments of each level according to the principle of local control; the timing signal output module of the controller will send out an ignition signal, a solenoid valve actuation signal, or a separation signal at a set time point.

[0038] The improved control mechanism is set between the controller and the explosive device, and the timing signal is transmitted in the order of the controller, the improved control mechanism and the explosive device. Figure 2 As shown, the improved control mechanism includes multiple control channels, each of which can be switched between a test state and 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 formal launch state of the rocket; there are multiple improved control mechanisms, such as Figure 1There are four improved control mechanisms shown; there are multiple channels inside the improved control mechanism, so multiple solenoid valves or pyrotechnic timings can use the same improved control mechanism. The arrangement of the improved control mechanism on the rocket is based on the principle of avoiding or reducing the impact on the timing signal cable as much as possible. It is required that all timing signals pass through the improved control mechanism. In general, the improved control mechanism can be arranged on the path of the original timing signal cable. The improved control mechanism in this example is improved on the basis of patent CN201010231660. The pyrotechnic 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 assembly and guide rod are accommodated in the box body. The motor assembly includes a motor reduction mechanism, a fixing clamp, a plug fixing plate and two plugs. The fixing clamp fixes the motor reduction mechanism on the plug fixing plate. The two plugs are symmetrically mounted on the plug fixing plate with respect to the fixing clamp. The circuit board assembly includes a circuit board, a micro switch and two sockets. The circuit board is fixed to the bottom surface of the box body. The two sockets are symmetrically welded on both sides of the circuit board with respect to the fixing clips, and each corresponds to a 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 plugged in with their corresponding sockets, thereby changing the state of the pyrotechnic control circuit between on and off, thereby realizing the control of the signals in the pyrotechnic control circuit; for the convenience of description, the structure in which each control channel in the patent realizes the plugging or disconnection of the two plugs with their corresponding sockets is called a group of plug-in or disconnection connection channel structure. Each control channel of the improved control mechanism of this example switches between a test state or a non-test state, that is, two groups of plug-in or disconnection connection channel structures are provided, one group of which changes the state of the pyrotechnic control circuit between on and off, and the other group changes the state of the timing tester control circuit between on and off; the specific implementation method includes: each control channel includes at least one group of connection channels and at least one group of short-circuit protection channels, and according to the requirements for the test state or the non-test state, a group of connection channels and a group of short-circuit protection channels are switched, so that the improved control mechanism corresponds to the test state or the non-test state (that is, the formal launch state of the rocket). The specific implementation method of switching a group of connection channels and a group of short-circuit protection channels includes: each control channel is provided with two groups of reciprocating plugs, and the reciprocating movement of the plugs makes them plugged in or disconnected with the corresponding circuit board sockets, thereby realizing the switching of the improved control mechanism to the corresponding test state or non-test state, such as Figure 3As shown in the figure, the circle represents the pin, and the semicircle represents the socket. The two together (concentric state-the state in the dotted box) 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 connects the connection 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 formal launch state, the timing tester is short-circuited, so that the pyrotechnic product or the solenoid valve can receive the launch signal output by the controller to complete the ignition of the pyrotechnic product or the opening and closing of the solenoid valve. Correspondingly, the motor assembly, circuit board assembly, guide rod and other structures must also match the two sets of reciprocating plugs and two sets of sockets. This is the prior art and will not be repeated here.

[0039] When the timing tester improves the corresponding test status of the control agency, it receives the timing signal sent by the controller and performs self-test on the timing signal on the arrow.

[0040] like Figure 4 As shown, 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 voltage conversion circuits, wherein the isolated DC / DC circuit adapts to 9-36V input (for external power supply) and outputs 12V; the output 12V power supply is used to power other modules through multiple voltage conversion circuits, for example, 1.8V, 2.5V, 3.3V power supply is provided to the main control module and isolated power supply is provided to the communication circuit. The second main control module includes a main control chip and peripheral circuits such as storage circuits. The second main control module receives commands from the rocket communication bus through the communication module, and starts or stops collecting timing signals according to the set logic, such as timing: first-stage ignition, first-stage separation, second-stage ignition, second-stage separation, third-stage ignition, third-stage separation, final-stage ignition, final-stage separation, etc. When the timing signal is input, the collected timing signal is measured and calculated, and compared with the set timing moment and duration length, and a preliminary judgment is made as to whether the error exceeds the set threshold. The timing parameter information and the judgment result are encoded according to the communication protocol, and sent to the rocket communication bus through the communication module and transmitted back to the ground control system. The timing signal input module includes an optocoupler, which acts as an isolation, and shapes the 28V voltage timing signal voltage into a suitable voltage signal to the main control chip, depending on the parameters of the main control chip, which is 3.3V in this example; if Figure 5The figure shows the optocoupler input detection circuit. The optocoupler itself has an isolation function and does not require an isolated power supply, which can greatly simplify the number and types of electronic components; the optocoupler output signal only depends on whether there is current flowing through the front circuit, and no uncertain signal will be generated when the input end is floating. It can effectively adapt to the situation where the input end is floating or the input end level difference is low, and adapt to the positive end control, negative end control and two-end control of the signal output circuit; the input ends of the optocouplers can be isolated from each other, which can effectively adapt to the situation where the input signal has a common positive pole or a common negative pole.

