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MHT6019-2014 English PDF

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MHT6019-2014: Airplane pre-conditioning air unit
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MH/T 6019-2014English909 Add to Cart 5 days [Need to translate] Airplane pre-conditioning air unit MH/T 6019-2014

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Standard similar to MHT6019-2014

GB/T 23420   MH/T 7022   MH/T 1076.4   MH/T 6029   

Basic data

Standard ID MH/T 6019-2014 (MH/T6019-2014)
Description (Translated English) Airplane pre-conditioning air unit
Sector / Industry Civil Aviation Industry Standard (Recommended)
Classification of Chinese Standard V56
Word Count Estimation 26,260
Date of Issue 25/8/2014
Date of Implementation 1/12/2014
Issuing agency(ies) Civil Aviation Administration of China

MHT6019-2014: Airplane pre-conditioning air unit

---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 power unit ICS 49.100 V 56 MH Industry Standards of Civil Aviation Administration of the People's Republic of China Replace MH/T 6019-1999 Aircraft ground power unit 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...1 4 Technical requirements...3 4.1 General...3 4.2 Environmental conditions...3 4.3 Electrical Characteristics...4 4.4 Protection and monitoring system...12 4.5 Control circuit and chain power supply...15 4.6 Safety requirements...15 5 Test method...18 5.1 Test environment, instruments and meters...18 5.2 Check appearance...19 5.3 Measurement quality...19 5.4 Measuring external dimensions...19 5.5 Checking the connector...19 5.6 Checking the fire extinguisher...19 5.7 Checking the emergency button...19 5.8 Checking the load capacity of the AC power supply...19 5.9 Checking the load capacity of the DC power supply...19 5.10 Measuring AC steady-state output characteristics...20 5.11 Measuring AC transient output characteristics...21 5.12 Measuring DC steady-state output characteristics...22 5.13 Measuring DC transient output characteristics...22 5.14 Check protection and monitoring devices...23 5.15 Measuring fuel consumption rate and oil consumption rate...24 5.16 Check aircraft interlock power supply function...25 5.17 Check each indicating device...25 5.18 Check electromagnetic compatibility...25 5.19 Measuring temperature rise...25 5.20 Checking the startup performance at room temperature...25 5.21 Check low temperature start measures...25 5.22 Measuring noise...25 5.23 Measuring vibration value...26 5.24 Measuring insulation resistance...26 5.25 Withstand voltage test...26 5.26 Check chassis safety...26 5.27 Low temperature test...26 5.28 High temperature test...27 5.29 Damp heat test...27 5.30 Mold growth test (parts)...27 5.31 Salt spray test (parts)...27 5.32 Rain test...27 5.33 Reliability and maintainability test...27 6 Inspection Rules...27 6.1 Inspection classification...28 6.2 Inspection items...28 6.3 Judgment rules and re-inspection rules...30 6.4 Inspection conditions...30 7 Marks, labels, accompanying documents, packaging, transportation, storage...30 7.1 Marks and labels...30 7.2 Attached documents...30 7.3 Packaging...31 7.4 Transport...31 7.5 Storage...31 MH

