BepiColombo Heat Pipe Requirements Specification

Transcription

1 Title: Heat Pipe equirements Specification Document No.: CI Code.: WBS Code.: BC.ASU.SP B3143 & B3232 Issue: 1 Name Signature Date: Prepared by: Checked by: Product Assurance: Project Management: Distribution: See Distribution List Copying of this document, and giving it to others and the use or communication of the contents there-of, are forbidden without express authority. Offenders are liable to the payment of damages. All rights are reserved in the event of the grant of a patent or the registration of a utility model or design. Doc. No: BC.ASU.SP EADS Astrium Page 1 of 24

2 Change ecord Issue Date Sheet Description of Change elease Draft all first issue for ITT Initial Issue Doc. No: BC.ASU.SP EADS Astrium Page 2 of 24

3 Table of Contents 1 INTODUCTION AND SCOPE Introduction Scope Summary Description DOCUMENTS Applicable Documents Standards eference Documents DESIGN EQUIEMENTS Proof Pressure Burst Fracture Control & Analysis Dimensions Identification Mass Thermal Shock Shock Storage / Pre-Launch Operations VEIFICATION EQUIEMENTS General equirements Qualification Test equirements Burst Test Acceptance Test equirements Non-Condensible Gas Test eflux Mode Characterisation PEPAATION FO DELIVE New IATA egulations GDI APPLICABILIT MATIX...18 Doc. No: BC.ASU.SP EADS Astrium Page 3 of 24

4 List of Figures Figure 3.8-1: flight shock loads List of Tables Table 3.9-1: Limit Accelerations for Ground Operations Table 3.9-2: Ground transportation shock loads Doc. No: BC.ASU.SP EADS Astrium Page 4 of 24

5 Doc. No: BC.ASU.SP EADS Astrium Page 5 of 24

6 1 INTODUCTION AND SCOPE 1.1 Introduction This document forms the top level of a two-part specification for the heat pipes to be used on the MTM and MPO. The second part comprises the document AD01, which is the standard specification used by Astrium Ltd in the procurement of all heat pipes. Together, these two specifications establish the design, performance, fabrication and verification requirements on suppliers of surface mounted and embedded heat pipes for use in the spacecraft. 1.2 Scope It identifies all requirements in AD01 which are either not applicable to, or require modification for, the mission. The -specific requirements are then presented in this document. All requirements which remain unchanged from the Astrium Ltd standard heat pipe specification (AD01) are not repeated here. The Heat Pipe Specification forms, with its applicable documents, the formal and binding document for all technical agreements between Customer and the MLI Contractor. equirements within this document are shown in an italic font. Each requirement is preceded by a summary line that contains the following fields, delimited by "/". Doors equirement Number Created From Verification Method The Doors equirement Number has the form HP-xxx where xxx is a unique number assigned consecutively. The Created From field shows the parent requirement or "Created" if the requirement is created at this level. The Verification Method codes are as follows: S - Similarity - eview of Design A - Analysis Doc. No: BC.ASU.SP EADS Astrium Page 6 of 24

7 I - Inspection T - Test If tables are considered as part of the requirement they are referenced clearly in the text and inserted after and separated from the requirement table and are managed as free text attached to the identifier requirement. The trace to the upper level requirements (Upper Links) is managed using the following format: AAA-NNN where AAA is a label associated to the upper document and NNN the requirement identifier of this upper level. or CEATED keyword if the requirement has no link with upper level. All document elements not presented in the format explained above are not requirements and will not be verified or tracked. 1.3 Summary Description is an Interdisciplinary Cornerstone Mission to the planet Mercury, in collaboration between ESA and ISAS/JAXA of Japan. It consists of two scientific orbiters, the Mercury Planetary Orbiter (MPO) and the Mercury Magnetospheric Orbiter (MMO), which are dedicated to the detailed study of the planet and of its magnetosphere. These spacecraft are brought to Mercury by the Mercury Transfer Module (MTM), essentially a propulsion module which forms the lower spacecraft in a vertical stack of three. The MTM contains both solar-electric and chemical propulsion equipment and has a total radiator area of approximately 9.5m², comprising 3 panels. All 3 radiator panels require embedded and surface heat pipes. The MPO has a single radiator. Both embedded and surface heat pipes are also required for the MPO. Doc. No: BC.ASU.SP EADS Astrium Page 7 of 24

