CN110006678B - Space environment fault diagnosis equipment and method - Google Patents
Space environment fault diagnosis equipment and method Download PDFInfo
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- CN110006678B CN110006678B CN201910329761.4A CN201910329761A CN110006678B CN 110006678 B CN110006678 B CN 110006678B CN 201910329761 A CN201910329761 A CN 201910329761A CN 110006678 B CN110006678 B CN 110006678B
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Abstract
The invention discloses space environment fault diagnosis equipment and a diagnosis method, wherein the equipment comprises a fault diagnosis instrument and handheld equipment, the handheld equipment is connected with the fault diagnosis instrument, and the fault diagnosis instrument is accessed to an internal bus of a subsystem of an environment control and life support system; the fault diagnosis instrument is used for acquiring real-time data of the subsystems, wherein the real-time data comprises subsystem analog quantity, remote measurement parameters and fault codes; the internal bus of the life support system subsystem can obtain data of the subsystem in real time, and meanwhile, the ground expert base reasoning knowledge is used for guiding a astronaut to eliminate faults and achieving fault location. The invention adopts a mode of combining automation and manual work to complete the positioning, diagnosis and processing of space environment faults, and astronauts can participate in fault diagnosis through modes of olfaction, hearing, visual observation, actual operation and the like, thereby solving the problem that the conventional on-orbit fault diagnosis mainly depends on ground support, reducing mass data transmission between satellites and ground and improving the accuracy of on-orbit fault positioning.
Description
Technical Field
The invention belongs to the technical field of electronic information, and particularly relates to space environment fault diagnosis equipment and a space environment fault diagnosis method.
Background
At present, in a space environment, a fault diagnosis mode is that a system-level controller acquires parameters of each subsystem sensor, and if a fault mode occurs, the controller gives processing measures according to fault criteria, wherein the measures are mainly alarming or shutdown maintenance. However, each subsystem has the following two problems when a failure mode is given:
1) the fault mode given by each subsystem cannot be completely detailed to a certain component, and the maintenance means of the subsystems is carried out by replacing the fault component, so that further troubleshooting and diagnosis are needed until the fault component is positioned;
2) the failure modes of all subsystems are not comprehensive, the failure modes of some subsystems have no automatic failure criterion function, a controller cannot automatically identify the failure, and a spacecraft needs to sense the failure by using other means such as a sense organ and the like so as to identify the failure.
Therefore, in the troubleshooting process, the troubleshooting method of automatically acquiring the sensor parameters through the system-level controller is difficult or needs to be carried out at double cost to accurately position the fault assembly, and in the fault diagnosis mode, a large amount of data needs to be transmitted to the ground and is guided by ground personnel to carry out fault diagnosis, so that the workload of the ground personnel is increased, and therefore the fault diagnosis equipment capable of accurately positioning the fault and saving the labor cost is needed.
Disclosure of Invention
The invention provides space environment fault diagnosis equipment and a diagnosis method aiming at the defects of inaccurate fault location and dependence on ground support for diagnosis transition in the current fault diagnosis means.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a space environment fault diagnosis device comprises a fault diagnosis instrument and a handheld device, wherein the handheld device is connected with the fault diagnosis instrument, and the fault diagnosis instrument is accessed to an internal bus of a subsystem of an environment control and life support system;
the fault diagnosis instrument is used for acquiring real-time data of the subsystems, wherein the real-time data comprises subsystem analog quantity, remote measurement parameters and fault codes;
the internal bus of the life support system subsystem can obtain data of the subsystem in real time, and meanwhile, the ground expert base reasoning knowledge is used for guiding a astronaut to eliminate faults and achieving fault location.
Preferably, the fault diagnosis instrument comprises a portable notebook computer and a switching box, wherein the portable notebook computer is connected with an internal bus of the life support system subsystem through the switching box.
Preferably, the internal bus of the life support system subsystem is connected with a plurality of controllers, and the controllers are connected with the sensors of the subsystems.