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 6019-1999 "Aircraft Ground Power Unit" from the date of implementation. This standard and MH/T 6019-1999 Compared with major changes, in addition to editorial changes, the main changes are as follows. - Revised and updated the normative reference documents (see Chapter 2, Chapter 2 of the.1999 edition); --Modified the DC rated voltage from 28.5 V to 28 V (see 4.3.2.1, 4.1.2 of the.1999 edition); --Modified the output regulations of the power supply unit, the conditions for outputting the specified power. the relative humidity was changed from "less than or equal to 95%" to "10%～100%"; the ambient temperature is changed from "-40 ℃～＋50 ℃" to "-30 ℃～＋55 ℃" (see 4.2.2, 4.2.2 of the.1999 edition); --Modified the standard adopted for the connector, from HB 6184 to ISO 461 (see 4.3.3,.1999 edition 4.1.3); --Modify the AC steady-state voltage, the phase voltage is changed from "112 V～118 V" to "109.5 V～122 V" (see 4.3.5.2.1, 4.4.1.1 of the.1999 version); --Modified the no-load voltage setting range, from "the lower limit should not be greater than 104 V, the upper limit should not be less than 127 V" to "when no load, The output voltage should be adjustable to check the normal operation of the undervoltage and overvoltage protection devices" (see 4.3.1.1, 4.4.1.2 of the.1999 edition); --Modified the phase shift, from "118°～122°" to "117.5°～122.5° (see 4.3.5.2.1,.1999 version 4.4.1.4); --Modified the load conditions of the three-phase unbalanced load (see 4.3.5.1, 4.4.1.3 of the.1999 edition); - Delete the requirements of frequency drift amount, frequency drift rate, frequency modulation amount and frequency modulation rate (see 4.4.1.8 and 4.4.1.9); --Added the requirements for AC distortion coefficient, distortion spectrum, and frequency modulation spectrum (see 4.3.5.2.1); --Added the requirement of AC steady-state load characteristics (see 4.3.5.1); --- Increase the requirements of AC transient load characteristics (see 4.3.6.1); --Modified the AC transient voltage characteristic curve (see 4.3.6.2, 4.4.2.1 of the.1999 edition); --Modified the AC transient frequency characteristic curve (see 4.3.6.3, 4.4.2.2 of the.1999 edition); --- Added the requirement of non-stop power transmission (NBPT) limitation (see 4.3.6.4); --Modified the DC steady-state voltage range. from "26 V～30 V range" to "should be within 24 V～29.5 V range" (see 4.3.7, 4.4.3.1 of the.1999 version); --- Added AC power supply load capacity requirements (see 4.3.1.2); --Added the classification of DC power supply load capacity (see 4.3.2.2); --Added the requirement for DC transient start engine (see 4.3.2.2 and 4.3.8.3); --Modified the requirement of DC transient load characteristics from "the load is suddenly increased from 5% of the rated load to 85%, and then suddenly reduced to 5%", to "Sudden addition and sudden reduction of loads that do not exceed the rated continuous working current" (see 4.3.8.1,.1999 edition 4.4.4); --Modified the DC transient voltage characteristic curve (see 4.3.8.2, 4.4.4 of the.1999 edition); - Deleted the special requirements for DC 57 V and 70 V output (see 4.4.5 of the.1999 edition); --Modified the AC undervoltage protection from "102 V" to "104 V" (see 4.4.1.2.2, 4.5.1.2 of the.1999 edition); --Modify the frequency protection parameter, the out of range is changed from "370 Hz～430 Hz" to "380 Hz～420 Hz", and "when When the frequency is lower than 350 Hz, the delay should be less than 0.2 s.” Frequency protection requirements (see 4.4.1.2.3, 4.5.1.3 of the.1999 edition And 4.5.1.4); --Added the requirements for neutral line open circuit and ground fault protection (see 4.4.1.2.6 and 4.4.1.2.7); --- Increased the requirements for multiple output overcurrent and short circuit protection (see 4.4.1.2.4); --- Added "monitoring" function requirements (see 4.4.3); - Modified the ambient temperature for low temperature start, from "-40 ℃" to "-30 ℃" (see 4.6.2.5.2,.1999 version 4.6.2); -Modified "Electromagnetic compatibility shall comply with the A1 category in GJB 151-86" to "Electromagnetic compatibility of power supply unit shall comply with Meet the requirements of ISO 7137" (see 4.3.4, 4.12.3 of the.1999 edition); -Deleted the requirement of insulation system (see 4.11.1 of.1999 edition); --- Added (automotive power supply unit) chassis safety requirements (see 4.6.4); - Deleted the requirements for driving and braking of automotive power supply units (see 4.9 of the.1999 edition); --Modified and added test methods corresponding to general rules, environmental conditions, electrical characteristics, protection systems, control circuits and safety requirements (See Chapter 5, Chapter 5 of the.1999 edition). 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. Weihai Guangtai Airport Equipment Co., Ltd. The main drafters of this standard. Yang Caijun, Chen Jiangan, Lei Xiaoming, Wang Jingdong. This standard replaces MH/T 6019-1999. The previous issuance of this standard is. MH/T 6019-1999.MH Aircraft ground power unit

