CN111089741A - Helicopter satellite communication system reliability test profile design method - Google Patents
Helicopter satellite communication system reliability test profile design method Download PDFInfo
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- CN111089741A CN111089741A CN201911201997.6A CN201911201997A CN111089741A CN 111089741 A CN111089741 A CN 111089741A CN 201911201997 A CN201911201997 A CN 201911201997A CN 111089741 A CN111089741 A CN 111089741A
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- 238000004891 communication Methods 0.000 title claims abstract description 56
- 238000012360 testing method Methods 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000013461 design Methods 0.000 title claims abstract description 8
- 238000011161 development Methods 0.000 claims abstract description 14
- 238000009434 installation Methods 0.000 claims abstract description 4
- 238000002791 soaking Methods 0.000 claims description 12
- 230000007613 environmental effect Effects 0.000 claims description 7
- 238000013142 basic testing Methods 0.000 claims description 3
- 238000010408 sweeping Methods 0.000 claims description 3
- 230000002194 synthesizing effect Effects 0.000 claims description 2
- 230000035882 stress Effects 0.000 description 20
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000013095 identification testing Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/008—Subject matter not provided for in other groups of this subclass by doing functionality tests
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
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Abstract
The invention discloses a design method of a reliability test profile of a helicopter satellite communication system, which respectively determines N-type helicopter environment conditions suitable for product installation and electric stress requirements of various helicopter satellite communication devices according to development requirements, and determines the application time and the number of test points, electric stress and temperature stress values, humidity stress and vibration stress values of various stresses.
Description
Technical Field
The invention relates to the field of satellite communication, in particular to a design method of a reliability test profile suitable for a helicopter satellite communication system.
Background
The helicopter satellite communication system is composed of various helicopter-mounted satellite communication devices and ground equipment, wherein the helicopter-mounted satellite communication devices are mainly installed on helicopters of different models. And the over-the-horizon communication services such as data, voice, video and the like are provided between the helicopter and a ground base.
Helicopter satellite communication system contains helicopter satellite communication equipment many kinds, reliability index height, the flexible operation is convenient, needs can satisfy the environmental requirement of various different helicopters, or the different mounted position of the same kind of helicopter. According to the GJB 899A regulation, the reliability test adopts a comprehensive environment test profile, and each stress value is determined according to the field use type of equipment, the installation position of the equipment and the expected use condition. For the multipurpose device GJB 899A, only a multipurpose device profile synthesis method suitable for a fixed wing aircraft is given, and the method is not suitable for helicopter profile synthesis. According to the traditional test scheme, each airborne product in the helicopter satellite communication system needs to be tested for multiple times, and the existing reliability identification test method has the defects of high organization difficulty, long period, high cost and large number of test pieces, and is difficult to meet the requirements of reliability development and identification of the helicopter satellite communication system.
Disclosure of Invention
The purpose of the invention is as follows: the invention mainly solves the problem of difficulty in reliability test of a helicopter satellite communication system, and provides a method for designing a reliability test profile of the helicopter satellite communication system. The environment requirements of multiple helicopters can be met by one-time testing, the examination requirements of multiple helicopter-mounted satellite communication equipment are met, and the cost-efficiency ratio of the testing is effectively improved.
The technical scheme is as follows: in order to achieve the purpose, the invention adopts the technical scheme that:
a design method for a reliability test profile of a helicopter satellite communication system comprises the following steps:
step 1, respectively determining the environmental conditions of the N-type helicopter suitable for the product according to the development requirements.
And 2, respectively determining the electrical stress requirements of various helicopter satellite communication equipment according to the development requirements.
A composed helicopter satellite communications system is obtained as shown in fig. 1. The system comprises UHF frequency band and Ku frequency band two-type helicopter-mounted satellite communication equipment, the UHF frequency band helicopter-mounted satellite communication equipment can be installed on a 4-type helicopter, and the Ku frequency band helicopter-mounted satellite communication equipment can be installed on a 2-type helicopter.
And 3, drawing a basic test profile according to the development requirement and the GJB 899A requirement, and determining the application time of each stress and the number of test points.
Step 4, determining the magnitude of the electrical stress and the temperature stress: should be selected according to the lowest and highest values of various requirements, and should not exceed the working limit of the product.
Step 5, determining the humidity stress: the most severe value is selected according to the development requirement or the technical condition requirements of various helicopter environments.
Step 6, determining the vibration stress magnitude: the helicopter-borne satellite communication equipment vibration comprises sine continuous logarithmic scanning vibration and sine fixed-frequency vibration, and no vibration stress is applied during cold soaking and hot soaking.
