CN112304653A - Universal comprehensive test method and system for satellite test - Google Patents
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Abstract
The invention discloses a general comprehensive test method for satellite test, which comprises the following steps: a self-testing system in the satellite to be tested performs self-testing on the satellite to be tested to obtain a self-testing result; the ground test system carries out ground test on the satellite to be tested to obtain a ground test result; and verifying the self-testing result based on the ground testing result to obtain the comprehensive testing result of the satellite to be tested. The invention also discloses a general comprehensive test method for satellite test. In the method, aiming at the requirements of rapid integration and rapid test of the small satellite, the research current situation analysis of the domestic and foreign rapid test technology of the satellite is summarized, the actual situation of the project is combined, the optimization technology of the test flow of the satellite is researched, the rapid test method and the rapid test system combining the internal test and the external test are provided, the overall scheme demonstration of the rapid test system of the satellite is completed, the composition and the technical approach of the rapid test system of the satellite are determined, and the technical support is provided for achieving the rapid test of the satellite.
Description
Technical Field
The invention relates to the technical field of space. And more particularly, to a universal integrated test method and system for satellite testing.
Background
The testing work of the satellite is carried out through the whole process of development and generation of the satellite, wherein the testing time directly determines the development and production period of the satellite. With the steady development of aerospace industry in China, the number of spacecrafts is more and more, and the testing efficiency needs to be improved while the testing quality of the spacecrafts is ensured. Generally, according to project planning, final assembly, integration and testing (AIT) is completed within 2-3 years, which puts a very high demand on the testing efficiency of the satellite. According to conventional satellite testing techniques, a satellite takes at least several months to complete production and testing, and has become unable to meet the stringent development and production cycle requirements.
In order to improve the testing efficiency of satellites, the rapid AIT of foreign spacecraft has been developed for many years and has performed very well, and the rapid AIT of foreign spacecraft has gradually shifted from experimental verification to practical application. For example, in the rapid AIT proposed in the united states "rapid response space" (ORS) program, a series of rapid AIT demonstration trials were conducted for the testing requirements of ORS satellites. In the AIT test protocol, rapid AIT takes on average about 22 h. Because of the adoption of automatic testing, the testing time is more stable, and the automatic testing efficiency is greatly improved. Meanwhile, the description of the final assembly operation flow is graphical, and the final assembly efficiency can be improved compared with a document which uses a plurality of characters to describe operation steps by matching with as few characters as possible. However, in the automated test, the total assembly operation time fluctuates greatly due to the influence of the training degree of the personnel and the technical level of the total assembly team rather than the influence of the change of the satellite configuration.
Therefore, a research on a rapid testing technology of a small satellite is urgently needed, and a general comprehensive testing method and a general comprehensive testing system for satellite testing are provided to achieve the aims of rapid integration, testing and generation of the satellite.
Disclosure of Invention
The invention aims to provide a universal comprehensive test method for satellite test, so as to achieve the aims of rapid integration, test and generation of satellites.
In order to achieve the purpose, the invention adopts the following technical scheme:
a universal integrated test method for satellite testing, the method comprising:
a self-testing system in the satellite to be tested performs self-testing on the satellite to be tested to obtain a self-testing result;
the ground test system carries out ground test on the satellite to be tested to obtain a ground test result; and
and verifying the self-test result based on the ground test result to obtain a comprehensive test result of the satellite to be tested.
Optionally, the ground testing of the satellite to be tested by the ground testing system includes:
acquiring remote measurement parameters by a satellite to be measured;
the satellite to be tested sends the acquired remote measurement parameters to a ground test system; and
and the ground test system interprets the telemetering parameters to obtain the ground test result.
Optionally, the verifying the self-test result based on the ground test result, and the obtaining the comprehensive test result of the satellite to be tested includes:
taking the self-test result as a reference comprehensive test result; and
and the satellite to be tested receives the ground test result and judges whether the reference comprehensive test result is consistent with the ground test result or not, wherein if the reference comprehensive test result is consistent with the ground test result, the reference comprehensive test result is taken as the comprehensive test result.
Further optionally, if the reference comprehensive test result is inconsistent with the ground test result, the ground test result is taken as the comprehensive test result.
Optionally, if the reference comprehensive test result is inconsistent with the ground test result, determining that the test fails, and performing the test again.
Optionally, before the self-testing system in the satellite under test performs self-testing on the satellite under test, the method further includes:
and performing satellite component and subsystem quality identification test on the satellite to be tested, wherein the quality identification test adopts a qualified component, a standard interface, a modularized structure and a repeatable process.