A space environment fault diagnosis method comprises the following steps:
1) the fault diagnosis instrument is communicated with an internal bus of a life support system subsystem to acquire real-time data on the bus;
2) judging the occurrence of the fault according to the real-time data;
3) after the fault occurs, starting fault phenomenon confirmation: selecting and confirming a plurality of current fault phenomena through a fault diagnosis instrument, or judging through a fault analysis code of the fault diagnosis instrument;
4) after the fault phenomenon is confirmed, the fault diagnosis instrument acquires relevant historical/current relevant data, deduces and prompts component assemblies possibly having faults by combining a diagnosis strategy, and gives external conditions participating in the maintenance;
5) the fault diagnosis instrument prompts an operation method;
6) after the operation is finished, checking and confirming, including checking the change of parameters or phenomena;
7) matching the confirmation result with an expert knowledge base of the fault diagnosis instrument, adding or deleting suspected fault assemblies, generating next operation prompts, returning to the step 5), and continuously confirming the final fault assemblies;
8) after the fault component assembly is positioned, providing relevant information of the positioning component assembly and prompting the installation position of the fault component assembly; directly switching to step 13 when maintenance is not needed);
9) when maintenance is needed, a maintenance strategy is generated;
10) in the maintenance process, the diagnostic instrument prompts an astronaut to operate;
11) after the operation of the astronaut is finished, prompting the astronaut of the content to be confirmed, and if the parameters can be obtained in real time through a diagnostic instrument, automatically confirming by software;
12) matching the confirmation result with an expert knowledge base, determining whether the maintenance process is correct, entering the next step if the maintenance process is correct, and finishing diagnosis; if not, returning to the step 10);
13) after the maintenance is finished, generating statistical information of the diagnosis and maintenance process; and giving related suggestions in the process of subsequent tasks.
Preferably, in the step 2), the fault occurrence judgment is that the fault occurrence is sensed through smell, hearing and vision of an astronaut or is prompted through a fault diagnosis instrument.
Preferably, in step 10), the prompting method for prompting the operation step of the astronaut is pictures, files and videos, if instruction sending is involved, instruction coding or name and sending mode are given, and the sending mode is application to the ground or autonomous sending through a handheld device.
Preferably, in the step 4), when the external condition of the maintenance is participated, the prompting mode comprises pictures and characters; and the astronaut confirms whether the external conditions are met, and then the subsequent diagnosis process is started.
Preferably, in step 5), if instruction transmission is involved, instruction codes or names and transmission modes are given, and the instructions are applied to the ground or autonomously transmitted through the handheld device.
Preferably, in step 6), the parameters are obtained in real time by the fault diagnosis instrument and automatically confirmed.
Preferably, in step 8), the name, number and three-dimensional appearance of the positioning component are given, and the installation position of the component is prompted in the form of figures and characters.
The invention has the following beneficial effects:
the portable space fault diagnosis equipment carries out space fault diagnosis through the fault diagnosis instrument and the handheld equipment, is simple, has quick and accurate diagnosis, and is used for guiding astronauts to eliminate faults by combining and utilizing the reasoning knowledge of a ground expert library so as to realize fault positioning. The invention is suitable for the fields of space computers, industrial control and the like with complex fault modes and accurate positioning requirements, can utilize portable fault diagnosis equipment to provide data, diagnosis information and expert knowledge on line and guide maintenance personnel to troubleshoot and maintain in vivid figures, thereby shortening the fault detection and operation time, improving the maintenance efficiency and safety, saving human resources and improving the autonomous emergency capability of the maintenance personnel, and has important popularization and application values.
According to the diagnosis method, the on-orbit troubleshooting and maintenance of the astronaut are guided by the participation of the fault diagnosis equipment and the astronaut and by using the inference knowledge and the diagnosis information of the ground expert library in the form of vivid pictures and characters, and the fault component assembly can be quickly and accurately positioned, so that the fault detection, isolation and operation time is greatly shortened, and the maintenance efficiency is improved; the invention adopts the mode of combining automation and manual work to diagnose the fault, and the astronaut carries out diagnosis operation through the prompt of the fault diagnosis equipment, thereby breaking away from the guidance excessively depending on ground support personnel, realizing the target of on-orbit autonomous fault elimination of the astronaut, avoiding transmitting a large amount of data to the ground, reducing the workload of the ground support personnel and saving human resources.
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FIG. 1 is a diagnostic device access diagram of the present invention;
FIG. 2 is a flow chart of the fault diagnosis of the present invention;
fig. 3 is an exemplary diagram of fault diagnosis according to the present invention.
Detailed Description
The invention is further described below with reference to the following figures and examples.
The invention relates to a space environment fault diagnosis device which adopts a mode of combining automation and manual work to carry out fault diagnosis, namely, a diagnosis test method participated by astronauts is added in a fault diagnosis scheme, and the astronauts are allowed to participate in the fault diagnosis through modes of smell sense, hearing sense, visual sense, actual operation and the like. Secondly, the diagnosis scheme combining automation and manual work needs to provide a human-computer interaction interface to support the on-line or off-line auxiliary test of astronauts, so that space environment fault diagnosis equipment is provided, and the equipment consists of a fault diagnosis instrument and handheld equipment, wherein the fault diagnosis instrument consists of a portable notebook computer and a 1553B adapter box.
The fault diagnosis instrument is accessed to a system bus, is in data communication with other computers, can obtain data on the bus in real time, simultaneously utilizes expert base reasoning knowledge in the fault diagnosis instrument to guide a astronaut to eliminate faults, realizes quick fault preparation positioning, improves the on-orbit autonomous activity of the astronaut, and is a handheld device which is an auxiliary device for on-orbit fault elimination, and the access diagram of the fault diagnosis device is shown as an attached figure 1.