8 2 DOCUMENTS 2.1 Applicable Documents HP-34/Created/ In AD01, the applicable documents listed in 2.1 do not apply; they are superseded by the documents listed below. AD Title Doc. No. AD01 Specification for Heat Pipes MPS0021 AD02 AD03 AD04 AD05 AD06 AD07 General Design & Interface equirements Environment equirements and Test Specification Structural Design of Pressurised Hardware PA equirements for Subcontractors embedded heat pipe drawing surface heat pipe drawing BC-ASD-SP BC-ASD-SP ECSS-E (Draft) BC-ASD-SP AD08 Fracture Control ECSS-E30-01 AD09 CSG Safety egulations - Specific ules - Spacecraft CSG-S-22A-CN - Volume 2 - Part 2, Issue 5, evision 4, 2 December Standards 2.3 eference Documents Doc. No: BC.ASU.SP EADS Astrium Page 8 of 24

9 3 DESIGN EQUIEMENTS 3.1 Proof Pressure HP-61/Created/ AD shall be superseded by HP-63. HP-63/Created/T The heat pipes shall not suffer functional degradation or physical permanent deformation after having been subjected to an internal pressure defined as follows: Surface mounted pipes 1.5 times the saturation pressure at the non-operating temperature (90 C). Embedded pipes 1.5 times the pressure at the panel manufacturing temperature (150 C). 3.2 Burst HP-67/Created/ AD shall be superseded by HP-66. HP-66/Created/T The heat pipes shall not leak or burst after having been subjected to an internal pressure corresponding to the following conditions: Surface mounted pipes 2.5 times the saturation pressure at the non-operating temperature (90 C). Embedded pipes 2.5 times the pressure at the panel manufacturing temperature (150 C). Doc. No: BC.ASU.SP EADS Astrium Page 9 of 24

10 3.3 Fracture Control & Analysis HP-69/Created/ AD shall be superseded by HP-70. HP-70/Created/A, The approach in Figure 12 of AD04 shall apply. 3.4 Dimensions HP-72/Created/ AD shall apply, except that for the purpose of the ITT only, the dimensions are specified in the Statement of Work, rather than on a drawing. 3.5 Identification HP-95/Created/ The heat pipes intended for the MTM shall be identified by part numbers of the form: BC-MTMHP-XXX, where XXX is a 3-digit number. HP-96/Created/ The heat pipes intended for the MPO shall be identified by part numbers of the form: BC-MPOHP-XXX, where XXX is a 3-digit number. 3.6 Mass HP-529/Created/ The target mass per unit length for the Surface Heat Pipes, fully charged, shall be 285g/m, ignoring end-caps. A mass of 5g is allocated to end caps plus filler tubes. HP-530/Created/ The target mass for all the Embedded Heat Pipes, fully charged, shall be 190 g/m. A mass of 5g is allocated to end caps plus filler tubes. Doc. No: BC.ASU.SP EADS Astrium Page 10 of 24

11 3.7 Thermal Shock HP-534/Created/ AD shall be superseded by HP-535. HP-535/Created/T The heat pipes shall be able to withstand without damage, permanent deformation or functional performance degradation the following: 190 temperature cycles between -50 C and +50 C with 5 ± 0.5 minutes soak at each extreme temperature, followed by 10 temperature cycles between -50 C and +80 C with 2 ± 0.5 minutes soak at each extreme temperature. The transition time between each extreme temperature shall be less than 2 minutes. 3.8 Shock AD shall be superseded by the requirements in this section. HP-74/Created/T The MTM heat pipes, types BC-MTMHP-XXX shall be compliant with the GDI shock spectrum for the MTM, shown in HP-93. HP-92/Created/T The MPO heat pipes, types BC-MPOHP-XXX shall be compliant with the GDI shock spectrum for the MPO, shown in HP-93. HP-93/GDI-2712/T, The heat pipes shall withstand the shocks generated by activation of release mechanisms. The levels for the MTM and MPO are defined in the figure below, measured at the interface of the equipment to the structure. elease shocks at frequencies below 100 Hz shall be treated as latching shocks specified below. Doc. No: BC.ASU.SP EADS Astrium Page 11 of 24

