SAE AS 8033-1981 Nickel Cadmium Vented Rechargeable Aircraft Batteries (Non-Sealed Maintainable Type)《镉镍开口的可充电飞机蓄电池 (未密封可维修型)》.pdf

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4、 (outside USA)Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/AS8033 AEROSPACESTANDARDAS8033 Issued 1981-02 Reaffirmed 2017-10 Nickel Cadmium Vented Rechargeab

5、le Aircraft Batteries (Non-Sealed, Maintainable Type) RATIONALE AS8033 has been reaffirmed to comply with the SAE Five-Year Review policy. OUTLINE1.PURPOSE2.SCOPE AND DEFINITIONS2.1Definitions3.GENERAL REQUIREMENTS3.1Electrical3.2Nameplate Markings3.2.1Safetya.Explosive Gases in Overchargeb.Short Ci

6、rcuit Powerc.Caustic Electrolyted.High Voltage Shocke.Secure Installation Mounting3.2.2Performance Ratings3.2.3Operational Information3.2.4Cell Markings3.3Environmental Requirements3.3.1Operational Shock3.3.2Operational Vibration3.3.3Humidity3.3.4Inverted Operation3.3.5Corrosion Resistance3.3.6Fluid

7、s Resistance4.MINIMUM REQUIREMENTS - SAFETY4.1Explosion of Hydrogen/Oxygen Gases4.1.1Purging System4.1.2Ignition Sources4.1.3Explosion Containment4.2Fire4.2.1Self Extinguishing Materials4.2.2Purging of Smoke and Toxic Gases4.3Cell Vents4.4Dielectric Strength4.5Battery Energy Leakage4.6Crash Safety5.

8、MANUFACTURING PERFORMANCE RATING - STANDARD PROCEDURES5.1Discharge Performance5.1.1Capacity Delivery (Emergency Energy Source)a.“C1” - Rated Minimum Capacity at 23C (73F)b.Capacity Derating (Dc) as a Function of Temperature (T)c.Capacity Derating (Dc) as a Function of Discharge Rate Multiples (M)5.1

9、.2Power Delivery (Engine Start Capability)a.“I mp ” - Power Rating at 23C (73F)b.I mp Derating (D I ) as a Function of Temperature (T)c .I mp Derating (D I ) as a Function of State of Charge (S)5.2Charge Performance5.2.1On Board-Constant Potential5.2.2On Board-Constant Current to Voltage Cutoff5.2.3

10、On Board-Charge Voltage as a Function of Electrolyte Temperature5.2.4Maintenance Reconditioning5.3Charge Retention - Storage5.4Supplemental Characteristics5.4.1Battery Heaters5.4.2Battery Cooling/Heating1.PURPOSEIt is the purpose of this Aerospace Standard to provide for the definition of the requir

11、ements of vented type, rechargeable, Nickel-Cadmium batteries of the form generally used in aircraft. These batteries serve as power sources for engine starting and also function to provide a source of emergency back-up electrical energy for essential loads. This Aerospace Standard establishes minim

12、um standards for those functional characteristics of the battery which are required to enhance the safety of both personnel and aircraft, insofar as it is dependent on the battery. It is the further purpose of this Aerospace Standard to delineate those characteristics which are utilized in the norma

13、l, non-emergency functions of the battery.This Aerospace Standard defines the minimum acceptable functional characteristics where they pertain to safety related issues and outlines the responsibilities of the battery manufacturer, the systems designer and maintenance personnel to ensure that those s

14、afety functions are not compromised. This Aerospace Standard also defines the measurement methods whereby the manufacturers rated values of normal performance functions may be confirmed. The requirements for manufacturer supplied nameplate data and additional application information are also defined

15、.It is the further purpose of this Aerospace Standard to delineate those battery related issues which Aircraft System designers and Aircraft maintenance personnel must consider in their respective tasks and about which they must receive design/maintenance information from the battery manufacturer.2.