The invention discloses a space environment fault diagnosis method, which comprises the following steps as shown in a flow chart shown in figure 2:
1) the fault diagnosis instrument is accessed to the internal bus, communicates with the computer, acquires real-time data on the bus, displays the received parameters on the computer in a list form, dynamically displays the current running state of each product, and is convenient for a spaceman to quickly find the specific parameters of a specific product when a fault occurs;
2) the fault can be known through two channels, namely, the fault is sensed through the smell, the hearing and the visual sense of an astronaut; secondly, alarming and prompting through a fault diagnosis instrument;
3) after the occurrence of the failure, the failure phenomenon confirmation work is started. The method can confirm the fault phenomena through two methods, namely, an astronaut selects and confirms a plurality of current fault phenomena through fault diagnosis instrument software; secondly, obtaining a fault analysis code through a fault diagnosis instrument, and directly selecting by default;
4) after the fault phenomenon is confirmed, the fault diagnosis instrument acquires relevant historical/current relevant data, displays the data in a curve/list mode, and infers and prompts suspected components which may have faults by combining with self diagnosis strategies. And prompting external conditions (such as tools, spare accessories and the like) of the astronaut, wherein the external conditions need to participate in the maintenance, and the prompting mode comprises pictures and characters. Confirming whether external conditions are met by the astronaut, and starting a subsequent diagnosis process after the external conditions are met;
5) the diagnostic instrument prompts the astronaut to operate the method in a picture, text or video mode. If instruction sending is involved, the instruction needs to be sent autonomously through the handheld device;
6) after the operation of the astronaut is finished, prompting the astronaut about the content to be confirmed, including the change of parameters or a certain phenomenon. If the parameters can be obtained in real time by the diagnostic instrument, the software automatically confirms;
7) matching the confirmation result with the expert knowledge base of the diagnostic instrument by the astronaut, adding or deleting suspected fault assemblies, generating the next operation prompt, returning to the step 5, and continuously confirming the final fault assemblies;
8) when the fault assembly is located, the name, the number and the three-dimensional appearance of the location assembly are given, and the installation position of the assembly is prompted in the form of figures and characters. Directly switching to the step 13 when maintenance is not needed;
9) when maintenance is needed, a maintenance strategy is generated; prompting and confirming external conditions (tools and spare accessories) participating in maintenance in the form of pictures and characters;
10) in the maintenance process, the diagnostic instrument prompts the operation steps of the astronaut, the prompting method is pictures, files and videos, if instruction sending is involved, instruction codes or names and sending modes (application to the ground or autonomous sending through handheld equipment) are given;
11) after the operation of the astronaut is finished, prompting the astronaut about the content to be confirmed, including the change of parameters or a certain phenomenon. If the parameters can be obtained in real time by the diagnostic instrument, the software automatically confirms;
12) and matching the confirmation result with an expert knowledge base, determining whether the maintenance process is correct, entering the next step correctly, and finishing the diagnosis. If not, returning to the step 10.
13) After the maintenance is finished, generating statistical information of the diagnosis and maintenance process, wherein the statistical information comprises diagnosis time and operation steps; and giving relevant suggestions in the subsequent task process, such as contents needing important attention.
Examples
When a certain system runs, the air-saving pump is used for pumping air for 10min, the indication of the pressure sensor is always higher than 10kpa, a spacecraft holds the fault diagnosis instrument and accesses a system bus through the 1553B adapter box, fault data are obtained, the current state of the system is identified, and fault elimination is carried out according to a fault tree in the diagnosis instrument.
