CN116222323A - Time sequence signal self-test system on carrier rocket - Google Patents
Time sequence signal self-test system on carrier rocket Download PDFInfo
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- CN116222323A CN116222323A CN202211643604.9A CN202211643604A CN116222323A CN 116222323 A CN116222323 A CN 116222323A CN 202211643604 A CN202211643604 A CN 202211643604A CN 116222323 A CN116222323 A CN 116222323A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
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- Testing And Monitoring For Control Systems (AREA)
- Testing Electric Properties And Detecting Electric Faults (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a self-testing system for time sequence signals on a carrier rocket, which comprises the following components: the system comprises a power supply module, a controller, an improved control mechanism and a timing tester; 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. According to the system and the method for self-testing the time sequence signal on the carrier rocket, the time sequence tester is integrated in the carrier rocket, so that ground test equipment and process cables are reduced, the test flow is simplified, the self-testing on the time sequence signal on the carrier rocket is realized, and the automation level is improved. Through improving control mechanism, integrated initiating explosive device short-circuit protection function and tester test gating function, guaranteed the security, satisfied the demand of arrow self-test under the condition of not increasing other arrow equipment.
Description
Technical Field
The invention belongs to the technical field of carrier rocket testing, and particularly relates to a carrier rocket on-rocket time sequence signal self-testing system.
Background
The carrier rocket can send out a large number of initiating explosive device signals and electromagnetic valve action signals from before formal launching to the end of flight. The initiating explosive device signals comprise ignition signals and separation signals, and the signals comprise first-stage ignition, first-stage separation, second-stage ignition, second-stage separation, third-stage ignition, third-stage separation and the like according to time sequence; the electromagnetic valve action, namely the opening and closing signal, is a signal which lasts for a certain time length and can be repeatedly sent out. In the testing of each stage of the launch vehicle before the formal launch, the above-mentioned time sequence signal is generally checked to determine whether it meets the design requirement, and the key detection parameters are the signal sending time and the signal duration. The common method is that a cabin cover is arranged on an rocket body, or in a rocket cabin section separation state, the connection between an rocket controller and an initiating explosive device or an electromagnetic valve is disconnected, in general, the initiating explosive device or the electromagnetic valve needs to be short-circuited during testing, an on-rocket interface and ground equipment (such as a time sequence equivalent device) are tested and connected by using a transfer cable, then a time sequence tester is used for testing on-rocket time sequence signals, the preparation steps are more, the flow is complex, and the automatic requirement of rapid test launching of a carrier rocket is not met.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a self-testing system for time sequence signals on a carrier rocket, which is used for simplifying ground equipment and meeting the rapid testing requirements of time sequence signals (such as initiating explosive device signals, electromagnetic valve action signals and the like) of the carrier rocket.
In order to achieve the above purpose, the technical scheme provided by the invention is as follows:
the system is integrated on a rocket body, comprises 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.
Further, each path of control channel is switched between a test state or a non-test state, and specifically 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.
Further, the switching between the set of on channels and the set of short-circuit protection channels specifically includes
Each path of control channel is provided with two pairs (groups) of plugs capable of reciprocating, and the plugs reciprocate to enable the plugs to be plugged in or disconnected from the corresponding circuit board sockets, so that the switching of the corresponding test state or the non-test state of the improved control mechanism is realized.
Further, the system also comprises a tail section controller, wherein the tail section controller sends out a test (entering a test state) command or a non-test (entering a non-test state) command to be input to the improved control mechanism, so that the improved control mechanism correspondingly switches to the test state or the non-test state.
Further, the time sequence tester comprises an isolation 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, a storage circuit and other peripheral circuits, receives information from an arrow communication bus through the communication module, and starts to acquire time sequence signals or stops acquiring 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 (including the sending time and duration length of the detected time sequence signal and a deviation threshold), encoding the time sequence information parameter and interpretation result according to a communication protocol, transmitting the encoded time sequence information parameter and interpretation result to a rocket communication bus through a communication module, and finally transmitting the encoded time sequence information parameter and interpretation result back to the ground;
the time sequence signal input module comprises an optical coupler, wherein the optical coupler plays an isolating role, and the voltage of the 28V voltage time sequence signal is shaped into a (3.3V) 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.