And 7, executing the magnitude and the application time of the sine continuous logarithmic scanning vibration according to the GJB 899A related requirements, and executing the operation once every 1 hour.
And 8, selecting N fixed frequencies in total according to the functional vibration test requirements of each helicopter by the sine fixed frequency vibration, and if N is greater than 2, combining the sine fixed frequency with frequency intervals smaller than 10%, and keeping the frequency with a higher reserve value. And then determining the number M of sinusoidal fixed frequency vibrations applied in the test.
And 9, dividing the M fixed-frequency vibrations into I groups, wherein the frequency number of each group is not more than 4, sequentially synthesizing the I groups in a fixed frequency mode after frequency sweeping, and respectively applying the I groups once in a low-temperature working section and a high-temperature working section of each cycle, wherein the application time is according to the service communication time requirement of the satellite communication equipment.
Preferably: step 9 each application time is between 3Min and 5 Min.
Compared with the prior art, the invention has the following beneficial effects:
1) the method replaces the traditional comprehensive reliability test of the helicopter satellite communication system, can reduce the test times, and saves the test cost and test pieces.
2) The method comprehensively considers the environmental characteristics of various helicopters and the use requirements of airborne satellite communication equipment, provides a specific method for selecting and cutting environmental stress and applying time, and has strong operability.
3) The method fully considers the deployment requirement of the helicopter satellite communication system, and can fully examine the suitability and reliability indexes of the airborne satellite communication equipment through one-time test.
Drawings
FIG. 1 is a schematic diagram of a helicopter satellite communications system
FIG. 2 is a cross-sectional view of the reliability test of the Ku frequency range helicopter-mounted satellite communication system
FIG. 3 is a sectional view of the uhf band helicopter-mounted satellite communication system reliability test
Detailed Description
The present invention is further illustrated by the following description in conjunction with the accompanying drawings and the specific embodiments, it is to be understood that these examples are given solely for the purpose of illustration and are not intended as a definition of the limits of the invention, since various equivalent modifications will occur to those skilled in the art upon reading the present invention and fall within the limits of the appended claims.
A design method for a reliability test profile of a helicopter satellite communication system comprises the following steps:
step 1, respectively determining the environmental conditions of the N-type helicopter suitable for the product according to the development requirements.
And 2, respectively determining the electrical stress requirements of various helicopter satellite communication equipment according to the development requirements.
A composed helicopter satellite communications system is obtained as shown in fig. 1. The system comprises UHF frequency band and Ku frequency band two-type helicopter-mounted satellite communication equipment, the UHF frequency band helicopter-mounted satellite communication equipment can be installed on a 4-type helicopter, and the Ku frequency band helicopter-mounted satellite communication equipment can be installed on a 2-type helicopter.
And 3, drawing a basic test profile according to the development requirement and the GJB 899A requirement, and determining the application time of each stress and the number of test points.
Step 4, determining the magnitude of the electrical stress and the temperature stress: should be selected according to the lowest and highest values of various requirements, and should not exceed the working limit of the product.
1) Electrical stress
According to technical protocols and product specification requirements, the upper and lower limits of electric stress of the two types of equipment are consistent, the electric stress is not applied during cold soaking and hot soaking, and the tested object is started to be powered on and off for 3 times and works after the cold soaking and the hot soaking are finished.
2) Temperature stress
According to the technical protocol and the requirements of product specifications, the low-temperature working temperature of the two types of equipment is-40 ℃, the high-temperature working temperature is +60 ℃, the cold soaking temperature is-55 ℃, the hot soaking temperature is +70 ℃, and the equipment is applied for 1 hour in a reliability test according to a use profile.
Step 5, determining the humidity stress: the most severe value is selected according to the development requirement or the technical condition requirements of various helicopter environments.
According to technical protocols and product specification requirements, the method is executed according to the requirements of GJB 899A-2009 B3.7.2.5 section.
Step 6, determining the vibration stress magnitude: the helicopter-borne satellite communication equipment vibration comprises sine continuous logarithmic scanning vibration and sine fixed-frequency vibration, and no vibration stress is applied during cold soaking and hot soaking. The magnitude and application time of the sinusoidal continuous logarithmic scan vibration was performed according to the GJB 899A related requirements, once every 1 hour of operation. The sine fixed-frequency vibration is characterized in that N fixed frequencies in total are selected according to the functional vibration test requirements of various helicopters, if N is larger than 2, the sine fixed-frequency intervals are combined in a mode that the frequency intervals are smaller than 10%, and the frequency with a high reserve value is reserved. The number of sinusoidal fixed frequency vibrations M applied in the test is determined according to the above-described principle. Dividing M fixed-frequency vibrations into I groups, wherein the frequency number of each group is not more than 4, sequentially carrying out fixed-frequency synthesis on the I groups after frequency sweeping, respectively applying the I groups once in a low-temperature working section and a high-temperature working section of each cycle, and applying time each time is generally between 3Min and 5Min according to the service communication time requirement of the satellite communication equipment.
