1、 Reference number ISO 27875:2010(E) ISO 2010INTERNATIONAL STANDARD ISO 27875 First edition 2010-03-01 Space systems Re-entry risk management for unmanned spacecraft and launch vehicle orbital stages Systmes spatiaux Gestion du risque de la rentre pour les tapes orbitales des vhicules spatiaux non ha
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7、27875:2010(E) ISO 2010 All rights reserved iiiContents Page Foreword iv Introduction.v 1 Scope1 2 Normative references1 3 Terms and definitions .1 4 Re-entry risk management .2 4.1 General .2 4.2 Re-entry safety programme2 4.3 Re-entry safety oversight and management.2 4.4 Re-entry risk assessment a
8、nd mitigation plan.2 5 Risk assessment .3 5.1 General .3 5.2 Safety requirements3 5.3 Process and resources for analysis3 5.4 Estimation of risk 4 5.5 Risk decision and actions 4 6 Risk-reduction measures .6 6.1 General .6 6.2 Controlled re-entry 6 6.3 Structural design measures to reduce re-entry s
9、urvivability .6 6.4 Notification.6 7 Nonconformities processing6 Annex A (normative) Required content of the re-entry risk assessment and mitigation plan .7 Annex B (normative) Compliance matrix .11 Bibliography12 ISO 27875:2010(E) iv ISO 2010 All rights reservedForeword ISO (the International Organ
10、ization for Standardization) is a worldwide federation of national standards bodies (ISO member 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 establish
11、ed has the right to be represented on that committee. International organizations, governmental 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.
12、 International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, 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. Pu
13、blication as an International Standard requires approval by at least 75 % of the member bodies 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 paten
14、t rights. ISO 27875 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. ISO 27875:2010(E) ISO 2010 All rights reserved vIntroduction According to international treaties, the “launching state” is liable for damage or injuries c
15、aused by unmanned spacecraft and launch vehicle orbital stages that re-enter the Earths atmosphere. In addition, commercial operators are subject to the national safety regulations or laws of the launching country that relate to re-entry of spacecraft and launch vehicle orbital stages. In order to m
16、inimize damage and injury from re-entering spacecraft and launch vehicle orbital stages, it is the responsibility of all parties (developers, manufacturers, space service providers, satellite operators and launch service providers) to take preventive measures during spacecraft design and space opera
17、tions. INTERNATIONAL STANDARD ISO 27875:2010(E) ISO 2010 All rights reserved 1Space systems Re-entry risk management for unmanned spacecraft and launch vehicle orbital stages 1 Scope This International Standard provides a framework with which to assess, reduce and control the potential risks that sp
18、acecraft and launch vehicle orbital stages pose to people and the environment when those space vehicles re-enter the Earths atmosphere and impact the Earths surface. It is intended to be applied to the planning, design and review of space vehicle missions for which controlled or uncontrolled re-entr
19、y is possible. Objects that separate during the ascent phase and impact the ground are addressed in ISO 14620-2. This International Standard complements ISO 14620-1 and ISO 17666. This International Standard is not applicable to spacecraft containing nuclear power sources 1) . NOTE Useful background
20、 information for this International Standard is available in ISO 24113. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced
21、 document (including any amendments) applies. ISO 14620-1, Space systems Safety requirements Part 1: System safety ISO 17666, Space systems Risk management 3 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1 controlled re-entry type of re-entry w
22、here the time of re-entry is controlled and the impact of debris is confined to a designated ground zone NOTE This International Standard does not cover specific design to be retrieved, such as the Space Transportation System. 3.2 launch vehicle orbital stage stage of a launch vehicle that can be in
23、jected into orbit 1) Such spacecraft are controlled by the Principles Relevant to the Use of Nuclear Power Sources in Outer Space, (General Assembly resolution 47/68 of 14 December 1992), A/RES/47/68 47 U.N. ISO 27875:2010(E) 2 ISO 2010 All rights reserved3.3 re-entry process in which atmospheric dr
24、ag escalates deceleration of a spacecraft or launch vehicle orbital stage leading to its destruction or return to Earth 3.4 spacecraft system designed to perform specific tasks or functions in space 3.5 uncontrolled re-entry type of re-entry where the time and ground zone of impact are not controlle
25、d 4 Re-entry risk management 4.1 General Re-entry risk management shall be conducted as a part of a system safety programme based on ISO 14620-1 under the concept of risk management based on ISO 17666. 4.2 Re-entry safety programme In addition to the safety activities required by ISO 14620-1, a re-e
26、ntry safety programme shall be established to ensure: a) minimization of damage and injuries caused by re-entering spacecraft or launch vehicle orbital stages; b) corrective action for risks assessed to exceed programme or mission thresholds. 4.3 Re-entry safety oversight and management The safety r
27、epresentative defined in ISO 14620-1 or equivalent person or section shall have access to the safety data, approve the plans and the results of the work, and report the status to the head of organization. At each design and operation phase, a review committee shall review the result of the safety as
28、sessment and the plan for the next phase, and endorse the decision to proceed to the following phase. Required input data, purpose of review and output shall be defined for each review. The requirements in this International Standard may be tailored before their application. The results of tailoring
29、, however, shall be subject to the agreement of the responsible departments, the safety representative and the customer, if required. 4.4 Re-entry risk assessment and mitigation plan A re-entry risk assessment and mitigation plan (RRAMP) through project life cycle shall be prepared as part of the sa
