CN109582573A - Test missile-borne integration control plane software version method - Google Patents
Test missile-borne integration control plane software version method Download PDFInfo
- Publication number
- CN109582573A CN109582573A CN201811413245.1A CN201811413245A CN109582573A CN 109582573 A CN109582573 A CN 109582573A CN 201811413245 A CN201811413245 A CN 201811413245A CN 109582573 A CN109582573 A CN 109582573A
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- software version
- control plane
- missile
- test equipment
- integration control
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/36—Preventing errors by testing or debugging software
- G06F11/3668—Software testing
- G06F11/3672—Test management
- G06F11/3688—Test management for test execution, e.g. scheduling of test suites
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F8/00—Arrangements for software engineering
- G06F8/70—Software maintenance or management
- G06F8/71—Version control; Configuration management
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- Theoretical Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Software Systems (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Computer Security & Cryptography (AREA)
- Computer Hardware Design (AREA)
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Abstract
The present invention relates to flying vehicles control fields, and in particular to a kind of test missile-borne integration control plane software version method.This method includes: integrated control plane before not shooting, and after having loaded software, can carry out the readback of software version number, by RS232 serial ports to confirm whether software loads correctly.But after integrated control plane is shot, RS232 serial ports is just no longer drawn, instead the 1553B bus interface interacted with aircraft.It also needs constantly to upgrade after installing bullet due to missile-borne integration control plane, the readback of software version cannot be carried out after upgrading again by RS232 serial ports, therefore the present invention uses 1553B bus interface, by software version test equipment readback software version, to verify the correctness of integrated control plane software upgrading.
Description
Technical field
The present invention relates to the technical fields of flying vehicles control, more particularly, to a kind of test missile-borne integration control plane software
Version method.
Background technique
Random aviation aircraft, which updates, to be accelerated, and missile-borne integration control plane needs constantly upgrading.It needs to lead to after upgrading
Dedicated software version test equipment readback software version is crossed, to verify the correctness of integrated control plane software upgrading.
Under the premise of the prior art needs to remove bullet upper flap, being connect by software test apparatus with guided missile breakaway plug makes
Bus test integration control plane software version number.The prior art tests missile-borne integration control plane software version speed
Slowly, cumbersome, poor reliability.
Summary of the invention
In consideration of it, the present invention provides a kind of test missile-bornes in order to solve at least one technical problem in the prior art
Integrated control plane software version method.This method comprises:
1) the 1553B bus protocol between integrated control plane and software version test equipment is formulated, including bus is led to
Interrogate address information, message-length, head word information, data block type, data transmission format etc.；
2) after integrated control plane powers on, if receiving the test command that software version test equipment issues, one is returned to
Body control plane software version number；
3) software version test equipment acquires the software version of integrated control plane feedback by starting thread, if collecting
Software version is then printed out the software version number tested by interface；
Technical effect of the invention may is that the present invention under the premise of not removing bullet upper flap, is set by software test
The standby connection with guided missile breakaway plug is surveyed using the integrated control plane software version number of 1553B bus test relative to RS232 serial ports
Examination software version number speed is faster, operation is simpler, reliability is higher.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it is therefore apparent that drawings described below is only some embodiments of the present invention, for this
For the technical staff in field, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is the flow diagram of the test missile-borne integration control plane software version method of one embodiment of the invention；
Fig. 2 is 1553B bus software testing process schematic diagram in the integrated control plane software of one embodiment of the invention；
Fig. 3 is the software test apparatus and guided missile connection schematic diagram of one embodiment of the invention.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described.Obviously, described embodiment is
A part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiments of the present invention, those skilled in the art
Without making creative work, every other embodiment obtained, shall fall within the protection scope of the present invention.
The feature and illustrative examples of various aspects of the invention is described more fully below.In following detailed description
In, many details are proposed, in order to provide complete understanding of the present invention.But come for those skilled in the art
It says it will be apparent that the present invention can be implemented in the case where not needing some details in these details.Below to reality
The description of example is applied just for the sake of providing and better understanding to of the invention by showing example of the invention.The present invention is never
It is limited to any specific setting and method set forth below, but covering finishes under the premise of without departing from the spirit of the present invention
Structure, method, any improvement of device, substitutions and modifications.In the the accompanying drawings and the following description, well known structure and skill is not shown
Art is unnecessary fuzzy to avoid causing to the present invention.