1 Scope

This standard specifies the technical requirements, test methods, inspection rules and signs, accompanying documents, transportation and storage of aircraft ground power units And so on. This standard applies to AC 400 Hz, 115 V/200 V and DC 28 V aircraft that are powered by internal combustion engines to provide electrical energy to the aircraft. Ground power unit (hereinafter referred to as power unit).

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 755-2008 Rotating electric machine rating and performance GB/T 1589 Road vehicle outline size, axle load and mass limit GB/T 2423.16 Environmental testing of electrical and electronic products Part 2.Test method Test J and guideline. Mold growth GB/T 2423.17 Environmental testing of electrical and electronic products Part 2.Test method Test Ka. Salt spray GB 5226.1 Electrical safety of machinery Electrical equipment of machinery Part 1.General technical conditions GB/T 14436 General Rules of Guarantee Documents for Industrial Products GB/T 15706 General Principles of Mechanical Safety Design Risk Assessment and Risk Reduction GB 16754 Safety Emergency Stop Design Principles of Machinery Compilation composition, content and presentation method of GB/T 19678 manual GB/T.20136 General test method for internal combustion engine power station GB/T 21404 General requirements for determination and measurement methods of internal combustion engine power GB/T 21426-2008 Special environmental conditions and plateau requirements for power stations with internal combustion engines

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, expressed in VA. 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 and minimum peak voltages within a 1 s time interval. 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. Note. For DC systems, the fundamental component is the DC average value. 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.