Further, the isolation power supply module comprises a path of isolation 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.
Further, judgment logic is added in 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 value, warning information is output.
In another aspect, the present invention provides a method for self-testing a timing signal on a launch vehicle, characterized by using the system for self-testing a timing signal on a launch vehicle according to claims 1 to 6, comprising the steps of:
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.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
according to the system and the method for self-testing the time sequence signal on the carrier rocket, the time sequence tester is integrated in the carrier rocket, so that ground test equipment and process cables are reduced, the test flow is simplified, the self-testing on the time sequence signal on the carrier rocket is realized, and the automation level is improved. By improving the control mechanism, the initiating explosive device short-circuit protection function and the test gating function of the tester are integrated, so that the requirements of on-arrow self-test are met under the conditions of ensuring the safety and not adding other on-arrow equipment;
the input of the time sequence tester adopts an optocoupler multichannel synchronous parallel input design, has the advantages of abundant quantity, good compatibility and universality, high synchronism, synchronous acquisition of multipath signals (for example, the multipath signals can be synchronously acquired when satellites and arrows are separated), and the time sequence tester can be used as modularized equipment, meets the requirements of rockets of different models, and shortens development time and cost.
Drawings
FIG. 1 is a schematic diagram of a system of the present invention;
FIG. 2 is a schematic diagram of an improved regulatory agency test state and a formal emission state;
FIG. 3 is a schematic diagram of a structure in which each channel is switched between a test state and a non-test state, i.e. two sets of channels are connected in an inserting or disconnecting manner;
FIG. 4 is a schematic diagram of a timing tester;
fig. 5 is a schematic diagram of an optocoupler input detection circuit.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, are intended to fall within the scope of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a self-test system for timing signals on a rocket body of a launch vehicle, the system being integrated on the rocket body, and comprising a power module, at least one controller, and at least one improved control mechanism and a timing tester; the rocket in this example comprises a first stage, a second stage, a third stage and a final stage, and each stage is correspondingly provided with a controller and an improved control mechanism; the fire engine also comprises a primary, a secondary, a tertiary and a final corresponding initiating explosive device or electromagnetic valve; when the time sequence signal is tested, the initiating explosive device or the electromagnetic valve is required to be short-circuited, and the time sequence signal reaches the time sequence tester for testing through the improved control mechanism;
the power supply module supplies power to other equipment of the on-arrow time sequence self-test system;
the power supply module can provide energy for electrical equipment and initiating explosive devices by utilizing an original power supply system of a rocket, and only a standby power supply function, such as a time sequence tester, an improved control mechanism and the like, is added in the time sequence self-testing system on the rocket.
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 information transmitted by the rocket communication bus and then sends the information to the first main control module, and the first main control module compiles the received information into a time sequence signal and controls the time sequence signal output module to output the time sequence signal. In a test state, the output time sequence signal completes the test of the time sequence signal by improving a control mechanism or entering a time sequence tester; in a non-test state, the output time sequence signal enables the initiating explosive device to ignite by improving the control mechanism or entering the initiating explosive device or enables the electromagnetic valve to act by entering the electromagnetic valve; the controller is provided with a plurality of arrows and is generally arranged in the cabin section of each stage by adopting the principle of nearby control; and the time sequence signal output module of the controller sends out an ignition signal, an electromagnetic valve actuating signal or a separation signal at a set time point.