12 SS[g] SS-LVA MTM SS-general MPO frequency[hz] Figure 3.8-1: flight shock loads 3.9 Storage / Pre-Launch Operations HP-77/Created/T, Points (a) to (d) in AD01, shall apply unchanged. Points (e) and (f) shall be replaced by the following requirements in this section. HP-98/GDI-2190/T The heat pipes and associated transport containers shall be sized to survive transportation and handling loads as defined in the following table (vertical means in the direction parallel to gravity): GOUND EVENT VETICAL HOIZONTAL Transportation 3.0g 3.0g HP-112/GDI-2199/ Table 3.9-1: Limit Accelerations for Ground Operations The transportation containers shall be designed to ensure that the flight unit contained within is protected from and shall be undamaged by shocks. Doc. No: BC.ASU.SP EADS Astrium Page 12 of 24

13 HP-147/GDI-3629/T During ground transportation the heat pipes shall withstand without damage the limit shock loads defined in the following table: Table 3.9-2: Ground transportation shock loads Doc. No: BC.ASU.SP EADS Astrium Page 13 of 24

14 4 VEIFICATION EQUIEMENTS 4.1 General equirements HP-537/Created/ AD shall be superseded by HP-538. HP-538/Created/I, The manufacturer shall be responsible for adequate and effective control over his procurement sources to ensure that materials procured for the equipment meet all quality and traceability requirements. Adequate records of inspections and tests performed shall be maintained until the end of 2021 (TBC). Purchase Orders shall be controlled to ensure incorporation of all pertinent technical, quality and traceability requirements, including authorised changes. 4.2 Qualification Test equirements HP-80/Created/ AD shall apply, except for the following sub-sections: Burst Test - shall be replaced by HP Burst Test HP-85/Created/T The heat pipes shall be subjected to the burst pressure defined in Section 3.2 of this specification for a period of 30 minutes. After this period the pressure shall be increased until burst occurs or to a pressure of 400 bar, whichever occurs first. The failure mode shall be such that does not eject solid particles. i.e. failure shall be by splitting of the pipe and not ejection of an end cap. The burst pressure test shall be carried out at a temperature of 90 C (surface heat pipe) or 150 C (embedded heat pipe) or at a lower temperature with a calculated allowance for material strength vs. temperature. Any such allowance shall be subject to approval by ASTIUM. 4.3 Acceptance Test equirements HP-81/Created/ AD shall apply, with the following exceptions: Non-Condensible Gas Test - shall be replaced by HP-87 Doc. No: BC.ASU.SP EADS Astrium Page 14 of 24

