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MHT6018-2014 English PDF

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MHT6018-2014: (Aircraft ground static power supply)
Status: Valid
Standard IDUSDBUY PDFLead-DaysStandard Title (Description)Status
MH/T 6018-2014979 Add to Cart 6 days (Aircraft ground static power supply) Valid

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Basic data

Standard ID: MH/T 6018-2014 (MH/T6018-2014)
Description (Translated English): (Aircraft ground static power supply)
Sector / Industry: Civil Aviation Industry Standard (Recommended)
Word Count Estimation: 39,352
Date of Issue: 25/8/2014
Date of Implementation: 1/12/2014
Issuing agency(ies): Civil Aviation Administration of China

MHT6018-2014: (Aircraft ground static power supply)

---This is a DRAFT version for illustration, not a final translation. Full copy of true-PDF in English version (including equations, symbols, images, flow-chart, tables, and figures etc.) will be manually/carefully translated upon your order.
Aircraft ground solid-state power ICS 49.100 V 56 MH Civil Aviation Industry Standard of the People's Republic of China Replace MH/T 6018-1999 Aircraft ground static power supply 2014-08-25 released 2014-12-01 Implementation Issued by Civil Aviation Administration of China

Table of contents

Foreword...III 1 Scope...1 2 Normative references...1 3 Terms and definitions...2 4 Technical requirements...4 4.1 General...4 4.2 Conditions of use...4 4.3 Electrical Characteristics...4 4.4 Monitoring and protection devices...13 4.5 Safety requirements...17 5 Test method...19 5.1 Test environment, instruments and meters...19 5.2 Check appearance...19 5.3 Measurement quality...19 5.4 Measuring external dimensions...19 5.5 Checking the connector...20 5.6 Checking the emergency button...20 5.7 Input power supply test...20 5.8 Checking the load capacity of AC static variable power supply...20 5.9 Checking the load capacity of the DC static variable power supply...20 5.10 Check the starting inrush current...20 5.11 Measuring efficiency...20 5.12 Measuring power factor...21 5.13 AC steady-state output characteristics...21 5.14 Measuring AC transient output characteristics...23 5.15 Measuring DC steady-state output characteristics...24 5.16 Measuring DC transient output characteristics...24 5.17 Checking protection and monitoring devices...24 5.18 Electromagnetic compatibility test...26 5.19 Degree of protection...26 5.20 Withstand voltage test...26 5.21 Measuring insulation resistance...26 5.22 Measuring noise level...26 5.23 Low temperature test...26 5.24 High temperature test...27 5.25 Damp heat test...27 5.26 Mold growth test (parts)...27 5.27 Salt spray test (parts)...27 5.28 Rain test...27 6 Inspection Rules...27 6.1 Inspection classification...27 6.2 Inspection items...27 6.3 Judgment rules and re-inspection rules...30 7 Marks, instructions, packaging, transportation, storage...30 7.1 Logo...30 7.2 Random files...30 7.3 Packaging...30 7.4 Transport...31 7.5 Storage...31 Appendix A (Normative Appendix) Derating factor for altitudes above 1 000 m...32 Appendix B (Informative Appendix) Power Comprehensive Test System...33