16、SCOPE AND DEFINITIONThe Nickel Cadmium battery covered by this Aerospace Standard is the type which is generally, although not exclusively, used for engine starting purposes in turbine-powered aircraft and/or on aircraft with turbine type Auxiliary Power Units. This turbine starting function require

17、s high power delivery rates from the battery for 15 to 30 seconds or more for each engine start. This same battery may also be used at lower power delivery rates, as the final redundant source of emergency electrical energy for the operation of essential flight equipment for required periods of 30 t

18、o 60 minutes.The battery generally consists of a group of plastic jarred cells contained within an enclosing battery case. They are electrically connected in series with each other and usually terminate in an electrical connector mounted in the case front wall. The battery case may be secured to the

19、 aircraft structure by any of a number of clamping techniques.The outer or battery case is ventilated to purge it of gases, such as the hydrogen and oxygen produced in overcharge. This ventilation may be of the closed air circuit type which is accomplished by passing air through the case and then ex

20、hausting these gases overboard. An alternative method, which is used to purge these gases from the battery case, is to encourage their natural convective diffusion with the ambient air in the compartment which contains the battery, by use of relatively open construction of the battery case and cover

21、.SAE INTERNATIONAL AS8033 Page 2 of 17_ 2.(Continued)The battery, while in service, is generally charged by one of two methods :1) by direct electrical connection to the D.C. bus which in turn is supplied by a regulated/controlled “constant potential” source such as a D.C. generator, or 2) from a de

22、dicated “constant current” source in a system whereby the battery response voltage controls the termination, and also possibly the reinitiation, of that charge current. The “control” voltage of the “constant current” charge system or the regulated supply voltage of the “constant potential” system, m

23、ay be compensated, or automatically adjusted, according to cell temperature, in order to more accurately control the state of “full charge” and minimize the amount of water used during overcharge.These batteries may be equipped internally with heaters, thermal switches, thermal sensors, etc. for per

24、forming various functions both inside the battery and/or in the aircraft/battery system. In addition, some battery types have air passages between cells with appropriate plenum chambers above and below the cells, for more positive responsive control of cell temperature, by the passage of conditioned

25、 air.2.1Definitions :Battery - The complete cased assembly of interconnected electrochemical cells, ready for installation in the aircraft.“C 1 ” - The numerical value of the minimum expected capacity in units of ampere hours, at a discharge rate of C 1 amperes (the one-hour rate), and a battery tem

26、perature of 23C. C 1 is the rating which indicates the relative amount of available emergency electrical energy capability of a particular cell/battery design.Capacity - The dischargeable ampere hours available from a fully charged cell/battery at any specified discharge rate/temperature condition.C

27、ell - The basic battery building block. An electrochemical storage device consisting of positive and negative plates, separator, gas barrier and electrolyte contained in a cell case (jar) with suitable electrical terminals for connection to additional cells.Charging - The return of electrical energy

28、 to a battery and its storage in electrochemical form.Discharging - The removal of electrical energy from a battery.Electrolyte - The ionically conductive alkaline solution used in the nickel cadmium cell.Gas Barrier - The ionically conductive film, between the cell plates, which forces all plate ge

29、nerated gases to the top of the electrolyte and prevents them from reaching plates of opposite polarity.I mp - The numerical value of discharge current capability of a battery at maximum power delivery, partway through a simulated turbine engine start. the I mp rating indicates relative engine-start

30、ing power capability of the battery, and is the minimum value of I mp expected from the fully charged battery at 23C. For engine start system design purposes, the use of a straight line approximation between a terminal voltage of 1.2N volts at zero load current and 0.6N volts at I mp Amps, tends to

31、be slightly conservative in the first few seconds of discharge toward engine light-off.Overcharging - The continued passage of electrical “charging” current after the cell plates are charged. It results in the generation of hydrogen and oxygen gases. The onset of overcharge is manifested in the form

32、 of a transition from negligible gassing to complete conversion of all (over) charge current to gas.SAE INTERNATIONAL AS8033 Page 3 of 17_ 2.1(Continued)Potassium Hydroxide - The caustic material which is mixed with pure water to formulate the electrolyte solution which is used in nickel cadmium cel