Optionally, when the satellite to be tested includes a plurality of satellites, before the self-test system in the satellite to be tested performs self-test on the satellite to be tested, the method further includes:
judging the type of the required quality identification test based on the requirement;
selecting one satellite to be tested in the plurality of satellites to be tested as a standard satellite to be tested;
performing all types of quality identification tests on the standard satellite to be detected to obtain a standard quality identification template; and
and performing quality identification tests on other satellites to be detected except the standard satellite to be detected in the satellites to be detected based on the standard quality identification template.
Optionally, the method further comprises:
respectively establishing an equivalent device of a component or a system of the satellite to be tested; and
and during testing, replacing the corresponding component or system with the equivalent device.
It is an object of the present invention to provide a universal integrated test system for satellite testing.
A universal integrated test system for satellite testing, the system comprising:
the self-testing system is positioned on the satellite to be tested and is configured to carry out self-testing on the satellite to be tested to obtain a self-testing result;
the ground test system is configured to perform ground test on the satellite to be tested to obtain a ground test result; and
and the comprehensive test system is configured to verify the self-test result based on the ground test result to obtain a comprehensive test result of the satellite to be tested.
Optionally, the ground test system comprises:
an acquisition unit configured to acquire a telemetry parameter from a satellite to be measured;
a transmitting unit configured to transmit the acquired telemetry parameters to a ground test system; and
and the judging unit is configured to interpret the telemetry parameters and acquire the ground test result.
The invention has the following beneficial effects:
in the method, aiming at the requirements of rapid integration and rapid test of the small satellite, the research current situation analysis of the domestic and foreign rapid test technology of the satellite is summarized, the actual situation of the project is combined, the optimization technology of the test flow of the satellite is researched, the rapid test method and the rapid test system combining the internal test and the external test are provided, the overall scheme demonstration of the rapid test system of the satellite is completed, the composition and the technical approach of the rapid test system of the satellite are determined, and the technical support is provided for achieving the rapid test of the satellite.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 shows a flowchart of a general comprehensive test method according to an embodiment of the present invention.
Fig. 2 shows a block diagram of a general integrated test system according to an embodiment of the present invention.
Fig. 3 is a schematic diagram illustrating a hardware system structure of a general integrated test system according to an embodiment of the present invention.
Fig. 4 shows a connection diagram of the general integrated test system in the embodiment of the present invention.
FIG. 5 shows a generic integrated test system test software component and system data flow in an embodiment of the invention.
Detailed Description
In order to make the technical solutions of the present invention better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
At present, the satellite test period (from the complete set of single satellite to the complete integrated test of the whole satellite) in China is generally long, the test process is repeated frequently, fault location is difficult after faults occur, and the test period is generally as long as several months. China begins to pay attention to research on a spacecraft rapid response system and a spacecraft rapid test technology in recent years, but related research is in a starting stage.
The method is mainly based on the current development state, aims at the requirements of rapid integration and rapid test of the small satellites, summarizes the research current situation analysis of the domestic and foreign satellite rapid test technology, combines the practical situation of engineering, researches the optimization technology of the satellite test flow, provides the rapid test method and the rapid test system combining the internal test and the external test, completes the overall scheme demonstration of the satellite rapid test system, determines the composition and the technical approach of the satellite rapid test system, and provides technical support for the rapid test of the satellites. Specifically, the fast response concept and the fast AIT research are developed from the design concept and the design system of the spacecraft, and the requirements of fast testing and processing of the spacecraft are met through automation, universalization and the like of a ground testing system.
As shown in fig. 1, the present application provides a general integrated test method for satellite testing. The method comprises the following steps: a self-testing system in the satellite to be tested performs self-testing on the satellite to be tested to obtain a self-testing result; the ground test system carries out ground test on the satellite to be tested to obtain a ground test result; and verifying the self-testing result based on the ground testing result to obtain the comprehensive testing result of the satellite to be tested.
In the application, aiming at the front edge problem of the rapid test of the microsatellite, a new idea and a new scheme for the rapid test of the satellite are provided, wherein the new idea and the new scheme are combined by internal test and external test, and a test flow optimization technology and an automatic test technology are combined to provide technical support for the mass production and the rapid test of the satellite.
In the application, the rapid spacecraft testing technology at home and abroad is deeply researched and analyzed through literature research and visit exchange. The overseas key research objects are a rapid response Space plan of the United states and a series of rockets and satellites developed by Space X; the domestic key research unit is Harbin industrial university satellite institute and Shanghai satellite engineering research institute, and forms a current state analysis report of the satellite rapid test technology at home and abroad after research.