The improved regulating mechanism is arranged between the controller and the initiating explosive device, and the time sequence signal is transmitted along the sequence of the controller, the improved regulating mechanism and the initiating explosive device. As shown in fig. 2, the improved regulating mechanism comprises multiple regulating channels, and each channel can be switched between a test state or a non-test state, so that the improved regulating mechanism corresponds to the test state or the non-test state; the non-test state in this example refers to the rocket formal launch state; there are a plurality of improved regulating mechanisms, four of which are shown in FIG. 1; the improved regulating mechanism has several channels, so that the same improved regulating mechanism may be used in the multiple solenoid valves or initiating explosive devices, and the improved regulating mechanism may be set on rocket to avoid or reduce the influence of the time sequence signal cable as far as possible. The improved control mechanism in the example is improved on the basis of a patent CN201010231660, and the initiating explosive device control device comprises a box body, a motor assembly, a circuit board assembly, a guide rod and an external connector, wherein the motor assembly, the circuit board assembly and the guide rod are accommodated in the box body, the motor assembly comprises a motor speed reducing mechanism, a fixing clamp, a plug fixing plate and two plugs, the fixing clamp fixes the motor speed reducing mechanism on the plug fixing plate, and the two plugs are symmetrically arranged on the plug fixing plate by the fixing clamp; the circuit board assembly comprises a circuit board, a micro switch and two sockets, wherein the circuit board is fixed on the bottom surface of the box body, the two sockets are symmetrically welded on two sides of the circuit board respectively by the fixing clamps, and the two sockets correspond to plugs on the same side respectively; the external connector is electrically connected with the two sockets through the circuit board; when the electric power control circuit works, the motor speed reducing mechanism drives the whole motor assembly to reciprocate under the guide of the guide rod, so that the two plugs are respectively inserted into the corresponding sockets, the state of the electric power control circuit is changed between on and off, and the control of signals in the electric power control circuit is realized; for convenience of description, the structure of each path of control channel in the patent for realizing that two plugs are respectively plugged into or disconnected from the corresponding sockets is called a group of plugging or disconnecting switch-on channel structure. Each path of control channel of the improved control mechanism of the example is switched between a test state and a non-test state, namely two groups of plug-in or switch-off channel structures are arranged, one group of the control circuits of the initiating explosive device are changed between on and off, and the other group of the control circuits of the time sequence tester are changed between on and off; the specific implementation method comprises the following steps: 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 on the test state or the non-test state, so that the improved control mechanism corresponds to the test state or the non-test state (namely the rocket formal emission state). The specific implementation method for switching between the group of the connection channels and the group of the short-circuit protection channels comprises the following steps: each path of control channel is provided with two groups of plugs capable of reciprocating, and the plugs can be inserted into or separated from corresponding circuit board sockets in a reciprocating mode, so that the switching of the corresponding test state or non-test state of the improved control mechanism is realized, as shown in fig. 3, circles in the figure represent pins, semi-circles represent sockets, and the two plugs are in an on state when being combined together (concentric state-state in a broken line frame), and are in an off state otherwise. After switching to the test state, the initiating explosive device is short-circuited, and the time sequence tester is communicated with the communicated channel, so that the time sequence tester can detect the time sequence signal output by the controller, record the time sequence signal and complete the automatic test of the time sequence signal. After the switch to the formal emission state, the time sequence tester is short-circuited, so that the initiating explosive device or the electromagnetic valve can receive the emission signal output by the controller, and the ignition of the initiating explosive device or the opening and closing of the electromagnetic valve are completed. Correspondingly, the motor assembly, the circuit board assembly, the guide rod and other structures are matched with the two groups of plugs capable of reciprocating motion and the two groups of sockets, which are the prior art and are not repeated here.
When the time sequence tester improves the corresponding test state of the control mechanism, the time sequence tester receives the time sequence signal sent by the controller and carries out self-test on the time sequence signal on the arrow.
