Full-ammunition box-opening-free test system and method

Abstract

The invention relates to the technical field of missile testing, in particular to a full-missile box-opening-free testing system and method. The system comprises a missile tester, a missile and a missile-borne computer, and the missile tester is used for simulating the function of a launching device to output direct current; the missile is used for receiving the direct current and converting the direct current into power supply for a plurality of missile-borne components by utilizing a power distribution function of the missile; the missile-borne computer is arranged on the missile; and the missile tester is also used for sending a test instruction to the missile-borne computer and receiving a test result returned by the missile-borne computer. According to the full-missile box-opening-free test system and method, a missile-borne computer test mode is designed, serial port configuration of the launching device is carried out according to a test instruction, forwarding of the test instruction and a test result is completed through the missile-borne computer, tests of all missile-borne devices are completed under the condition that missile packaging boxes are not opened, and operation is easy and safe.

Description

Technical Field

[0001] The invention relates to the technical field of missile testing, and in particular to a full-missile unpacking-free testing system and method. Background Art

[0002] After the missile is delivered to the user, the entire missile needs to be tested for the launch process regularly. If an abnormality occurs during the test, further functional tests need to be performed on the components on the missile to determine the cause of the failure. After the missile is packed, the external interface is only connected to the plug-in on the wall of the packaging box through an adapter cable. The plug-in cannot directly communicate with the components on the missile. Therefore, the current method for testing components on the missile is to disassemble the components from the missile and test them with special test equipment or open the missile test cover and test different components with different cables. Missiles have pyrotechnics such as engines, thermal batteries, and warheads. The existing methods for testing components on missiles are complex and dangerous. Summary of the invention

[0003] In view of the above-mentioned shortcomings of the prior art, the purpose of the present invention is to provide a full-missile no-boxing testing system and method. The present invention realizes the functional testing of various components on the missile with the same test cable without opening the missile packaging box and the missile test port cover. The testing method is simple and safe.

[0004] In order to achieve the above-mentioned purpose and other related purposes, the present invention provides a full-bullet no-opening-box testing system, comprising:

[0005] Missile tester, used to simulate the function of the launcher to output direct current;

[0006] The missile is used to receive the direct current and convert the direct current into power for multiple components on the missile by using its own power distribution function;

[0007] an onboard computer, which is disposed on the missile;

[0008] The missile tester is also used to send test instructions to the onboard computer and receive test results returned by the onboard computer.

[0009] In one embodiment of the present invention, the plurality of missile-mounted components include a seeker, a servo, an inertial group, a GPS, and a data link.

[0010] In one embodiment of the present invention, the missile and the on-board computer are stored in the missile packaging box, and the on-board computer is communicatively connected with the plurality of on-board components via an on-board cable.

[0011] In one embodiment of the present invention, the missile is provided with a plug-in connector, the missile packaging box is provided with a connector, the on-board computer is connected to the plug-in connector via an on-board cable, the plug-in connector is connected to the connector via a switching cable, and the connector is connected to the missile tester via a test cable.

[0012] In one embodiment of the present invention, the missile tester is used to display the test results in real time in a graphical and windowed form, and to save the test results.

[0013] In one embodiment of the present invention, the test instructions include a steering gear self-test instruction, a seeker self-test instruction, and an inertial group zero position test instruction.

[0014] In one embodiment of the present invention, the onboard computer is a single chip microcomputer.

[0015] The present invention also provides a full-bullet no-unpacking test method, including the full-bullet no-unpacking test system, including:

[0016] S1, the missile tester sends test instructions, including steering gear self-check instructions, seeker self-check instructions, and inertial group zero position test instructions. After the missile computer is initialized, if the preset frame of test instructions are continuously received within a preset time, it enters the test mode, otherwise it enters the normal working mode;

[0017] S2, the missile computer determines the missile component to be tested corresponding to the test instruction according to the test instruction, and configures the communication interface between the missile computer and the missile tester to be consistent with the missile component to be tested;

[0018] S3, the missile tester sends the test instruction to the missile, and the on-board computer forwards the test instruction to the on-board component to be tested in real time;

[0019] S4. The on-board computer forwards the test results of the on-board component to be tested to the missile tester, and the missile tester analyzes, stores and displays the results.