4 Technical requirements

4.1 General The electrical characteristics specified in this standard refer to the electrical characteristics at the aircraft connector. Unless otherwise specified, the power unit to The cable length of the source connector should not be less than 10 m. AC voltage characteristics refer to the phase voltage characteristics of any phase in a three-phase AC power supply system. Unless otherwise specified, all AC voltage refers to voltage Root mean value (Vrms), DC voltage refers to the average voltage. 4.2 Environmental conditions 4.2.1 Conditions for output rated power Under the following conditions, the power unit should be able to output rated power. a) Ambient temperature. not more than 40 ℃; b) Relative humidity. not more than 60%; c) Altitude. not higher than 1 000 m. 4.2.2 Conditions for outputting specified power (allowing to modify power) Under the following conditions, the power supply unit should be able to output the specified power and work reliably. a) Ambient temperature. -30 ℃～＋55 ℃; b) Relative humidity. 10%～100% (non-condensing); c) Altitude. not more than 4 000 m. 4.2.3 Correction of power and ambient temperature When the actual operating conditions of the power unit are different from those specified in 4.2.1, its power should be converted into actual operating conditions according to the provisions of GB/T 21404 The engine power is converted into electrical power, but the maximum power should not exceed the rated power of the generator. When the operating altitude of the power supply unit exceeds 1,000 m (but not more than 4,000 m), the upper limit of the ambient temperature is set per altitude Increase 100 m and decrease 0.5 ℃ for correction. 4.3 Electrical characteristics 4.3.1 AC power 4.3.1.1 General The AC power supply should be three-phase four-wire, Y-type connection, rated voltage of 115 V/200 V, rated frequency of 400 Hz, phase sequence ABC, The output connection mode is shown in Figure 1. When there is no load, the output voltage should be adjustable to check the normal operation of undervoltage and overvoltage protection devices. 4.3.1.2 AC power load capacity The load capacity of the AC power supply is the continuous capacity (kVA), and the load capacity should meet the requirements of Table 1. Note. The power factor is the average value of the three-phase power factor, and the power factor of each phase can be different. 4.3.2 DC power supply 4.3.2.1 General The DC power supply should be a two-wire system with a normal output rated voltage of 28 V. The output connection mode is shown in Figure 2. When there is no load, the output voltage should be adjustable to check the normal operation of undervoltage and overvoltage protection devices. 4.3.2.2 DC power supply load capacity The DC power supply unit is divided into three specifications. 400 A, 600 A, and 800 A. The DC power supply unit has two working conditions. continuous working and starting aircraft engine. The continuous working current of each working condition and the starting current of the aircraft engine meet the requirements in Table 2. 4.3.3 Connector The connector shall meet the requirements of ISO 461. 4.3.4 Electromagnetic compatibility The electromagnetic compatibility of the power supply unit should meet the requirements of ISO 7137. 4.3.5 AC steady-state output characteristics 4.3.5.1 Load characteristics During normal operation, the AC steady-state load characteristics at the aircraft connector are shown in Table 3. Note 1.Under all conditions, the additional load can be resistive. Note 2.Under the condition of power supply capacity limitation, the above situations may occur simultaneously. 4.3.5.2 AC steady-state voltage characteristics 4.3.5.2.1 General Under all the load characteristics specified in Table 3, the steady-state electrical characteristics of the AC power supply unit should meet the requirements of Table 4.If there is more AC power For group output, the characteristics of all connectors should meet the requirements of Table 4. 4.3.5.2.3 Maximum phase voltage limit When the load is unbalanced, measures should be taken to limit the maximum phase voltage at each connector should not exceed 124 V. 4.3.5.2.4 Cable voltage drop compensation characteristics In order to keep the voltage at the connector stable, increase the output voltage of the power unit according to the load current and power factor to compensate for the output line Voltage drop on the road. The power supply should have cable voltage drop compensation characteristics. 4.3.6 AC transient output characteristics 4.3.6.1 AC transient load characteristics During normal operation, the AC transient load characteristics at the aircraft connector are as follows. a) Sudden increase or decrease of 0-100%, a three-phase balanced load of rated capacity with a power factor of 0.8; b) Motor load start. under the condition of basic load, plus low power factor (typical value 0.4～0.6 lag) electric When the machine starts the load, the total load power does not exceed the rated output capacity of the power supply; c) In the non-interrupted power transmission (NBPT) working state, it can run in parallel with the onboard power supply for a short time. 4.3.6.2 AC transient voltage characteristics Under 4.3.6.1 AC transient load conditions, the AC transient voltage characteristics of the power supply should be kept within the limit curve in Figure 7. 4.3.6.3 AC transient frequency characteristics Under 4.3.6.1 AC transient load conditions, the transient frequency characteristics of the power supply should be kept within the limit curve in Figure 8. 4.3.6.4 Uninterrupted power transmission (NBPT) restrictions In the process of uninterrupted power conversion, the power unit can run in an uninterrupted manner, and when it is not synchronized with the onboard power supply, the voltage, The frequency should be kept within the specified limit value. within the maximum time of 100 ms, the phase difference between the ground power supply and the airborne power supply does not exceed ±30°, The frequency difference does not exceed ±2 Hz, and the root mean square voltage difference does not exceed ±10 V. If the condition of uninterrupted conversion is exceeded, the power unit will start Own protection device. 