30、fety data package specified in ISO 14620-1. The RRAMP will define the work plan corresponding to each requirement in this International Standard and detailed schedules of critical activities (design, analysis and testing reviews) throughout the life of the programme. The required contents of the RRA
31、MP are given in Annex A and the compliance between this International Standard and the RRAMP is described in Annex B. The RRAMP shall be approved by the safety representative, the head of project management and the customers. The RRAMP will change and evolve as the project proceeds. ISO 27875:2010(E
32、) ISO 2010 All rights reserved 35 Risk assessment 5.1 General Because the general concept for risk assessment is given in ISO 17666, this clause supplements specific requirements related to re-entry matter using terms (risk scenario, risk magnitude, risk decision and actions, etc.) defined in ISO 17
33、666. 5.2 Safety requirements Specific re-entry safety requirements imposed contractually, voluntarily or by national or international authorities shall be identified and applied, and where possible, quantified with threshold parameters. Deliberate re-entry risk assessment actions (analyses, reports,
34、 etc.) shall be defined and scheduled. A compliance matrix between safety requirements and system design and operation plan, which includes achieved quantitative results, threshold values, consequences of not meeting thresholds and the probability that those consequences would be realized, shall be
35、maintained. The expected output is the assessment parameters (e.g. risk to people on the ground and the associated mathematical parameters) and the thresholds for them or the concept for risk decision and actions according to the probability and severity of consequences. 5.3 Process and resources fo
36、r analysis Analysis corresponding to the safety requirements shall be conducted with the following approved processes, methods, tools, models and data. a) Description and justification of analysis tools and approach, including 1) algorithms for trajectory, aerodynamic, aerothermodynamic and thermal
37、analyses, object physical characteristics and aerodynamic and thermal properties for re-entry trajectory and heating analysis, 2) requisite physical characteristics and aerodynamic and thermal properties for trajectory and thermal analyses, 3) treatment of component thermal shielding and vehicle dis
38、assembly during the break-up process, 4) atmosphere model, 5) human population distribution model and definition of casualty area, 6) criteria for eliminating any vehicle components from the risk analyses, and 7) any other criteria or assumptions that affect the assessment of casualty; b) mission-de
39、pendent assumptions, if not defined in routine procedure, including 1) attitude mode (e.g. tumbling, side-on stable), 2) contribution of oxidation to the heating rate, and 3) conditions of the break-up process and sequence; c) specific vehicle and orbit data, including 1) initial orbit, 2) initial t
40、emperature, ISO 27875:2010(E) 4 ISO 2010 All rights reserved3) detailed identification of the spacecraft or launch vehicle orbital stage including its components (e.g. propellant tanks, pressurized vessels, major structural elements) and their construction, mass, dimensions, shapes, material propert
41、ies (e.g. melting point, density), connectivity, mutual shielding and nesting and other factors (e.g. aerodynamic drag coefficient, coefficients for average heating), and 4) properties of small but potentially surviving and hazardous objects that are likely to be released during re-entry. NOTE If th
42、e safety requirements identify a risk scenario other than ground casualty, an adequate process is added to the above set. 5.4 Estimation of risk According to the risk defined in 5.2, the risks of re-entry (probability of occurrence and severity of consequences) shall be estimated and reported as fol
43、lows: a) critical components with their characteristics, in enough detail to conduct trajectory and thermal analyses (e.g. mass, shape, dimensions); b) results of analyses including an estimate of the characteristics of the fragments likely to survive re-entry (e.g. mass, shape, dimensions, velocity
44、, kinetic energy at impact); c) probability of hazard and severity of consequence estimated according to the risk scenario identified by safety requirements; d) in the case of a planned controlled re-entry 1) a prediction of the ground area to be affected by the falling objects, 2) a hazard analysis
45、 for the circumstance when the re-entry is controlled successfully, and 3) a hazard analysis for the circumstance when the re-entry is not controlled successfully; e) in the case of onboard radioactive substances, toxic substances or any other environmental pollutants, an assessment of the effects t
46、hat they have on the Earths environment, including human health. 5.5 Risk decision and actions The risk magnitude shall be determined by the severity and probability of a hazard. For each risk scenario the risk decision and actions corresponding to the risk magnitude estimated in 5.4 shall be determ
47、ined, documented and approved by a safety representative. The result of the assessment shall be expressed in a risk assessment matrix. The rough concept for risk decision and actions for typical ground casualties and ground pollution is shown in Figure 1. ISO 27875:2010(E) ISO 2010 All rights reserv
48、ed 5Figure 1 Flow for risk assessment and disposal planning ISO 27875:2010(E) 6 ISO 2010 All rights reserved6 Risk-reduction measures 6.1 General The following typical measures to reduce re-entry risks are defined in 6.2, 6.3 and 6.4. Other measures (e.g. launch at different inclination to minimize
49、population at risk, intentional break-up just prior to re-entry or reduced orbital lifetime to avoid increased population growth) may be taken if the mission objective or mission cost-benefit metrics allow(s) them. The measures, namely a) controlled re-entry, b) structural design to reduce impact risks, and c) notification shall be planned, designed and documented in the safety data package specified in ISO 14620-1, and shall be reviewed in the Safety Review. 6.2 Controlled re-entry If the survivability analysis for an unc
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