BS ISO 15859-8-2004 Aerospace series - Space systems - Fluid characteristics sampling and test methods - Kerosine propellant《航空航天系统 航天系统 流体特性、抽样和试验方法 煤油推进剂》.pdf

《BS ISO 15859-8-2004 Aerospace series - Space systems - Fluid characteristics sampling and test methods - Kerosine propellant《航空航天系统 航天系统 流体特性、抽样和试验方法 煤油推进剂》.pdf》由会员分享，可在线阅读，更多相关《BS ISO 15859-8-2004 Aerospace series - Space systems - Fluid characteristics sampling and test methods - Kerosine propellant《航空航天系统 航天系统 流体特性、抽样和试验方法 煤油推进剂》.pdf（16页珍藏版）》请在麦多课文档分享上搜索。

1、BRITISH STANDARD AEROSPACE SERIES BS ISO 15859-8:2004 Space systems Fluid characteristics, sampling and test methods Part 8: Kerosine propellant ICS 49.140 BS ISO 15859-8:2004 This British Standard was published under the authority of the Standards Policy and Strategy Committee on 16 August 2004 BSI

2、 16 August 2004 ISBN 0 580 44272 1 National foreword This British Standard reproduces verbatim ISO 15859-8:2004 and implements it as the UK national standard. The UK participation in its preparation was entrusted by Technical Committee ACE/68, Space systems and operations, to Subcommittee ACE/68/-/3

3、, Operations and ground support, which has the responsibility to: A list of organizations represented on this subcommittee can be obtained on request to its secretary. Cross-references The British Standards which implement international or European publications referred to in this document may be fo

4、und in the BSI Catalogue under the section entitled “International Standards Correspondence Index”, or by using the “Search” facility of the BSI Electronic Catalogue or of British Standards Online. This publication does not purport to include all the necessary provisions of a contract. Users are res

5、ponsible for its correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. aid enquirers to understand the text; present to the responsible international/European committee any enquiries on the interpretation, or proposals for change, and keep

6、 the UK interests informed; monitor related international and European developments and promulgate them in the UK. Summary of pages This document comprises a front cover, an inside front cover, the ISO title page, pages ii to iv, pages 1 to 8, an inside back cover and a back cover. The BSI copyright

7、 notice displayed in this document indicates when the document was last issued. Amendments issued since publication Amd. No. Date Comments Reference number ISO 15859-8:2004(E) OSI 4002INTERNATIONAL STANDARD ISO 15859-8 First edition 2004-06-01 Space systems Fluid characteristics, sampling and test m

8、ethods Part 8: Kerosine propellant Systmes spatiaux Caractristiques, chantillonnage et mthodes dessai des fluides Partie 8: Krosne (carburant) BSISO158598:2004IS-95851 O8:(4002E) DPlcsid Fremia ihTs PDF file may ctnoian emdebt dedyfepcaes. In ccaocnadrw eith Aebods licensilop gnic,y this file mairp

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13、 74 E-mail coirypthgiso.o gr We bwww.is.o gro Pulbisdehi n Switlrez dnaii ISO 4002 Allr ithgsr esedevrBSISO158598:2004IS-95851 O8:(4002E) I SO 4002 All irthgs ersedevr iiiForeword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO mem

14、ber bodies). The work of preparing International Standards is normally carried out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmen

15、tal and non-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted in accordance with the rules given in the ISO/IEC Direc

16、tives, Part 2. The main task of technical committees is to prepare International Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodi

17、es casting a vote. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 15859-8 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehi

18、cles, Subcommittee SC 14, Space systems and operations. ISO 15859 consists of the following parts, under the general title Space systems Fluid characteristics, sampling and test methods: Part 1: Oxygen Part 2: Hydrogen Part 3: Nitrogen Part 4: Helium Part 5: Nitrogen tetroxide propellants Part 6: Mo

19、nomethylhydrazine propellant Part 7: Hydrazine propellant Part 8: Kerosine propellant Part 9: Argon Part 10: Water Part 11: Ammonia Part 12: Carbon dioxide Part 13: Breathing air BSISO158598:2004IS-95851 O8:(4002E) iv I SO 4002 All irthgs ersedevrIntroduction Fluid operations at a spaceport or launc