Foreword

This standard was drafted in accordance with the rules given in GB/T 1.1-2009 "Guidelines for Standardization Work Part 1.Standard Structure and Compilation". This standard will replace MH/T 6018-1999 "Ground Static Power Supply" from the date of implementation. Compared with MH/T 6018-1999, there is a larger revision In addition to editorial changes, the main changes are as follows. --Modified the standard Chinese and English names (see cover, cover of MH/T 6018-1999); -Deleted "115 V (single phase), 26 V (single phase) and 36 V (three phase)" in Chapter 1 (see Chapter 1 of the.1999 edition); - Modify "DC 28.5 V" to "DC 28 V" (see 4.3.2.1, Chapter 1 of.1999 edition); --Modify the normative references; (see Chapter 2, Chapter 2 of the.1999 edition); -Added the "General Rules" under the technical requirements (see 4.1); --Modified "Ambient temperature. -20 ℃～50 ℃; when using below -20 ℃, appropriate heating measures can be taken according to user needs" It is "Outdoor type operating temperature. -30 ℃～55 ℃ and indoor type operating temperature. 0 ℃～40 ℃" (see 4.2.1,.1999 edition 4.2.1 a)); --- Added "Storage temperature. -40 ℃～60 ℃" (see 4.2.1); --Modified the relative humidity "10%～95%" to "10%～100% (non-condensing)" and "the altitude is less than or equal to 2 000 m" As "the altitude does not exceed 1000 m," (see 4.2.1,.1999 edition 4.2.1); - Modified "input power supply requirements" to "input power supply quality meets IEC 61000-2-4.2002 level 3." (see 4.2.2, 1999 version 4.1.1); -Deleted "output power supply" and "static power supply should be able to operate normally and continuously for 12 h under rated conditions" (see.1999 edition 4.1.2, 4.2.2); --- Increase the load capacity requirements of AC static variable power supply (see 4.3.1.2); -Modified "No-load voltage setting range" and moved it to 4.3.1.1 (see 4.3.1.1,.1999 edition 4.4.1.2); - Increase the load capacity of the DC static variable power supply (see 4.3.2.2); --Added the connector requirements (see 4.3.3); -Modified "Electromagnetic compatibility should comply with the A1 category in GJB 151-86" to "Input side meets IEC 61000-6-2..2005 Comply with GB 17799.4-2012 and the connector at ISO 7137.1995" (see 4.3.4.1,.1999 edition 4.8.1); --- Added "starting impulse current" (see 4.3.5); -Deleted the "soft start" function requirement (see.1999 version 4.6.1); -Modified "Efficiency 85%" to "Compound efficiency not less than 90%" (see 4.3.6,.1999 version 4.3); --- Increase the input power factor requirements under rated working conditions (see 4.3.7); --Modified AC steady-state output characteristics (see 4.3.8,.1999 edition 4.4.1); --Added the requirement of "three-phase average voltage and steady-state frequency" from rated load to overload of AC static variable power supply (see Table 4); --Modified "the steady-state voltage range of each phase in the steady-state voltage range 112 V～118 V" to "single-phase voltage range 112 V～120.5 V” (see Table 4,.1999 edition 4.4.1.1); - Modified "three-phase voltage unbalance" to "phase voltage unbalance" and "3 V" to "4.0 V" (see Table 4,.1999 edition 4.4.1.3); - Modified the phase shift "118°～122°" to "117.5°～122.5°" (see Table 4,.1999 edition 4.4.1.4); - Modified "total harmonic content" to "distortion coefficient" (see Table 4,.1999 edition 4.4.1.6); - Modified "single harmonic content" to "distortion spectrum" (see Table 4,.1999 edition 4.4.1.6); --Modified the steady-state frequency range "400 Hz±0.4 Hz" to "395 Hz～405 Hz" (see Table 4,.1999 edition 4.4.1.7); --Added frequency modulation spectrum requirements and attached drawings (see Table 4); -Modified "AC transient load" to "sudden increase or decrease of 0～150% of rated capacity three-phase balanced load" and motor load start Two loading situations (see 4.3.9.1,.1999 version 4.4.2); --- Added the uninterrupted power transmission working state in the load characteristics (see 4.3.9.1); --Modified the AC transient voltage characteristics requirements and the drawings (see 4.3.9.2,.1999 edition figure 1); --Modified AC transient frequency characteristics requirements and drawings (see 4.3.9.3,.1999 edition figure 1) --- Added the requirement of uninterrupted power transmission restriction (see 4.3.9.4); --- Added load characteristics in DC steady-state output (see 4.3.10); --Modified the DC voltage "26 V～30 V" to "24 V～29.5 V" (see Table 4,.1999 edition 4.4.3.1); - Delete the figure of pulsation amplitude (see figure 2 of.1999 edition); --Added the "distortion coefficient" and "distortion spectrum" requirements in the DC steady-state output characteristics (see Table 4); -Modified the load requirement in the DC transient output characteristics "when the load is suddenly increased from 5% of the rated load to 85%, and then suddenly reduced to 5%" "During normal operation, the DC transient load characteristics at the connector of the aircraft, including sudden addition and sudden reduction, do not exceed the rated continuous operation Current load" (see 4.3.11.1,.1999 edition 4.4.4); --Modified the requirements for the DC transient voltage limit and the accompanying drawings (see 4.3.11.2 and Figure 10,.1999 Edition Figure 3); --Modified the engine starting characteristics requirements and drawings (see 4.3.11.3,.1999 edition 4.4.4 b)); --Added the reference standards GB/T 15706-2012, GB 5226.1-2008 and IEC 61140.2009 in electrical protection Requirements for coordination of machine protection functions (see 4.4.1); -Deleted the "missing phase" requirement in electrical protection (see the.1999 version 4.5.1.2); --Modified "over voltage", "under voltage", "over frequency and under frequency", "over current and short circuit", "phase The requirements and diagrams of “Preface” (see 4.4.2.1～4.4.2.5,.1999 edition 4.5.2); - Modify "overload" to "overcurrent", and modify the requirements (see 4.4.2.4,.1999 edition 4.5.2.3); --- Added the protection requirements and drawings for the "DC component" in electrical protection (see 4.4.2.6); --Added the requirements for neutral line open circuit and ground fault protection (see 4.4.2.7 and 4.4.2.8); --Modified the requirements and drawings for "overvoltage", "undervoltage", "overcurrent and short circuit" in "DC system protection" (see 4.4.3.1~ 4.4.3.3,.1999 version 4.5.3); ---Added the requirements of "control circuit" and "static power supply should have two working modes" (see 4.5.1 and 4.5.3) --Modified the "static power supply used to power the aircraft, it should have the function of interlocking power supply with the aircraft." When the interlock function is present, the voltage provided by the aircraft is in the range of 16 V to 30 V, and the current drawn from the aircraft cannot exceed 0.5 A. The static variable power supply shall not supply power to the aircraft through this connection line" (see 4.4.4.3,.1999 edition 4.7.1); --- Added "monitoring" function requirements (see 4.4.4.1) --- Added "Electrical Safety" requirements (see 4.5.2); --- Revised personal safety "Static power supply should ensure the safety of operators when in use" to "safety requirements for personnel protection" (See 4.5.3,.1999 edition 4.7.2); --- Increase the design requirements of static variable power supply (see 4.5.4); - The test methods and inspection rules have been revised and re-edited according to the newly revised requirements (see 5 and 6,.1999 editions 5 and 6); -Modified the marking requirements (see 7.1,.1999 edition 7.1 and 7.2); ---Added the packaging box marking requirements (see 7.3); This standard emphasizes technical performance requirements and verification methods, and fully considers the use requirements of civil aviation. Its requirements include static variable power supply design and manufacturing. The technical content of each stage of manufacturing, sales, and use is deleted, and the content of management and contract is deleted. Please note that certain contents of this document may involve patents. The issuing agency of this document is not responsible for identifying these patents. This standard was proposed by the Airport Department of the Civil Aviation Administration of China. This standard was approved by the Aircraft Airworthiness Certification Department of the Civil Aviation Administration of China. This standard is under the jurisdiction of the China Academy of Civil Aviation Science and Technology. Drafting organization of this standard. Xi'an Aike Saibo Electric Co., Ltd. The main drafter of this standard. Bai Xiaoqing. This standard replaces MH/T 6018-1999. The previous release of this standard is. MH/T 6018-1999. Aircraft ground static power supply