[0020] In an embodiment of the present invention, the preset time is 100 ms, and the preset frame is 3 frames.

[0021] In one embodiment of the present invention, the communication interface configuration includes communication baud rate, frame header, frame tail, frame length and check mode.

[0022] As described above, the full-bullet no-opening-box testing system and method of the present invention has the following beneficial effects:

[0023] (1) The full-missile unpacking test system of the present invention comprises a missile tester, a missile, and an onboard computer. The present invention utilizes the onboard computer test mode to test various onboard components. Each onboard component communicates with the onboard computer, and only the onboard computer communicates with the external launch device. Therefore, the onboard computer is used as an intermediary to forward the test instructions of the missile tester to the onboard components through the onboard computer, and the test results of the onboard components are forwarded to the missile tester through the onboard computer.

[0024] (2) The whole missile unpacking-free testing method of the present invention designs a missile-mounted computer test mode, configures the launch device serial port according to the test instructions, and uses the missile-mounted computer to complete the forwarding of test instructions and test results, so as to complete the test of each missile-mounted device without opening the missile packaging box, which is simple and safe to operate.

[0025] (3) The full-bomb unpacking test method of the present invention uses a test cable to complete the test of all components on the bomb. The cable has communication and power supply functions. There is only one connector at each end of the cable. There is no need to branch the cable, and the cable is simple.

[0026] (4) The full-bullet no-unpacking testing method of the present invention is comprehensive and can perform functional testing, zero-position testing and calibration on the components on the bullet.

[0027] (5) The missile tester application program of the full-missile unpacking test method of the present invention is easy to develop. It only needs to embed the factory acceptance software of the corresponding equipment on the missile into the missile tester, and the main program calls the factory acceptance software of the corresponding equipment to complete the test of the corresponding equipment. In addition, the missile tester application program of the present invention is easy to maintain. When the factory acceptance software of a certain equipment on the missile is upgraded, it only needs to embed the upgraded software into the missile tester, and there is no need to change other software of the missile tester. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A structural schematic diagram of a full-bullet, box-free testing system provided in an embodiment of the present application.

[0029] Figure 2 A flowchart of a full-bullet, no-box testing method provided in an embodiment of the present application.

[0030] Figure 3 A flow chart of switching test components on a bullet for a full-bullet no-unpacking testing method provided in an embodiment of the present application.

[0031] Figure 4 A test cable definition diagram for a full-flexible, no-unpacking test method provided in an embodiment of the present application.

[0032] Component number description

[0033] 1 Missile Tester

[0034] 2 Test cables

[0035] 3 Missiles

[0036] 4 Missile packaging boxes

[0037] 5 Pop up the computer

[0038] 6 Pop-up parts

[0039] 7 Adapter Cable

[0040] 8 Unplug DETAILED DESCRIPTION

[0041] The following describes the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0042] It should be noted that the illustrations provided in the following embodiments are only used to illustrate the basic concept of the present invention in a schematic manner, and thus the illustrations only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0043] Terms such as first or second can be used to describe various components, but these components are not limited by the above terms. The above terms are used to distinguish one component from another component, for example, without departing from the scope of the concept according to the present disclosure, a first component can be referred to as a second component, and similarly, a second component can be referred to as a first component.

[0044] In addition, "connected / coupled" means that one component is directly electrically coupled to another component or is indirectly electrically coupled through another component. The singular form may include the plural form unless explicitly stated in the sentence. In addition, "include / comprise" or "includes / comprises" used in this specification indicates that one or more components, steps, operations, and elements exist or have been added. The specific structural or functional descriptions of the examples of the implementation of the concepts disclosed in this specification are only illustrated to describe the examples of the implementation of the concepts, and the examples of the implementation of the concepts can be implemented in various forms, but these descriptions are not limited to the examples of the implementation described in this specification.

[0045] According to the concept, various modifications and changes can be applied to the examples of the embodiments, so that the examples of the embodiments will be illustrated in the drawings and described in the specification. However, the examples of the embodiments according to the concept are not limited to the specific embodiments, but include all changes, equivalents or replacements included in the spirit and technical scope of the present disclosure.