1) Ku frequency band helicopter-mounted satellite communication equipment
Sinusoidal continuous logarithmic scan: a sinusoidal continuous logarithmic sweep vibration from 5Hz to 500Hz and back to 5Hz was applied once every 1 hour of operation with a sweep vibration time of 14 minutes, depending on the mission requirements.
Sinusoidal fixed frequency vibration: according to the environmental technical conditions of the helicopter type 2, the main paddle frequency is 16Hz and 21.2Hz, and the acceleration is 0.6g and 1.5g respectively. And positioning the fixed-frequency vibration time for 3 minutes according to the communication requirement of the satellite communication equipment, wherein in the test, 16Hz sine fixed-frequency vibration and 21.2Hz sine fixed-frequency vibration are combined together and applied after the 3 rd frequency sweep vibration in each cycle.
2) UHF frequency range helicopter-mounted satellite communication equipment
Sinusoidal continuous logarithmic scan: applying sinusoidal continuous logarithmic scanning vibration from 5Hz to 500Hz and then returning to 5Hz once every 1 hour of work, wherein the scanning vibration time is 14 minutes according to the task requirement;
sinusoidal fixed frequency vibration: according to the environment technical conditions of the type 4 helicopter suitable for installation, the number of the fixed-frequency vibration is 9, and the fixed-frequency vibration is shown in the following table:
according to the principle, the frequency interval between 46.6Hz and 48Hz is less than 10%, 46.6Hz is reserved, and 48Hz is cut. And dividing the cut 8 fixed frequencies into 2 groups, positioning the fixed frequency vibration time for 3 minutes according to the communication requirement of the satellite-radio communication equipment, applying the first group after 1 st frequency sweep and 4 th frequency sweep of each cycle, and applying the second group after 3 rd frequency sweep and 6 th frequency sweep of each cycle.
Through the steps, the system reliability test section is drawn as shown in fig. 2 and 3.
According to the invention, the comprehensive stress profile for the system reliability test is obtained according to the environmental conditions of the various helicopters, and the problem of difficulty in reliability identification test of helicopter-borne satellite communication equipment in the helicopter satellite communication system is solved.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (2)
1. A design method for a reliability test profile of a helicopter satellite communication system is characterized by comprising the following steps:
step 1, respectively determining the environmental conditions of an N-type helicopter suitable for product installation according to development requirements;
step 2, respectively determining the electrical stress requirements of various helicopter satellite communication equipment according to the development requirements;
step 3, drawing a basic test profile according to the development requirement and the GJB 899A requirement, and determining the application time of each stress and the number of test points;
step 4, determining the magnitude of the electrical stress and the temperature stress: the method is characterized in that the method is selected according to the lowest value and the highest value in various requirements, and the working limit of a product is not exceeded;
step 5, determining the humidity stress: the most severe value is selected according to the development requirements or the requirements of various helicopter environment technical conditions;
step 6, determining the vibration stress magnitude: the vibration of the helicopter-borne satellite communication equipment comprises sine continuous logarithmic scanning vibration and sine fixed-frequency vibration, and no vibration stress is applied during cold soaking and hot soaking;
step 7, executing the magnitude and the application time of the sine continuous logarithmic scanning vibration according to the GJB 899A related requirements, and performing the operation once every 1 hour;
step 8, the sine fixed-frequency vibration should select N fixed frequencies in total according to the functional vibration test requirements of each helicopter, if N is larger than 2, the sine fixed-frequency intervals are combined at intervals smaller than 10%, and the frequency with a higher reserve value is kept; further determining the sine fixed frequency vibration number M applied in the test;
and 9, dividing the M fixed-frequency vibrations into I groups, wherein the frequency number of each group is not more than 4, sequentially synthesizing the I groups in a fixed frequency mode after frequency sweeping, and respectively applying the I groups once in a low-temperature working section and a high-temperature working section of each cycle, wherein the application time is according to the service communication time requirement of the satellite communication equipment.
2. The helicopter satellite communications system reliability test profile design method of claim 1, characterized by: step 9 each application time is between 3Min and 5 Min.
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