33、ls.Reconditioning - The programmed electrical exercise, consisting of a discharge/charge cycle(s), which is periodically utilized to restore the capability of full energy and power delivery to a battery which has electrically deteriorated while in service. It may also include water replacement and m

34、echanical cleaning procedures.Self-Discharge - The decrease in the state of charge of a cell, not resulting from an applied useful load, over a period of time, normally due to internal electrochemical losses and accelerated by higher temperature.Separator - Layer(s) of insulating material (convntion

35、ally a fabric) which provide electronic separation between electrically conductive cell plates of opposing polarities. It is placed adjacent to the gas barrier and provides physical support for the gas barrier material.Vent Cap - The check valve component on top of a cell which regulates the maximum

36、 internal pressure which the cell jar will hold while preventing the entrance of atmospheric gases under conditions of flutuating ambient pressures. It is removeable to allow water replacement to the electrolyte.3.GENERAL REQUIREMENTS3.1Electrical :The battery shall be provided with a means for elec

37、trically connecting it to an external circuit. This connection, along with its mating external circuit connector, the intercell connectors within the battery, and the internal cell components, shall be capable of carrying a short circuit current of approximately two times the rated value of Impfor a

38、 period of at least 3 minutes without igniting an explosive H2/O2mixture inside the cells or within the battery case. The battery is not required to be functional following a testing of this capability.3.2Nameplate Markings :It is recommended that all nameplate markings also be reproduced in appropr

39、iate pilot or aircraft operating handbooks and aircraft maintenance manuals.3.2.1Safety - Required :CAUTION notices related to personal or aircraft safety must be prominently and effectively displayed. They should communicate (1) the urgency of the caution, (2) the nature of the hazard, (3) the acti

40、on required in order to avoid the hazard, and (4) first aid/antidotal information for hazard recovery. The following hazard subjects shall be treated and communicated with highly visible battery labeling.a.Explosive Gases in Overcharge : The situations treated shall include both maintenance recondit

41、ioning and in-aircraft handling. The actions treated shall include, as a minimum, smoking, open lights, room or container ventilation, effective case purging ventilation system/connections when installing, and arcs when connecting/disconnecting live loads.b.Short Circuit Power : This subject shall i

42、nclude, as a minimum, such factors as magnitudes of potential short circuit currents that may be expected. They shall also include warnings about the use of uninsulated tools, metal brushes or metal supported brushes in battery cleaning, and the fusing/welding of personal jewelry such as rings, brac

43、elets, neck chains, etc.SAE INTERNATIONAL AS8033 Page 4 of 17_ 3.2.1(Continued)c.Caustic Electrolyte : This subject shall include, as a minimum, such actions as proper maintenance of vent caps, precautionary opening of vent caps, and eye and face protection when opening. Antidote information shall i

44、nclude prompt water flushing of skin surfaces which have been contaminated with potassium hydroxide.It shall also include immediate and extensive water flushing and medical attention following any instance of eye splash. The chemical constituents of the electrolyte used shall be displayed.d.High Vol

45、tage Shock : In those applications involving series connected batteries yielding system voltages greater than 40 to 50 volts, the subject of personal shock hazard shall be treated. Hazard factors here shall include the use of grounded battery circuit system with ungrounded battery cases, the high sy

46、stem voltage itself with exposed intercell connectors, and battery circuit to case leakage currents greater than 2 mA. Maintenance of cleanliness within the battery case shall be considered and stressed.e.Secure Installation Mounting : The subjects of continued secure mechanical restraint of this re

47、latively heavy component, and the use of appropriate methods to ensure continued electrical connection in the aircraft, shall be treated.3.2.2 Performance Ratings - Required :The following performance and functional information shall be provided by the battery manufacturer on the exterior surface of

48、 the battery case in a permanent and legible form.a.Battery manufacturers name and address.b.Battery rated capacity “C1” ampere hours.c.Battery rated Im pamperes.d.Nominal battery voltage and number of cells.e.Battery polarity.f.Manufacturers model or type designation.g.Battery maximum weight with electrolyte properly leveled.h.Nominal charging voltages at 23C: Vcp, Vcoand V. (See Figure 6 and paragraph 5.2.2 for definition).i.If applicab