[0046] It should be understood that when an element is described as being "coupled" or "connected" to another element, the element may be directly coupled or directly connected to the other element, or may be coupled or connected to the other element through a third element. Conversely, it should be understood that when an element is referred to as being "directly coupled to" or "directly coupled to" another element, no other element is placed between them. Other expressions describing the relationship between components (i.e., "between" and "directly between" or "adjacent to" and "directly adjacent to") need to be interpreted in the same manner.

[0047] The terms used in this specification are only used to describe specific examples of the embodiments and are not intended to limit the present disclosure. If there is no clear opposite meaning in the context, the singular form may include the plural form. In this specification, it should be understood that the term "including" or "having" indicates the presence of the features, quantities, steps, operations, components, parts or combinations thereof described in the specification, but the possibility of the presence or addition of one or more other features, quantities, steps, operations, components, parts or combinations thereof cannot be precluded.

[0048] If there is no contrary definition, all terms (including technical terms or scientific terms) used herein have the same meaning as those generally understood by ordinary technicians in the field. If the terms defined in the commonly used dictionary are not clearly defined in this specification, they should be interpreted as having the same meaning as in the context of the relevant technology, and not interpreted as ideal or overly formal meanings.

[0049] Descriptions of well-known components and processing techniques may be omitted so as not to unnecessarily obscure the embodiments of the disclosure.

[0050] Throughout the specification, the same reference numerals refer to the same elements. Thus, even if a reference numeral is not mentioned or described with reference to one figure, it may be mentioned or described with reference to another figure. Furthermore, even if a reference numeral is not shown in one figure, it may be mentioned or described with reference to another figure.

[0051] In addition, the logic level of the signal may be different or opposite to the described logic level. For example, a signal described as having a logic "high" level may alternatively have a logic "low" level, and a signal described as having a logic "low" level may alternatively have a logic "high" level.

[0052] The following will describe the various embodiments of the present disclosure in detail with reference to the accompanying drawings. However, it will be appreciated by those skilled in the art that in the various embodiments of the present disclosure, many technical details are provided in order to enable the reader to better understand the present disclosure. However, even without these technical details and various changes and modifications based on the following embodiments, the technical solutions claimed in the present disclosure can be implemented.

[0053] See also Figure 1 , Figure 1 The structural principle diagram of a full-missile unpacking test system provided in an embodiment of the present application. The present invention provides a full-missile unpacking test system, comprising a missile tester 1, a missile 3, and an onboard computer 5. The missile tester 1 is used to simulate the function of a launch device to output direct current; the missile 3 is used to receive the direct current and use its own power distribution function to convert the direct current into power supply for multiple onboard components 6; the onboard computer 5 is arranged on the missile 3; the missile tester 1 is also used to send test instructions to the onboard computer 5 and receive test results returned by the onboard computer 5.

[0054] Specifically, the missile tester 1 simulates the function of the launch device and outputs two direct currents to complete the power supply to the missile 3. The missile 3 uses its own power distribution function to convert the test power supply to the power supply of each on-board component 6. The multiple on-board components 6 include a seeker, a steering gear, an inertial group, a GPS, a data link, etc. The missile tester 1 simulates the launch device to send a test instruction to the on-board computer 5, and receives the test result returned by the on-board computer 5.

[0055] The method of the full-missile unpacking test system of the present invention uses the on-board computer test mode to test each on-board component. Each on-board component communicates with the on-board computer, and only the on-board computer communicates with the external launch device, so the on-board computer is used as an intermediary to forward the test instructions of the missile tester to the on-board components through the on-board computer, and the test results of the on-board components are forwarded to the missile tester through the on-board computer.

[0056] Specifically, the missile 3 and the onboard computer 5 are stored in the missile packaging box 4, and the onboard computer 5 is connected to the plurality of onboard components 6 through an onboard cable. The missile 3 is provided with a plug-in connector 8, and the missile packaging box 4 is provided with a connector 8. The onboard computer 5 is connected to the plug-in connector 8 through an onboard cable, and the plug-in connector 8 is connected to the connector 8 through a transfer cable 7, and the connector 8 is connected to the missile tester 1 through a test cable 2. The missile tester 1 is used to display the test results in real time in a graphical and windowed form, and save the test results.