In the traditional satellite test, the satellite does not have data interpretation capability, and all telemetering parameters need to be sent to ground equipment for interpretation by the ground equipment. Meanwhile, the low telemetry downlink rate prevents the satellite from being tested quickly. For the above situation, to realize the rapid test of the satellite, on one hand, the satellite itself needs to have a strong self-test capability, and on the other hand, the ground test system needs to support the rapid test. In the application, a rapid test system for a satellite is provided by taking the test system of an airplane as a reference.
The airplane is an important component in the aircraft, and the testing time of the airplane is far shorter than the time required by satellite testing. By taking the idea of airplane testing as a reference, a satellite rapid testing system combining internal testing and external testing is constructed. It should be noted that, since the satellite internal measurement relates to the design of the satellite itself, the internal measurement technology itself is not studied in the present application, but only from the architecture of the internal measurement and the external measurement.
In an alternative embodiment, the ground test system for ground testing the satellite to be tested includes: acquiring remote measurement parameters by a satellite to be measured; the satellite to be tested sends the acquired remote measurement parameters to a ground test system; and the ground test system judges and reads the remote measurement parameters to obtain a ground test result.
In yet another optional embodiment, verifying the self-test result based on the ground test result, and obtaining the comprehensive test result of the satellite to be tested includes: taking the self-testing result as a reference comprehensive testing result; and the satellite to be tested receives the ground test result and judges whether the reference comprehensive test result is consistent with the ground test result.
According to the judgment result, determining the comprehensive test result comprises the following steps:
1) and if the reference comprehensive test result is consistent with the ground test result, taking the reference comprehensive test result as a comprehensive test result.
2) And if the reference comprehensive test result is inconsistent with the ground test result, taking the ground test result as a comprehensive test result.
In an optional example, if the reference comprehensive test result is inconsistent with the ground test result, the test is judged to fail, and the test is performed again.
In the application, the test efficiency is improved and the test accuracy is ensured through the comprehensive verification of the self-test result and the ground test result.
In order to achieve the purpose of rapid testing, the conventional satellite testing process needs to be optimized. Much research and effort has been devoted in the united states to this regard and practical verification has been made. The core idea can be summarized as follows: 1) the satellite component and subsystem quality identification test is completed in advance, and then a qualified component, a standard interface, a modular structure and a repeatable process are used for integrating and testing one satellite according to requirements, so that the AIT time can be greatly reduced. 2) For the serialized and batched microsatellites, for the first satellite, all quality identification experiments are recommended to be carried out according to the standard, and after the same satellite production experience is obtained, the test flow of the subsequent satellite can be properly reduced, so that the aims of quickly producing and quickly testing the satellite are fulfilled. 3) The method is characterized in that satellite component or system equivalents are built, and the equivalents can be equivalently replaced for real components or systems, so that parameters of the whole system can be tested under the condition that a certain satellite component or subsystem is replaced, and the effect of rapidly testing the satellite component or the system is achieved.
Based on the above, the following alternative embodiments are proposed in the present application.
In an optional embodiment, before the self-test system in the satellite under test performs self-test on the satellite under test, the method further includes: and performing satellite component and subsystem quality identification test on the satellite to be tested, wherein the quality identification test adopts a qualified component, a standard interface, a modularized structure and a repeatable process.
In yet another optional embodiment, when the satellite under test includes a plurality of satellites, before the self-test system in the satellite under test performs self-test on the satellite under test, the method further includes: judging the type of the required quality identification test based on the requirement; selecting one to-be-tested satellite from a plurality of to-be-tested satellites as a standard to-be-tested satellite; performing all types of quality identification tests on a standard satellite to be detected to obtain a standard quality identification template; and performing quality identification tests on other satellites to be detected except the standard satellite to be detected in the satellites to be detected based on the standard quality identification template.
In yet another optional embodiment, the method further comprises: respectively establishing an equivalent device of a component or a system of the satellite to be tested; and during testing, replacing the corresponding part or system with the equivalent device.
As shown in fig. 2, in the present application, a general integrated test system for satellite testing is provided. The system comprises: the self-testing system is positioned on the satellite to be tested and is configured to carry out self-testing on the satellite to be tested to obtain a self-testing result; the ground test system is configured to carry out ground test on the satellite to be tested to obtain a ground test result; and the comprehensive test system is configured to verify the self-test result based on the ground test result and acquire the comprehensive test result of the satellite to be tested.