As shown in fig. 4, the timing tester is a modular universal device, and includes an isolated power module, a timing signal input module, a second main control module, and a communication module; the isolated power supply module comprises an isolated DC/DC circuit and a plurality of voltage conversion circuits, wherein the isolated DC/DC circuit is suitable for 9-36V input (for external power supply) and outputs 12V; the output 12V power supply supplies power to other modules through a plurality of voltage conversion circuits, for example, 1.8V, 2.5V and 3.3V power supply and isolation power supply of a communication circuit are provided for the main control module. The second main control module comprises a main control chip, a memory circuit and other peripheral circuits, and receives commands from the arrow communication bus through the communication module according to set logic, such as time sequence: first-stage ignition, first-stage separation, second-stage ignition, second-stage separation, third-stage ignition, third-stage separation, final-stage ignition, final-stage separation and the like, and starting or stopping acquisition of a time sequence signal; when the time sequence signal is input, the acquired time sequence signal is measured and calculated, the time sequence signal is compared with the set time sequence time and duration time length, whether the error exceeds the set threshold value is primarily judged, the time sequence parameter information and the interpretation result are encoded according to a communication protocol, and the time sequence parameter information and the interpretation result are sent to a rocket communication bus through a communication module and are transmitted back to a ground control system. The time sequence signal input module comprises an optical coupler which plays an isolating role, and shapes the voltage of the 28V voltage time sequence signal into a proper voltage signal which is sent to the main control chip, and the voltage signal is 3.3V in the example according to the parameters of the main control chip; as shown in fig. 5, the optocoupler input detection circuit is shown. The optocoupler has an isolation function, does not need to be supplied with power by an isolation power supply, and can greatly simplify the number and the types of electronic components; the optocoupler output signal only depends on whether current flows through the front-end circuit or not, and an uncertain signal is not generated when the input end is suspended, so that the optocoupler output signal can be effectively adapted to the conditions that the input end is suspended or the input end level difference is low level, and the optocoupler output signal is adapted to the conditions of positive end control, negative end control, two-end control and the like of the signal output circuit; the input ends between the optical couplers can be mutually isolated, and the condition that input signals share the positive electrode or input signals share the negative electrode can be effectively adapted.
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 a threshold value for 1s, or the time difference between the actual holding time length of the time sequence and the preset holding time length exceeds the threshold value for 1s, judging that the time sequence is wrong, and outputting alarm information; the original ground test scheme does not bind the judgment logic and can only be interpreted manually.
As one example, the system of the present invention further includes a tail section controller that issues a test signal or a non-test signal to the improved regulatory agency such that the improved regulatory agency corresponds to a test state or a non-test state. The non-test signal in the example is a rocket formal launch signal.
On the other hand, the invention provides a self-testing method for the time sequence signal on the rocket of the carrier rocket, which utilizes the self-testing system for the time sequence signal on the rocket of the carrier rocket, and comprises the following steps:
when the rocket enters an on-rocket time sequence self-test flow, a tail section controller sends a time sequence self-test instruction to perform short-circuit protection on a initiating explosive device resistor loop, and the controller output and a time sequence tester are conducted, so that the time sequence tester can detect the controller output and record a time sequence state;
when the rocket enters a formal rocket launching process, the tail section controller sends out a formal launching, namely non-test signal instruction, the time sequence tester is short-circuited, the output of the controller is communicated with a initiating explosive device or an electromagnetic valve, and at the moment, the initiating explosive device can be normally fired for detonation and the electromagnetic valve can be normally opened.
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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| Application Number | Priority Date | Filing Date | Title |
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| CN202211643604.9A CN116222323A (en) | 2022-12-20 | 2022-12-20 | Time sequence signal self-test system on carrier rocket |
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| CN202211643604.9A CN116222323A (en) | 2022-12-20 | 2022-12-20 | Time sequence signal self-test system on carrier rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116608741A (en) * | 2023-07-20 | 2023-08-18 | 东方空间技术(山东)有限公司 | Initiating explosive device time sequence testing system, method and equipment of rocket |
| CN116989621A (en) * | 2023-08-01 | 2023-11-03 | 东方空间技术(山东)有限公司 | Carrier rocket separation test system and method |
-
2022
- 2022-12-20 CN CN202211643604.9A patent/CN116222323A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116608741A (en) * | 2023-07-20 | 2023-08-18 | 东方空间技术(山东)有限公司 | Initiating explosive device time sequence testing system, method and equipment of rocket |
| CN116608741B (en) * | 2023-07-20 | 2023-10-03 | 东方空间技术(山东)有限公司 | Initiating explosive device time sequence testing system, method and equipment of rocket |
| CN116989621A (en) * | 2023-08-01 | 2023-11-03 | 东方空间技术(山东)有限公司 | Carrier rocket separation test system and method |
| CN116989621B (en) * | 2023-08-01 | 2024-05-07 | 东方空间技术(山东)有限公司 | Carrier rocket separation test system and method |
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