20、h site may involve a number of operators and supplier/customer interfaces, from the fluid production plant to the delivery to the launch vehicle or spacecraft. The purpose of ISO 15859 is to establish uniform requirements for the components, sampling and test methods of fluids used in the servicing

21、of launch vehicles, spacecraft and ground support equipment. The fluid composition limits specified are intended to define the purity and impurity limits of the fluid for loading into the launch vehicle or spacecraft. The fluid sampling and test methods are intended to be applied by any operator. Th

22、e fluid sampling and test methods are acceptable methods for verification of the fluid composition limits. BSISO158598:2004INTERNATIONAL STANDARD ISO 15859-8:2004(E)I SO 4002 All irthgs ersedevr 1Space systems Fluid characteristics, sampling and test methods Part 8: Kerosine propellant 1 Scope This

23、part of ISO 15859 specifies limits for the composition of kerosine and establishes the sampling and test requirements applicable for the verification of the kerosine composition. This part of ISO 15859 is applicable to kerosine propellant intended for use in fuel in propellant systems of space syste

24、ms as well as in both flight hardware and ground support facilities, systems and equipment. It may be applied to influent or effluent kerosine. This part of ISO 15859 is applicable to any sampling operation required to ensure that, when the fluid enters the launch vehicle or spacecraft, the fluid co

25、mposition complies with the limits provided hereafter or with any technical specification agreed to for a particular use. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undate

26、d references, the latest edition of the referenced document (including any amendments) applies. ISO 3012, Petroleum products Determination of thiol (mercaptan) sulfur in light and middle distillate fuels Potentiometric method ISO 3014, Petroleum products Determination of the smoke point of kerosine

27、ISO 9000, Quality management systems Fundamentals and vocabulary 3 Terms and definitions For the purposes of this document, the terms and definitions given in ISO 9000 and the following apply. 3.1 particulate matter undissolved solids retained on a filter paper with a 10-m nominal and 40-m absolute

28、rating 3.2 verification test analysis performed on the fluid in the container, or a sample thereof, which is representative of the supply, permitting the verification of fluid composition limits BSISO158598:2004IS-95851 O8:(4002E) 2 I SO 4002 All irthgs ersedevr4 Chemical composition and chemical an

29、d physical properties 4.1 Chemical composition Unless otherwise provided in an applicable technical specification, the chemical composition of kerosine propellant delivered to the flight vehicle interface shall be in accordance with the limits given in Table 1 when tested in accordance with the appl

30、icable test methods. Table 1 Composition limits Component Limit Existent gum mg/100 ml, max. 7 Potential gum, 16 h aging mg/100 ml, max. 14 Sulfur Total mass fraction, %, max. 0,05 Mercaptan-sulfur Mass fraction, %, max. 0,005 aAromatics Volume fraction, %, max. 5,0 Olefins Volume fraction, %, max.

31、2,0 Particulate matter mg/l, max 1,5 aThe mercaptan-sulfur determination may be waived at the option of the customer if the fuel is considered “sweet.“ 4.2 Chemical and physical properties The propellant shall be a clear and bright homogeneous liquid when examined visually by transmitted light. Unle

32、ss otherwise provided in an applicable technical specification, the chemical and physical properties of kerosine propellant delivered to the flight vehicle interface shall be in accordance with the limits given in Table 2 when tested in accordance with the applicable test methods. Table 2 Chemical a

33、nd physical properties Property Limit Initial boiling point a Fuel evaporated, 10 % 185 C to 210 C Fuel evaporated, 50 % at C a Fuel evaporated, 90 % at C a End point, max. 274 C Residue, volume fraction, %, max. 1,5 Distillation Distillation loss, volume fraction, %, max. 1,5 max. 0,815 Specific gr

34、avity min. 0,801 Freezing point C, max. 37,8 Thermal value: Net heat of combustion MJ/kg, min. 43,031 Viscosity mm 2 /s at 34,4 C, max. 16,5 Smoke point mm, min. 25,0 Copper strip corrosion max. a Water reaction b Flashpoint min.43,3 C Aniline point C a Copper corrosion test for 3 h at 100 C a aTo b