In an alternative embodiment, a ground testing system comprises:
an acquisition unit configured to acquire a telemetry parameter from a satellite to be measured;
a transmitting unit configured to transmit the acquired telemetry parameters to a ground test system; and
and the judging unit is configured to judge and read the remote measuring parameters and acquire a ground test result.
In the application, on the basis of the research of the current situation of the rapid test technology and the research of a rapid test system, the overall scheme demonstration of the rapid satellite test system is developed, the overall architecture and the system composition of the rapid satellite test system are determined, and the technical implementation way of each system is planned. In summary, since the satellite fast test technology relates to the satellite itself, the satellite external test equipment and the satellite test process, it is a systematic system work to realize the satellite fast test.
The general integrated test system adopts a distributed hardware system structure according to the design principles of generalization, automation and standardization according to the analysis of system function requirements so as to adapt to the test requirements of satellites of various models, and is mainly introduced for rapid test.
I. System hardware overall scheme design
As shown in fig. 3, according to the analysis of the system functional requirements, the general integrated test system mainly comprises a power supply system, a general measurement and control system, a general test combination (bus test), an excitation system, a load simulation system, a bus monitoring system, and a special system.
The universal integrated test system adopts a distributed hardware system structure according to the design principles of generalization, automation and standardization so as to adapt to the test requirements of satellites of various models. In the whole system, the master control system is responsible for maintaining the data flow of the whole ground comprehensive test platform, assisting a tester to complete the test work and managing other test equipment (such as a power supply system, a general measurement and control system, bus monitoring and the like). The network environment is connected with the main control equipment and the sub-system test equipment through a standard test communication protocol to form a finished satellite ground comprehensive test platform, so that a satellite general electrical comprehensive test system for unified command and scheduling is formed.
According to task requirements, through overall planning, the general comprehensive test system is composed of a general control monitoring system, a cloud storage system, a portable cloud system, a power supply system, a general measurement and control system, a general test combination, an excitation system, a load simulation system, a special system, a bus monitoring system and an internal cable network, the distributed general comprehensive test system is interconnected through a local area network link, and the overall block diagram of equipment is shown in fig. 4. The general control equipment and the subsystem test equipment of the general integrated test system are interconnected through an internal measurement and control Ethernet, the measurement and control Ethernet is composed of gigabit networks (gigabit Ethernet is mainly a gigabit optical fiber as an auxiliary), and data exchange is carried out between the general control equipment and the subsystem test equipment according to an internal communication protocol of the general integrated test system.
In fig. 3, the devices other than the signal switching combination are designed according to the general principle. The signals and definitions of satellites of different models are different, and matching is carried out by designing different signal switching combinations and testing cables.
Structurally, the general comprehensive test system is designed to adopt an assembly box structure. Except a data center, a master control monitoring subsystem, a power supply system, a general test combination, a bus monitoring system, a special system, a general measurement and control system and the like can form a relatively independent assembly box. The adoption of the assembly box structure is beneficial to flexible combination of the devices and convenient transportation and carrying.
Overall scheme design of system software
Figure 5 shows a satellite integrated test system data flow. The satellite testing software runs on the master control server and the subsystem controllers and mainly comprises master control software, data acquisition and control software, data transmission data processing software and the like. The functions implemented by the respective software are as follows.
(1) The master control software runs in a server of the master control monitoring system, and the functions of the master control software comprise: controlling and transferring each subsystem software, receiving and displaying response data; configuring a remote control instruction, generating a test task and a sequence and sending the test task and the sequence; receiving and analyzing the telemetering data, displaying and issuing the data and other services; the system has the functions of user management, test system management, automatic generation of test sequences, automatic testing, test data storage and management.
(2) The software is mainly used for controlling an instrument board card in the universal test combination and completing the satellite comprehensive test in a wired test mode. The automatic test software provides functions of test project management, system initialization, test execution, satellite-ground communication, board card driving, data management, instrument management and the like, and can realize virtualization and reconfigurable configuration of test hardware equipment. The technical realization method comprises the following steps: test Description specifications in IEEE are used for reference, and Test process management software with configurable capacity is designed by combining an interaction method and instruction characteristics of a physical hardware entity.
(3) The data processing and analyzing software has the main functions of analyzing the working states of all subsystems and single machines in the satellite testing process by utilizing various different data model methods and monitoring various performance indexes of the satellite on line in near real time and extremely fast response capability. The technical realization method comprises the following steps: the method is realized by utilizing a data-driven analysis and calculation method through high-performance calculation methods such as machine intelligence, scientific calculation visualization, memory modeling, memory calculation and the like.