It should be noted that in the absence of conflict, the feature in the embodiment of the present invention and embodiment can be tied mutually
It closes, each embodiment mutually can be referred to and be quoted.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the flow diagram of the test missile-borne integration control plane software version method of one embodiment of the invention；Fig. 2
It is 1553B bus software testing process schematic diagram in the integrated control plane software of one embodiment of the invention；Fig. 3 is the present invention one
The software test apparatus and guided missile connection schematic diagram of embodiment.
With reference to Fig. 1-Fig. 3, the embodiment of the invention provides one kind without dismantling integrated control plane on bullet, directly passes through
1553B bus carries out integrated control plane software version readback, and it is true that software version is carried out after shooting suitable for integrated control plane
Recognize, whether part version loads success.Software version number can be sent to software version by 1553B bus by integrated control plane
Test equipment.
As shown in figure 3, missile-borne integration control plane software version test macro may include: software version test equipment,
1553B bus cable separates breakaway plug on socket and bullet；Breakaway plug is set on guided missile on bullet, and 1553B bus cable connects
Software test apparatus and separation socket are connect, by the connection of breakaway plug on separation socket and bullet, realizes that integrated control plane is soft
The reading of part version.
In some embodiments, the workflow of software load test equipment can be as follows:
1) software loading equipemtn is connect with guided missile breakaway plug；
2) bus protocol for formulating software version test equipment is passed including address information, handshaking information, data
Transport format；
3) software version test equipment equipment starts；
4) handshaking information is sent to integrated control plane；
If 5) receive the feedback information of shaking hands of integrated control plane, test command is sent to by software version test equipment
Integrated control plane；
If 6) receive the software version number that integrated control plane returns, software version test terminates, cutting power supply.
In some embodiments, the workflow of integrated control plane is as shown in Figure 2；
1) after integrated control plane powers on, self-test, application program are run；
2) judge whether to receive the handshaking information that software version test equipment is sent, if receiving, be tested to software version
Equipment sends feedback information of shaking hands, and executes step 3) -4)；If not receiving, enter step 5)；
3) test command that software version test equipment is sent is received；
4) judge whether time-out of shaking hands, if having not timed out, continue waiting for handshaking information, if overtime, enter step 5)；
5) application program end of run controls electricity under computer.
It should be noted that above-mentioned flow operations can carry out different degrees of combined application, for simplicity, repeating no more
The sequence of above-mentioned operating procedure can be carried out spirit according to actual needs by various combined implementations, those skilled in the art
Adjustment living, or above-mentioned steps are subjected to the operation such as flexible combination.
In addition, the implementation of functional unit shown in above-described embodiment can for hardware, software, firmware or they
Combination.When realizing in hardware, may, for example, be electronic circuit, specific integrated circuit (ASIC), firmware appropriate,
Plug-in unit, function card etc..When being realized with software mode, element of the invention be used to execute the program of required task or
Code segment.Perhaps code segment can store in machine readable media program or the data-signal by carrying in carrier wave exists
Transmission medium or communication links are sent." machine readable media " may include any Jie for capableing of storage or transmission information
Matter.The example of machine readable media include electronic circuit, semiconductor memory devices, ROM, flash memory, erasable ROM (EROM),
Floppy disk, CD-ROM, CD, hard disk, fiber medium, radio frequency (RF) link, etc..Code segment can be via such as internet, interior
The computer network of networking etc. is downloaded.
Finally it should be noted that: the above embodiments are merely illustrative of the technical solutions of the present invention, but protection of the invention
Range is not limited thereto, and anyone skilled in the art in the technical scope disclosed by the present invention, can be thought easily
It is modified or replaceed to various equivalent, these, which are modified or replaceed, should all be included within the scope of the present invention.
Claims (5)
1. a kind of test missile-borne integration control plane software version method, which comprises the following steps:
Formulate the 1553B bus protocol between missile-borne integration control plane and software version test equipment, wherein the missile-borne
Integrated control plane includes 1553B bus, the 1553B bus protocol and 1553B bus widening；
Software version test equipment issues the test command for extracting software version number；
In response to test command, missile-borne integration control plane is to software version test equipment feedback software version number；
Software version test equipment acquires the software version number of missile-borne integration control plane feedback by starting thread；
If collecting software version number, software version test equipment prints the software version number tested by interface defeated
Out.