1 Scope

This standard specifies the technical requirements, test methods, inspection rules and markings of aircraft ground static power sources (hereinafter referred to as static power sources) Requirements for packaging, transportation, and storage. This standard applies to AC 400 Hz, 115 V/200 V and DC 28 V static power supplies that provide electrical energy to aircraft.

2 Normative references

The following documents are indispensable for the application of this document. For dated reference documents, only the dated version applies to this article Pieces. For undated references, the latest version (including all amendments) applies to this document. GB/T 2423.1-2008 Environmental testing of electric and electronic products Part 2 Test method Test A. Low temperature (IEC 60068-2-1. 2007, IDT) GB/T 2423.2-2008 Environmental testing of electrical and electronic products Part 2 Test method Test B. High temperature (IEC 60068-2-2. 2007, IDT) GB/T 2423.3-2006 Environmental testing of electric and electronic products Part 2 Test method Test Cab. Constant damp heat method GB/T 2423.16-2008 Environmental testing of electrical and electronic products Part 2.Test methods Test J and guidelines. Mold growth (IEC 60068-2-10.2005,IDT) GB/T 2423.17-2008 Environmental testing of electric and electronic products Part 2.Test method Test Ka. Salt spray (IEC 60068-2-11.1981, IDT) GB/T 2423.38-2008 Environmental testing of electric and electronic products Part 2.Test methods Test R. Water test methods and guidelines (IEC 60068-2-18.2000,IDT) GB/T 3768-1999 Acoustic sound pressure method to determine the sound power level of noise sources using a simple method of envelope measurement surface above the reflective surface (ISO 3746.1995, EQV) GB/T 3859.1-2013 General requirements for semiconductor converters and power grid commutated converters Part 1-1.Basic requirements specification (IEC 60146-1-1.2009, MOD) GB 4208-2008 Enclosure protection grade (IP code) (IEC 60529..2001, IDT) GB 5226.1-2008 Electrical Safety of Machinery Electrical Equipment of Machinery Part 1.General Technical Conditions (IEC 60204-1.2005, IDT) GB/T 13384-2008 General technical conditions for packaging of mechanical and electrical products GB/T 15706-2012 General Principles of Machinery Safety Design Risk Assessment and Risk Reduction (ISO 12100.2010, IDT) GB 16754-2008 Mechanical safety emergency stop design principles (ISO 13850.2006, IDT) GB 17799.4-2012 EMC general standard emission in industrial environment (IEC 61000-6-4..2011, IDT) GB/T 19678-2005 Manual composition, content and presentation method (IEC 62079.2001, IDT) ISO 461-1..2003 Aircraft Ground Power Connector Part 1.Design, Performance and Test Requirements (Aircraft-