(4) The data monitoring and issuing terminal software has the main function of serving as a monitoring window of a system, provides a whole set of data visualization method for a test engineer or designer, and helps to snoop any information in the satellite complex test process. The technical realization method comprises the following steps: and combining a data visualization method, fusing data characteristics and visualization technical characteristics in a satellite testing link, and embedding integrated display capabilities of Pro-E, 3DMax, TeeChart, BCGCHart and the like into system software to realize full-dimensional presentation of data.
(5) The fault diagnosis software has the main functions of helping designers and engineers to deeply mine valuable data in mass test data, is different from shallow interpretation means, and is applied to various test links of a satellite with deeper and thorough diagnosis and analysis capability. The technical realization method comprises the following steps: by adopting an open framework design idea, combining expert knowledge, a physical model and a data driving method and combining a distributed cloud computing technology, deduction and iteration are carried out in the provided safe sandbox environment, and fault detection, positioning and early warning are realized.
The integrated unit in the above embodiments, if implemented in the form of a software functional unit and sold or used as a separate product, may be stored in the above computer-readable storage medium. Based on such understanding, the technical solution of the present application may be substantially implemented or a part of or all or part of the technical solution contributing to the prior art may be embodied in the form of a software product stored in a storage medium, and including instructions for causing one or more computer devices (which may be personal computers, servers, network devices, or the like) to execute all or part of the steps of the method described in the embodiments of the present application.
In the above embodiments of the present application, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments.
In the several embodiments provided in the present application, it should be understood that the disclosed client may be implemented in other manners. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units is only one type of division of logical functions, and there may be other divisions when actually implemented, for example, a plurality of units or components may be combined or may be integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, units or modules, and may be in an electrical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present application may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit. The integrated unit can be realized in a form of hardware, and can also be realized in a form of a software functional unit.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (10)
1. A universal integrated test method for satellite testing, the method comprising:
a self-testing system in the satellite to be tested performs self-testing on the satellite to be tested to obtain a self-testing result;
the ground test system carries out ground test on the satellite to be tested to obtain a ground test result; and
and verifying the self-test result based on the ground test result to obtain a comprehensive test result of the satellite to be tested.
2. The method of claim 1, wherein the ground test system performing ground tests on the satellite under test comprises:
acquiring remote measurement parameters by a satellite to be measured;
the satellite to be tested sends the acquired remote measurement parameters to a ground test system; and
and the ground test system interprets the telemetering parameters to obtain the ground test result.
3. The method of claim 1, wherein the verifying the self-test result based on the ground test result and obtaining the integrated test result of the satellite under test comprises:
taking the self-test result as a reference comprehensive test result;
the satellite to be tested receives the ground test result and judges whether the reference comprehensive test result is consistent with the ground test result or not; and
and if the reference comprehensive test result is consistent with the ground test result, taking the reference comprehensive test result as the comprehensive test result.
4. The method of claim 3, wherein the ground test result is taken as the combined test result if the reference combined test result is inconsistent with the ground test result.
5. The method of claim 3, wherein if the reference integrated test result is inconsistent with the ground test result, determining that the test failed and performing the test again.
6. The method of claim 1, wherein before the self-test system in the satellite under test performs self-test on the satellite under test, the method further comprises:
and performing satellite component and subsystem quality identification test on the satellite to be tested, wherein the quality identification test adopts a qualified component, a standard interface, a modularized structure and a repeatable process.
7. The method of claim 1, wherein when the satellite under test comprises a plurality of satellites under test, before the self-test system in the satellite under test performs self-test on the satellite under test, the method further comprises:
judging the type of the required quality identification test based on the requirement;
selecting one satellite to be tested in the plurality of satellites to be tested as a standard satellite to be tested;
performing all types of quality identification tests on the standard satellite to be detected to obtain a standard quality identification template; and
and performing quality identification tests on other satellites to be detected except the standard satellite to be detected in the satellites to be detected based on the standard quality identification template.
8. The method of claim 1, further comprising:
respectively establishing an equivalent device of a component or a system of the satellite to be tested; and
and during testing, replacing the corresponding component or system with the equivalent device.
9. A universal integrated test system for satellite testing, the system comprising:
the self-testing system is positioned on the satellite to be tested and is configured to carry out self-testing on the satellite to be tested to obtain a self-testing result;
the ground test system is configured to perform ground test on the satellite to be tested to obtain a ground test result; and
and the comprehensive test system is configured to verify the self-test result based on the ground test result to obtain a comprehensive test result of the satellite to be tested.