FIG. 3 shows a pressure abnormal fault tree presented in the diagnostic apparatus, if the pressure display indicates that the analysis is normal or not, the pump is started for 10min, if the pressure is always higher than 10Kpa, then the pump rotation speed is determined to be normal, if the rotation speed is normal, then whether the feedback of the switching valve e is normal is detected, if the feedback is normal, then whether the feedback of the switching valve d is normal is further detected, if the feedback is also normal, then whether the feedback of the stop valve B is normal is detected, if the feedback is normal, the B end of the switching valve e is blocked by a plug, meanwhile, the air-saving pump is started for 10min, whether the pressure can be reduced to 10Kpa is observed, if the feedback can be reduced to 10Kpa, then the air-saving pump is connected to the B end of the switching valve d through a hose, the air-saving pump is restarted, whether the pressure can be reduced to 10Kpa is observed, if the connection between the stop valve B and the, when the pressure is reduced to 10Kpa, the sealing performance of the switching valve b is reduced due to the fault, and the sealing element needs to be replaced. The diagnosis of pressure abnormity requires that an astronaut participates in the operation for 3 times, tools such as a vacuum plug and a detection hose tool are adopted, and the astronaut sends an instruction by using a handheld device every time. The diagnostic device can visually inform the astronaut of what working mode the astronaut system is in, and what fault mode or modes are possible to occur in the current test information through diagnostic reasoning when the astronaut is in fault. To further determine which operations need to be done to determine the fault, each step operates the security measures of attention; after the operation is completed, how to restore the previous operation state and the like is required to obtain new test information data.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting the same, and although the present invention is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (8)
1. A space environment fault diagnosis device is characterized by comprising a fault diagnosis instrument and a handheld device, wherein the handheld device is connected with the fault diagnosis instrument, and the fault diagnosis instrument is accessed to an internal bus of a subsystem of an environment control and life support system;
the fault diagnosis instrument is used for acquiring real-time data of the subsystems, wherein the real-time data comprises subsystem analog quantity, remote measurement parameters and fault codes;
the internal bus of the life support system subsystem can obtain data of the subsystem in real time, and meanwhile, the ground expert base reasoning knowledge is used for guiding a astronaut to eliminate faults and realizing fault positioning;
the fault diagnosis instrument comprises a portable notebook computer and a switching box, wherein the portable notebook computer is connected with an internal bus of the life support system subsystem through the switching box;
the internal bus of the subsystem of the life support system is connected with a plurality of controllers, and the controllers are connected with the sensors of the subsystems.
2. A space environment fault diagnosis method based on the space environment fault diagnosis device according to claim 1, characterized by comprising the steps of:
1) the fault diagnosis instrument is communicated with an internal bus of a life support system subsystem to acquire real-time data on the bus;
2) judging the occurrence of the fault according to the real-time data;
3) after the fault occurs, starting fault phenomenon confirmation: selecting and confirming a plurality of current fault phenomena through a fault diagnosis instrument, or judging through a fault analysis code of the fault diagnosis instrument;
4) after the fault phenomenon is confirmed, the fault diagnosis instrument acquires relevant historical/current relevant data, deduces and prompts component assemblies possibly having faults by combining a diagnosis strategy, and gives external conditions participating in the maintenance;
5) the fault diagnosis instrument prompts an operation method;
6) after the operation is finished, checking and confirming, including checking the change of parameters or phenomena;
7) matching the confirmation result with an expert knowledge base of the fault diagnosis instrument, adding or deleting suspected fault assemblies, generating next operation prompts, returning to the step 5), and continuously confirming the final fault assemblies;
8) after the fault component assembly is positioned, providing relevant information of the positioning component assembly and prompting the installation position of the fault component assembly; directly switching to step 13 when maintenance is not needed);
9) when maintenance is needed, a maintenance strategy is generated;
10) in the maintenance process, the diagnostic instrument prompts an astronaut to operate;
11) after the operation of the astronaut is finished, prompting the astronaut of the content to be confirmed, and if the parameters can be obtained in real time through a diagnostic instrument, automatically confirming by software;
12) matching the confirmation result with an expert knowledge base, determining whether the maintenance process is correct, entering the next step if the maintenance process is correct, and finishing diagnosis; if not, returning to the step 10);
13) after the maintenance is finished, generating statistical information of the diagnosis and maintenance process; and giving related suggestions in the process of subsequent tasks.
3. A space environment fault diagnosis method according to claim 2, characterized in that in step 2), the fault occurrence judgment is that the fault occurrence is sensed through olfaction, hearing and visual perception of an astronaut or is prompted through a fault diagnosis instrument.
4. A space environment fault diagnosis method as claimed in claim 2, wherein in the step 10), the prompting method for prompting the operation steps of the astronaut is pictures, files and videos, and if instruction sending is involved, instruction codes or names and sending modes are given, and the sending modes are applications to the ground or autonomous sending through handheld equipment.
5. A space environment fault diagnosis method according to claim 2, wherein in step 4), when participating in the external conditions of the maintenance, the prompting modes comprise pictures and characters; and the astronaut confirms whether the external conditions are met, and then the subsequent diagnosis process is started.
6. A space environment fault diagnosis method according to claim 2, characterized in that in step 5), if command transmission is involved, command codes or names and transmission modes are given, and the command codes or names and transmission modes are applied to the ground or are autonomously transmitted through handheld equipment.
7. A space environment fault diagnosis method according to claim 2, characterized in that in step 6), the parameters are obtained in real time by a fault diagnosis instrument and automatically confirmed.
8. A space environment fault diagnosis method according to claim 2, wherein in step 8), names, numbers and three-dimensional appearances of the positioning component parts are given, and installation positions of the component parts are prompted in the form of figures and characters.
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