3 Terms and definitions

The following terms and definitions apply to this standard. 3.1 Pulsation During steady-state operation, the average value of DC current or DC voltage changes periodically or randomly. 3.2 Crest factor During steady-state operation, the absolute value of the ratio of the peak value of a cycle to the root mean square value. Note. The crest factor is a ratio. The crest factor of a standard sine wave is 2. 3.3 Load unbalance The difference between the highest phase load and the lowest phase load. 3.4 Phase voltage unbalance Under steady-state conditions, the maximum difference between phase voltages is expressed as follows. 3.5 Voltage modulation Under steady-state conditions, the AC peak voltage changes periodically or randomly around its average value. 3.6 Voltage modulation amplitude Under steady-state conditions, the difference between the maximum value and the minimum value of the peak voltage within a time interval of 1s. 3.7 Spectral components of voltage modulation Voltage modulation is represented by the quantization of the amplitude of each frequency component. 3.8 Instantaneous frequency The frequency of a single cycle. 3.9 Frequency modulation Under steady-state conditions, the instantaneous frequency changes periodically or randomly around its average value. 3.10 Frequency modulation amplitude Under steady-state conditions, the difference between the maximum and minimum instantaneous frequency within a time interval of 1 min. 3.11 Spectral components of frequency modulation The quantized representation of the amplitude of each frequency component in frequency modulation. 3.12 Distortion (current or voltage) In an AC system, the root mean square value of the AC waveform except the fundamental component. In a DC system, the root mean square value of the AC component in the DC waveform. 3.13 Distortion factor (current or voltage) The ratio of the distortion to the root mean square value of the fundamental. The distortion coefficient is usually expressed as a percentage as follows. 3.14 Distortion spectrum AC or DC distortion is represented by the quantization of the amplitude of each frequency component. Note 1.The distortion spectrum includes harmonic components and non-harmonic components of the fundamental frequency, which are usually generated by amplitude modulation or frequency modulation. Note 2.In order to be different from the relevant EMC requirements, for the 400 Hz fixed frequency power supply, the distortion spectrum only considers the frequency components below 16 kHz. 3.15 DC component of the AC voltage The time average value of the instantaneous value of the AC voltage.

4 Technical requirements

4.1 General The electrical characteristics specified in this standard refer to the electrical characteristics at the aircraft external power connector, from static variable power to the aircraft external power connector The cable length should not be less than 10 m (unless otherwise stated). AC voltage characteristics refer to the voltage characteristics of the phase line to the neutral line. All AC voltages refer to the root mean square value, and all DC values refer to the average Value (unless otherwise specified). 4.2 Conditions of use 4.2.1 Environmental conditions Static variable power supply should meet the following environmental conditions. a) Outdoor working temperature. -30 ℃～55 ℃; b) Indoor working temperature. 0 ℃～40 ℃; c) Storage temperature. -40 ℃～60 ℃; d) Relative humidity. relative humidity 10%～100% (non-condensing); e) The altitude does not exceed 1,000 m (when the altitude exceeds 1,000 m, the derating requirements should meet the requirements in Appendix A); f) Get in the rain (outdoor type). 4.2.2 Input power requirements The quality of input power supply meets the requirements of category 3 in IEC 61000-2-4.2002, the static variable power supply should be able to work normally. 4.3 Electrical characteristics 4.3.1 AC static variable power supply 4.3.1.1 General The output of AC static variable power supply should be three-phase four-wire, Y-type connection, rated voltage of 115 V/200 V, rated frequency of 400 Hz, and phase sequence ABC, if the neutral point is connected to the chassis ground wire, the connection wire should be able to withstand the maximum ground wire fault current of the shortest 5 s. See output connection figure 1. When there is no load, the output voltage should be adjustable to check the normal operation of the overvoltage and undervoltage protection devices. 4.3.1.2 Static variable power load capacity The static variable power load capacity is the continuous capacity (kVA), which should meet the requirements of Table 1. 4.3.2 DC static variable power supply 4.3.2.1 General The DC static variable power supply should be a two-wire system with a normal rated output voltage of 28 V. The typical circuit connection of the DC power supply is shown in Figure 2. 4.3.2.2 DC static variable power supply load capacity The DC static variable power supply is divided into three specifications. 400 A, 600 A, and 800 A. DC static variable power supply has continuous working and starting aircraft engine Two working conditions. The continuous working current of each working condition and the starting current of the aircraft engine shall meet the requirements of Table 2. 4.3.3 Connector The connector should meet the requirements of ISO 461. 4.3.4 Electromagnetic compatibility 4.3.4.1 Input side The electromagnetic compatibility of static variable power supply should meet the requirements of IEC 61000-6-2..2005 and GB 17799.4-2012. 4.3.4.2 At the connector The electromagnetic compatibility of static variable power supply should meet the requirements of ISO 7137.1995. 4.3.5 Starting inrush current The input side should adopt the soft ......
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