10. The universal integrated test system for satellite testing of claim 9, wherein the ground test system comprises:
an acquisition unit configured to acquire a telemetry parameter from a satellite to be measured;
a transmitting unit configured to transmit the acquired telemetry parameters to a ground test system; and
and the judging unit is configured to interpret the telemetry parameters and acquire the ground test result.
Priority Applications (1)
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114189272A (en) * | 2021-11-18 | 2022-03-15 | 北京微纳星空科技有限公司 | Comprehensive test system of microsatellite |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006256376A (en) * | 2005-03-15 | 2006-09-28 | Mitsubishi Electric Corp | Satellite testing device |
| CN102590733A (en) * | 2012-03-20 | 2012-07-18 | 中国人民解放军国防科学技术大学 | Circuitry built-in test device based on boundary scanning mechanism |
| US20140232595A1 (en) * | 2011-06-30 | 2014-08-21 | Tufts University | System and method for wireless collaborative verification of global navigation satellite system measurements |
| CN106314825A (en) * | 2016-10-12 | 2017-01-11 | 深圳航天东方红海特卫星有限公司 | Parallel and automatic integrated testing system for satellites |
| CN107588921A (en) * | 2016-07-08 | 2018-01-16 | 北京空间技术研制试验中心 | Rudders pneumatic power parameter measuring method |
| CN107612610A (en) * | 2017-08-31 | 2018-01-19 | 航天东方红卫星有限公司 | A kind of spaceborne TT＆C Transponder self-testing system and method based on slave computer |
| CN109344085A (en) * | 2018-11-14 | 2019-02-15 | 上海微小卫星工程中心 | A kind of method and system for analyzing satellite test data |
| CN110308381A (en) * | 2019-05-29 | 2019-10-08 | 深圳市紫光同创电子有限公司 | A kind of built-in self-test method and system of FPGA input and output logic module |
| CN110865556A (en) * | 2019-12-03 | 2020-03-06 | 中国科学院软件研究所 | Virtual satellite, and test platform and method for software and algorithm based on virtual satellite |
-
2020
- 2020-09-07 CN CN202010928467.8A patent/CN112304653A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006256376A (en) * | 2005-03-15 | 2006-09-28 | Mitsubishi Electric Corp | Satellite testing device |
| US20140232595A1 (en) * | 2011-06-30 | 2014-08-21 | Tufts University | System and method for wireless collaborative verification of global navigation satellite system measurements |
| CN102590733A (en) * | 2012-03-20 | 2012-07-18 | 中国人民解放军国防科学技术大学 | Circuitry built-in test device based on boundary scanning mechanism |
| CN107588921A (en) * | 2016-07-08 | 2018-01-16 | 北京空间技术研制试验中心 | Rudders pneumatic power parameter measuring method |
| CN106314825A (en) * | 2016-10-12 | 2017-01-11 | 深圳航天东方红海特卫星有限公司 | Parallel and automatic integrated testing system for satellites |
| CN107612610A (en) * | 2017-08-31 | 2018-01-19 | 航天东方红卫星有限公司 | A kind of spaceborne TT＆C Transponder self-testing system and method based on slave computer |
| CN109344085A (en) * | 2018-11-14 | 2019-02-15 | 上海微小卫星工程中心 | A kind of method and system for analyzing satellite test data |
| CN110308381A (en) * | 2019-05-29 | 2019-10-08 | 深圳市紫光同创电子有限公司 | A kind of built-in self-test method and system of FPGA input and output logic module |
| CN110865556A (en) * | 2019-12-03 | 2020-03-06 | 中国科学院软件研究所 | Virtual satellite, and test platform and method for software and algorithm based on virtual satellite |
Non-Patent Citations (3)
| Title |
|---|
| 张彤等: "飞行器运动参数的光学外测与组合导航内测比对分析", 《计算机工程与应用》 * |
| 理查德·布洛克利等: "《航空航天科技出版工程.3，结构技术》", 北京理工大学出版社 * |
| 马文来等: "《航空概论》", 31 July 2018, 中国民航出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114189272A (en) * | 2021-11-18 | 2022-03-15 | 北京微纳星空科技有限公司 | Comprehensive test system of microsatellite |
| CN114189272B (en) * | 2021-11-18 | 2024-01-16 | 北京微纳星空科技有限公司 | Comprehensive test system of microsatellite |
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