[0057] In one embodiment of the present invention, the missile computer 5 communicates with each missile component 6 through the missile cable, and communicates with the launch device, namely the missile tester 1, through plug-in / plug-out 8; the missile tester 1 displays the test data in real time in a graphical and windowed form, and can save the original test data. The missile 3 is stored in the missile packaging box 4, and the missile working connector is transferred to the wall of the packaging box 4 through the transfer cable 7.

[0058] See also Figure 4 , Figure 4 A test cable definition diagram for a full-missile unpacking test method provided in an embodiment of the present application. The test cable 2 node definition is the same as the missile working connector definition, with a launch device and missile computer 5 communication node and a missile power supply node. The node definition is simple, connecting the missile tester 1 and the connector on the wall of the packaging box 4.

[0059] Specifically, the test instructions include a steering gear self-test instruction, a seeker self-test instruction, and an inertial group zero position test instruction.

[0060] The application program of the missile tester 1 in the full-missile unpacking test system of the present invention adopts a modular design, and is composed of a framework module and a component module. The framework module only completes the test process management, and the component module is the component factory acceptance procedure, completing the component test and data processing. The framework module calls the corresponding component module according to different test components, and the change of a component test program has no effect on other component test modules and the framework module, and the software has good extensibility.

[0061] The full-bullet unpacking-free testing system of the present invention uses one test cable to complete the testing of all the bullet components 6. Both ends of the test cable 2 are provided with a connector respectively, without branch cables, and the cable is simple.

[0062] The full-missile box-free testing system of the present invention realizes the functional testing of various missile components using the same test cable without opening the packaging box 4 and the missile test port cover, and the testing method is simple and safe.

[0063] See also Figure 2 , Figure 3 , Figure 2 A flowchart of a full-bullet, no-box testing method provided in an embodiment of the present application. Figure 3 A flow chart of switching test components on a bullet for a full-bullet no-unpacking testing method provided in an embodiment of the present application.

[0064] The present invention also provides a full-bullet no-unpacking test method, including the full-bullet no-unpacking test system mentioned above, and the full-bullet no-unpacking test method includes:

[0065] S1. The missile tester 1 sends test instructions, including a servo self-check instruction, a seeker self-check instruction, and an inertial group zero position test instruction. After the missile computer 5 is initialized, if it receives test instructions of a preset frame continuously within a preset time, it enters the test mode, otherwise it enters the normal working mode.

[0066] S2. The onboard computer 5 determines the onboard component to be tested corresponding to the test instruction according to the test instruction, and configures the communication interface between the onboard computer 5 and the missile tester 1 to be consistent with the onboard component to be tested.

[0067] S3, the missile tester 1 sends the test instruction to the missile 3, and the on-board computer 5 forwards the test instruction to the on-board component to be tested in real time.

[0068] S4. The onboard computer 5 forwards the test results of the onboard components to be tested to the missile tester 1, and the missile tester 1 analyzes, stores and displays the results.

[0069] In one embodiment of the present invention, a full-bullet no-opening-box testing method comprises the following steps:

[0070] Connect the test cable 2 to the plug-in / plug-out adapter on the packaging box wall and the missile tester 1.

[0071] The missile 3 is powered on by controlling the missile tester 1.

[0072] The onboard computer 5 enters the test mode: the missile tester 1 sends a test command. After the onboard computer 5 is initialized, if 3 frames of test commands are received continuously within 100ms, it enters the test mode, otherwise it enters the normal mode and starts the missile launch process.

[0073] Communication serial port configuration: The missile tester 1 calls the factory acceptance software of the corresponding missile components and sends test instructions, such as the steering gear self-test instruction, the guidance head self-test instruction, and the inertial group zero position test instruction. The missile computer 5 determines the missile component to be tested according to the test instruction, and configures the launch device communication port to be consistent with the missile component. The serial port configuration includes the communication baud rate, frame header, frame tail, frame length and verification method.