2. the method according to claim 1, wherein the bus protocol includes:
Bus communication address information, message-length, head word information, data block type, data transmission format.
3. the method according to claim 1, wherein further include:
Software loading equipemtn is connect with guided missile breakaway plug；
The starting of software version test equipment equipment；
Handshaking information relevant to 1553B bus protocol is sent to missile-borne integration control plane；
If receiving the feedback information of shaking hands of missile-borne integration control plane, test command is sent to bullet by software version test equipment
Carry integrated control plane.
4. according to the method described in claim 3, it is characterized by further comprising:
If receiving the software version number that integrated control plane returns, software version test terminates, cutting power supply.
5. according to the method described in claim 3, it is characterized by further comprising:
S1 after missile-borne integration control plane powers on, runs self-test, application program；
S2, missile-borne integration control plane judge whether to receive the handshaking information that software version test equipment is sent,
If receiving handshaking information, missile-borne integration control plane (10) sends feedback information of shaking hands to software version test equipment,
And execute step S3 and S4)；
If not receiving handshaking information, S5 is entered step；
S3, missile-borne integration control plane (10) receive the test command that software version test equipment is sent；
S4, software version test equipment (20) judge whether time-out of shaking hands, if having not timed out, continue waiting for handshaking information,
If overtime, S5 is entered step；
S5, it is electric under missile-borne integration control plane when the application program end of run in software version test equipment (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811413245.1A CN109582573A (en) | 2018-11-23 | 2018-11-23 | Test missile-borne integration control plane software version method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811413245.1A CN109582573A (en) | 2018-11-23 | 2018-11-23 | Test missile-borne integration control plane software version method |
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| CN201811413245.1A Pending CN109582573A (en) | 2018-11-23 | 2018-11-23 | Test missile-borne integration control plane software version method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110727625A (en) * | 2019-09-23 | 2020-01-24 | 江西洪都航空工业集团有限责任公司 | Data loading equipment and data interaction method after loading of missile-borne integrated guide machine |
| CN114967493A (en) * | 2022-01-26 | 2022-08-30 | 西安雷通科技有限责任公司 | Guided rocket projectile missile-borne computer test simulation system and test method |
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| CN102147733A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Method for loading procedure to satellite borne remote terminal computer by using 1553B serial data bus |
| CN104461626A (en) * | 2014-12-08 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Software loading method using 1553B bus |
| DE102014209969A1 (en) * | 2014-05-26 | 2015-11-26 | Siemens Aktiengesellschaft | Method for computer-aided testing of a technical system |
| CN106200609A (en) * | 2015-04-29 | 2016-12-07 | 陕西中交天健车联网信息技术有限公司 | Automatically the device and method of engine of heavy-duty car ECU software version is tested |
| CN108153541A (en) * | 2017-12-13 | 2018-06-12 | 天津津航计算技术研究所 | FPGA online upgrading methods based on 1553B buses |
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2018
- 2018-11-23 CN CN201811413245.1A patent/CN109582573A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102147733A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Method for loading procedure to satellite borne remote terminal computer by using 1553B serial data bus |
| DE102014209969A1 (en) * | 2014-05-26 | 2015-11-26 | Siemens Aktiengesellschaft | Method for computer-aided testing of a technical system |
| CN104461626A (en) * | 2014-12-08 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Software loading method using 1553B bus |
| CN106200609A (en) * | 2015-04-29 | 2016-12-07 | 陕西中交天健车联网信息技术有限公司 | Automatically the device and method of engine of heavy-duty car ECU software version is tested |
| CN108153541A (en) * | 2017-12-13 | 2018-06-12 | 天津津航计算技术研究所 | FPGA online upgrading methods based on 1553B buses |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110727625A (en) * | 2019-09-23 | 2020-01-24 | 江西洪都航空工业集团有限责任公司 | Data loading equipment and data interaction method after loading of missile-borne integrated guide machine |
| CN114967493A (en) * | 2022-01-26 | 2022-08-30 | 西安雷通科技有限责任公司 | Guided rocket projectile missile-borne computer test simulation system and test method |
| CN114967493B (en) * | 2022-01-26 | 2024-07-05 | 西安雷通科技有限责任公司 | Computer test simulation system and test method for guided rocket missile-borne |
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Application publication date: 20190405 |