4.3.7 DC steady-state output characteristics When the load current runs from no-load to the rated continuous working current, the DC steady-state output characteristics of the aircraft connector should conform to the table 5 requirements. 4.3.8 DC transient output characteristics 4.3.8.1 DC transient load characteristics (non-engine starting) During normal operation, the DC transient load characteristics at the connector of the aircraft include sudden addition and sudden reduction of negative loads that do not exceed the rated continuous operating current. Load. 4.3.8.2 DC transient voltage characteristics The DC transient voltage of the power unit should be kept within the limit curve in Figure 10. Figure 10 DC transient voltage limit 4.3.8.3 Engine starting characteristics During engine start, the DC transient voltage is related to the engine impedance and the actual current. The DC transient voltage may exceed the extremes shown in Figure 10. Limit curve. The minimum value of the DC transient voltage corresponding to the engine at the maximum current shall meet the requirements of the technical documentation of the power unit product. 4.4 Protection and monitoring system 4.4.1 Electrical protection 4.4.1.1 General The protection items of AC power output should meet the requirements of 4.4.1.2, and the protection items of DC power output should meet the requirements of 4.4.1.3. These protection functions should not only protect personal safety, power unit, but also ensure coordination with the aircraft's protection functions. When a certain protection circuit operates After that, the connection between the power unit and the aircraft should remain disconnected until manual reset. The acousto-optic signal should be set as required. 4.4.1.2 AC system protection 4.4.1.2.1 Overvoltage When the voltage value of any phase exceeds the maximum voltage protection limit shown in Figure 11, the protection system shall cut off the power supply unit to the aircraft. 4.4.1.2.2 Undervoltage When the voltage value of any phase is lower than the minimum voltage protection limit shown in Figure 11, the protection system should cut off the power supply unit to the aircraft. Figure 11 AC voltage protection limit 4.4.1.2.3 Over frequency and under frequency When the output frequency of the power supply unit exceeds the range of 380 Hz～420 Hz, the protection system shall delay the action of 2 s～3 s to cut off the power unit Power the aircraft. When the frequency is lower than 350 Hz, the delay should be less than 0.2 s. 4.4.1.2.4 Overcurrent and short circuit When the load time characteristics exceed the requirements in Table 1, the overcurrent protection system should act and cut off the power supply unit to supply the aircraft. Overcurrent protection The protection characteristics are determined according to the provisions of the technical documents of the power unit product. If a short circuit occurs inside the power unit and its power distribution system, overcurrent protection The protection should act according to the inverse time limit characteristic to protect the power supply unit. All output branches of a multi-output power supply unit shall have separate overcurrent protection functions. The power unit can only detect overcurrent The branch of the elephant is broken. 4.4.1.2.5 Phase sequence When the voltage phase sequence does not meet the requirements of Figure 6, the protection system should cut off the power unit to supply the aircraft. 4.4.1.2.6 Center line open The power unit should have the neutral line open circuit protection function. When the neutral line is detected, the protection system should cut off the power unit to supply the aircraft. 4.4.1.2.7 Ground fault When the output neutral line of the AC power supply unit is not grounded, the voltage difference between the neutral line and the chassis (earth) should be continuously monitored, at the peak of the voltage difference Before 50 V, the protection system should cut off the power supply unit to the aircraft. 4.4.1.3 DC system protection 4.4.1.3.1 Overvoltage When the voltage exceeds the maximum voltage protection limit shown in Figure 12, the protection system should act to cut off the power supply unit to the aircraft. 4.4.1.3.2 Undervoltage When the voltage is lower than the minimum voltage protection limit shown in Figure 12, the protection system should act and cut off the power unit to supply the aircraft. If the power The unit has the ability to start the engine, and the minimum voltage time limit should be consistent with the worst characteristics during engine start. Figure 12 DC voltage protection limit 4.4.1.3.3 Reverse polarity When the output voltage polarity is incorrect, the reverse polarity protection should cut off the power unit to supply the aircraft. 4.4.1.3.4 Regurgitation When the reverse current is greater than 5% of the rated output current of the power unit, the reverse current protection shall cut off the power supply of the power unit to the aircraft. Should not make Use the aircraft power supply system to start the prime mover of the power unit. 4.4.1.3.5 Overcurrent and short circuit The DC power supply shall be equipped with over-current and short-circuit protection devices. The overcurrent protection value and delay time are in accordance with the specifications of the power unit product technical documents. The short-circuit protection should be able to immediately cut off the connection between the power unit and the aircraft electrical system when a short-circuit fault occurs. For power supplies with engine start, the maximum allowable error of the output current limit is ±10%. 4.4.2 Mechanical protection The power supply unit should generally be equipped with the following mechan...

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