[0041] The communication module is driven by the second main control module to communicate with the rocket communication bus.

[0042] For example, when the time difference between the actual issuance time of the sequence and the preset issuance time exceeds the threshold of 1s, or when the time difference between the actual holding time length of the sequence and the preset holding time length exceeds the threshold of 1s, the sequence is judged to be wrong and an alarm message is output; the original ground test plan does not have this judgment logic and can only be manually interpreted.

[0043] 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 a test state or a non-test state. In the example, the non-test signal is a rocket formal launch signal.

[0044] On the other hand, the present invention provides a method for self-testing a timing signal on a launch vehicle, using the aforementioned self-testing system for timing signal on a launch vehicle, comprising the following steps:

[0045] When the rocket enters the onboard timing self-test process, the tail stage controller issues a timing self-test command to short-circuit the pyrotechnic resistance circuit, connect the controller output and the timing tester, so that the timing tester can detect the controller output and record the timing status;

[0046] When the rocket enters the formal launch process, the tail stage controller sends out a formal launch, i.e. non-test signal command, short-circuits the timing tester, and connects the controller output to the pyrotechnics or solenoid valve. At this time, the pyrotechnics can ignite and detonate normally, and the solenoid valve can open normally.

Claims

1. A timing signal self-test system on a launch vehicle, characterized in that: The system is integrated on the rocket body and includes a power module, a controller, an improved control mechanism and a timing tester; The power supply module supplies power to other devices of the on-arrow timing self-test system; The controller includes a first communication module, a first main control module, and a timing signal output module. The first communication module receives a command transmitted from the rocket communication bus and sends it to the first main control module. The first main control module parses the received command and controls the timing signal output module to output a timing signal. The improved control mechanism includes multiple control channels, each of which can be switched between a test state and 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 test state.

2. The launch vehicle onboard timing signal self-test system according to claim 1, characterized in that Each control channel switches between a test state and a non-test state, specifically including: Each of the control channels includes at least one group of connection channels and at least one group of short-circuit protection channels. According to the requirements for the test state or the non-test state, the group of connection channels and the group of short-circuit protection channels are switched, so that the improved control mechanism corresponds to the test state or the non-test state.

3. The launch vehicle onboard timing signal self-test system according to claim 2, characterized in that The switching of a group of connection channels and a group of short-circuit protection channels specifically includes Each control channel is provided with two sets of reciprocating plugs, and the reciprocating movement of the plugs enables them to be plugged in or disconnected with the corresponding circuit board sockets, thereby realizing the switching of the improved control mechanism to the corresponding test state or non-test state.

4. The launch vehicle onboard timing signal self-test system according to claim 1 or 2, characterized in that It also includes a tail section controller, which sends a command to enter a test state or a command to enter a non-test state to the improved control mechanism, so that the improved control mechanism switches to the test state or the non-test state accordingly.

5. The launch vehicle onboard timing signal self-test system according to claim 3, characterized in that The timing tester comprises an isolation power supply module, a timing signal input module, a second main control module, and a communication module; The isolated power supply module provides suitable power for other modules; The second main control module includes a main control chip and peripheral circuits. The second main control module receives information from the rocket communication bus through the communication module, starts collecting timing signals or stops collecting timing signals; when a timing signal is input, the input timing signal is measured and calculated, and a preliminary interpretation is performed according to the set parameters, and the timing information parameters and the interpretation results are encoded according to the communication protocol and sent to the rocket communication bus through the communication module; The timing signal input module includes an optical coupler, which plays an isolation role and shapes the 28V voltage timing signal into a suitable voltage signal and inputs it to the main control chip; The communication module is driven by the second main control module to communicate with the rocket communication bus.

6. The launch vehicle onboard timing signal self-test system according to claim 1, characterized in that The isolated power supply module includes an isolated DC / DC circuit and multiple voltage conversion circuits; the input, isolated DC / DC circuit adapts to 9-36V input, and the output 12V voltage can be converted into input power for other modules through multiple voltage conversion circuits, including 1.8V, 2.5V, 3.3V power supplies for the main control module and isolated power supplies for the communication circuit.

7. The launch vehicle onboard timing signal self-test system according to claim 1, characterized in that A judgment logic is added to the tester software running on the main control module, and a warning message is output when the difference between the detected parameter and the set parameter exceeds a threshold.

8. A launch vehicle onboard timing self-test method, characterized in that The timing signal self-test system on a launch vehicle according to claims 1 to 6 comprises the following steps: When the rocket enters the onboard timing self-test state process, the tail stage controller issues a timing self-test instruction, the improved control mechanism performs short-circuit protection on the pyrotechnic resistance circuit, and connects the controller output and the timing tester, so that the timing tester can detect the controller output and record the timing state; When the rocket enters the formal launch process, the tail stage controller issues a formal launch command, that is, "entering non-test state". The improved control agency short-circuits the timing tester and connects the controller output to the pyrotechnics or solenoid valves. At this time, the pyrotechnics can ignite and detonate normally, and the solenoid valves can open normally.

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