35、e reported; not limited. bSee 4.3 for requirements. BSISO158598:2004IS-95851 O8:(4002E) I SO 4002 All irthgs ersedevr 34.3 Water reaction When tested as specified in Table 1 and Clause 7, the propellant shall separate sharply from the water layer. In addition, neither layer shall change in volume by

36、 more than 1 ml. 4.4 Additives 4.4.1 Type and amount The additives listed in this clause may be used singly or in combination, in amounts which shall not exceed those specified. No substance of known dangerous toxicity under usual conditions of handling and use shall be added except as specified her

37、ein. The type and amount of each additive used shall be reported. 4.4.2 Antioxidants The following active inhibitors may be added separately or in combination to the propellant in total concentration not in excess of 9 g of inhibitor (not including mass of solvent) per 375 l of fuel in order to prev

38、ent the formation of gum: a) 2,6-ditertiarybutyl-4-methyl phenol; b) N,N -disecondarybutyl paraphenylenediamine; c) 2,4-dimethyl-6-tertiarybutyl phenol; d) 2,6-ditertiarybutyl phenol. 4.4.3 Metal deactivator A metal deactivator, N,N -disalicylidene-1,2-propanediamine, may be added in an amount which

39、 shall not exceed 2,1 g of active ingredient per 375 l of fuel. 4.4.4 Dye A dye, methyl derivative of azobenzene-4-azo-2-naphthol, may be added in an amount which shall not exceed 14 g per 3 750 I of fuel. 5 Procurement The kerosine specified in Clause 1 should be procured in accordance with an appl

40、icable national standard. 6 Fluid sampling CAUTION Kerosine propellant is a combustible liquid and a fire hazard. Care should be taken in the handling and storage of kerosine propellant to prevent contact with ignition sources. Harmful if swallowed and/or aspirated into the lungs. Can cause skin irr

41、itation upon prolonged or repeated contact. BSISO158598:2004IS-95851 O8:(4002E) 4 I SO 4002 All irthgs ersedevr6.1 Plan In order to ensure that the fluid composition complies with the limits specified in this part of ISO 15859, a fluid sampling plan should be established by all the involved operator

42、s, from the production to the space vehicle interface, and approved by the final user. Sampling activities and test methods shall comply with all safety regulations and rules applicable to that task. This plan shall specify the sampling points, the sampling procedures, the sampling frequency, the sa

43、mple size, the number of samples, the test methods, and the responsibilities of any involved operator. 6.2 Responsibility for sampling Unless otherwise provided in an applicable technical specification, the kerosine delivered to the flight vehicle interface shall be sampled and verified by the suppl

44、ier responsible for providing the kerosine to the flight vehicle. The supplier may use his/her or any other resources suitable for the performance of the verification tests specified herein unless otherwise directed by the customer. 6.3 Sampling points Unless otherwise specified, sampling shall be c

45、onducted at the fluid storage site. 6.4 Sampling frequency Sampling shall be performed annually or in accordance with a time agreed upon by the supplier and the customer. 6.5 Sample size The quantity in a single sample container shall be sufficient to perform the analysis for the limiting characteri

46、stics. If a single sample does not contain a sufficient quantity to perform all of the analyses for the required quality verification test, additional samples shall be taken under similar conditions. 6.6 Number of samples The number of samples shall be in accordance with one of the following: a) one

47、 sample per storage container; b) any number of samples agreed upon by the supplier and the customer. 6.7 Storage container Unless otherwise provided by the applicable sampling plan, the fluid storage container shall not be refilled after the sample is taken. BSISO158598:2004IS-95851 O8:(4002E) I SO

48、 4002 All irthgs ersedevr 56.8 Liquid samples Liquid samples shall be a typical specimen from the liquid kerosine supply. Samples shall be obtained in accordance with one of the following. a) By filling the sample container and storage containers at the same time, on the same manifold, and under the

49、 same conditions and with the same procedures. b) By withdrawing a sample from the supply container through a suitable connection into the sample container. No pressure regulator shall be used between the supply and the sample containers. (Suitable purge and drain valves are permissible.) For safety reasons, the sample container and sampling system shall have a rated