[0074] Test instruction sending: According to the test instruction, the onboard computer 5 first controls the power distributor to supply power to the corresponding equipment on the missile, and then forwards the test instruction to the onboard components.

[0075] Test data upload: The data returned from the missile is forwarded to the missile tester 1 through the external communication port. The missile tester 1 displays and stores the data and analyzes the data to determine whether the status of the components on the missile is normal.

[0076] In summary, the full-bomb unpacking-free testing method of the present invention uses a test cable to complete the test of all components on the missile. The cable has communication and power supply functions. There is only one connector at each end of the cable. There is no need to branch the cable, and the cable is simple. The full-bomb unpacking-free testing method of the present invention is comprehensive and can perform functional testing, zero-position testing and calibration on the components on the missile. The missile tester application of the full-bomb unpacking-free testing method of the present invention is easy to develop. It only needs to embed the factory acceptance software of the corresponding equipment on the missile into the missile tester, and the main program calls the factory acceptance software of the corresponding equipment to complete the test of the corresponding equipment. And the missile tester application of the present invention is easy to maintain. When the factory acceptance software of a certain equipment on the missile is upgraded, it only needs to embed the upgraded software into the missile tester, and there is no need to change other software of the missile tester.

[0077] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A full-bullet no-opening-box testing system, characterized in that: include: A missile tester (1) for simulating the function of a launcher to output direct current; The missile (3) is used to receive the direct current and, using its own power distribution function, convert the direct current into power for a plurality of on-board components (6); an onboard computer (5) disposed on the missile (3); The missile tester (1) is also used to send test instructions to the onboard computer (5) and receive test results returned by the onboard computer (5).

2. The full-bullet no-opening-box testing system according to claim 1 is characterized in that: The plurality of missile-mounted components (6) include a seeker, a steering gear, an inertial group, a GPS, and a data link.

3. The full-bullet no-opening-box testing system according to claim 1 is characterized in that: The missile (3) and the on-board computer (5) are stored in the missile packaging box (4), and the on-board computer (5) is communicatively connected with a plurality of on-board components (6) via an on-board cable.

4. The full-bullet no-opening-box testing system according to claim 3 is characterized in that: The missile (3) is provided with a plug-in connector (8), the missile packaging box (4) is provided with a connector (8), the missile-mounted computer (5) is connected to the plug-in connector (8) via an on-missile cable, the plug-in connector (8) is connected to the connector (8) via a switching cable (7), and the connector (8) is connected to the missile tester (1) via a test cable (2).

5. The full-bullet no-opening-box testing system according to claim 1 is characterized in that: The missile tester (1) is used to display the test results in real time in a graphical and windowed form, and to save the test results.

6. The full-bullet no-opening-box testing system according to claim 1 is characterized in that: The test instructions include a steering gear self-test instruction, a seeker self-test instruction, and an inertial group zero position test instruction.

7. The full-bullet no-opening-box testing system according to any one of claims 1 to 6, characterized in that: The onboard computer (5) is a single chip microcomputer.

8. A full-bullet no-boxing test method, comprising the full-bullet no-boxing test system according to any one of claims 1 to 7, characterized in that: include: S1, the missile tester (1) sends a test command, including a steering gear self-check command, a seeker self-check command, and an inertial group zero position test command. After the missile computer (5) is initialized, if it continuously receives a preset frame of test commands within a preset time, it enters a test mode, otherwise it enters a normal working mode; S2, the onboard computer (5) determines the onboard component to be tested corresponding to the test instruction according to the test instruction, and configures the communication interface between the onboard computer (5) and the missile tester (1) to be consistent with the onboard component to be tested; S3, the missile tester (1) sends the test instruction to the missile (3), and the on-board computer (5) forwards the test instruction to the on-board component to be tested in real time; S4. The on-board computer (5) forwards the test results of the on-board component to be tested to the missile tester (1), and the missile tester (1) analyzes, stores and displays the results.

9. The full-bullet no-opening-box testing method according to claim 8, characterized in that: The preset time is 100ms, and the preset frame is 3 frames.

10. The full-bullet no-opening-box testing method according to claim 8, characterized in that: The communication interface configuration includes communication baud rate, frame header, frame tail, frame length and check mode.

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