15 4.3.1 Non-Condensible Gas Test HP-87/Created/T, Not less than one heat pipe per order (or every 20 pipes shipped or each section type) shall be tested for noncondensible gas at -40 C in reflux boiler mode and shall contain no more NCG than that stated below: Initial Allowed NCG Level: The heat pipe shall not initially contain more than either: (i) 9.2 x 10-9 kmol of NCG for ammonia fill of up to 54 g or (ii) 1.7 x kmol of NCG per gram of ammonia for fills over 54 g Then, depending upon whether the NCG test is being performed as part of a QUALIFICATION test campaign, or an ACCEPTANCE test campaign, the following test shall be carried out: 1. Acceptance: HP-543 applies. 2. Qualification: HP-544 applies. HP-543/Created/T For each type of heat pipe ordered from the supplier by ASTIUM a heat pipe burn-in test shall be carried out on a representative heat pipe and the results formally reported, each time that type of heat pipe is ordered. The test shall be performed as follows: The heat pipe(s) shall be operated at an average temperature for 0.5 days of 150 C and then 29.5 days at 100 C and tested for noncondensible gas at 0 and 30 days, in reflux boiler mode at -40 C. The following criteria shall be applied: Following the completion of testing, the heat pipe shall not finally contain more than either: (i) 1.4 x 10-8 kmol of NCG for ammonia fill of up to 54 g or (ii) 2.5 x kmol of NCG per gram of ammonia for fills over 54 g HP-544/Created/T For each new heat pipe being qualified by the supplier for ASTIUM, a heat pipe burn-in test shall be carried out on two (2) representative heat pipes and the results formally reported. The test shall be performed as follows: Doc. No: BC.ASU.SP EADS Astrium Page 15 of 24

16 The heat pipes shall be operated at an average temperature for 1 day of 150 C and then 29 days at 100 C and then stored at room temperature for a further 10 days. They shall be tested for noncondensible gas at 0, 30 and 40 days, in reflux boiler mode at -40 C. The following criteria shall be applied: Following the completion of the test, the heat pipe shall not finally contain more than either: (i) 1.4 x 10-8 kmol of NCG for ammonia fill of up to 54 g or (ii) 2.5 x kmol of NCG per gram of ammonia for fills over 54 g eflux Mode Characterisation HP-532/Created/T One embedded heat pipe of each type ordered shall undergo the following reflux mode characterisation test, the results of which shall be documented and reported to the Customer (ASTIUM): the test heat pipe shall be operated in reflux mode (vertically) at least 5 different input powers over a range from 5 to 100W shall be applied at least 90% of the length of the heat pipe (between the evaporator and condenser ends) shall be insulated during the characterisation test the performance shall be characterised in terms of the temperature difference measured between the evaporator and condenser ends the test shall be conducted for the perfectly vertical condition, as well as 2, 6 and 12 off-vertical. Doc. No: BC.ASU.SP EADS Astrium Page 16 of 24

17 5 PEPAATION FO DELIVE 5.1 New IATA egulations HP-89/Created/ The required heat pipes for the Bepicolombo spacecraft must comply with the latest IATA regulations for shipment of heat pipes. Doc. No: BC.ASU.SP EADS Astrium Page 17 of 24

18 6 GDI Applicability Matrix The following table lists the applicable requirements of the GDI. It contains, in the first column, the Local ID for each applicable GDI requirement number. The second column contains the GDI equirement number and the opening text of the requirement. The third column defines the Applicability /N The final column shows the intended verification method. If no method is shown it shall be assumed that verification is required and the method is TBD eq No. eference Applicabilit y Verif. Method 2 Applicable and eference Documents 2.1 Applicable Documents HP-231 GDI-3994: The following documents, of the latest issue, or o Applicable Standards HP-233 GDI-3993: The following documents, of the latest issue, or o... 3 General Design and Interface equirements 3.1 General Design equirements HP-236 GDI-3287: All documentation shall use the SI Int Lifetime HP-238 GDI-35: TBD The equipment/subsystem shall meet the requirement... HP-239 GDI-38: A Maintenance during storage shall be as limited as... HP-240 GDI-37: A The MPO equipment/subsystems shall be designed wit... HP-241 GDI-51: T,A The MPO equipment/subsystems shall be designed to... HP-242 GDI-47: T,A All MPO consumables shall be sized to allow for th... HP-243 GDI-53: T,A The MTM equipment/subsystems shall be designed wit Safety and Product Liability HP-247 GDI-55: A The subcontractor shall comply to the applicable s... HP-248 GDI-56: A The subcontractor shall comply to the applicable p Venting Doc. No: BC.ASU.SP EADS Astrium Page 18 of 24

19 eq No. eference Applicabilit y HP-250 GDI-59: The equipment/subsystem shall be able to operate w Interchangeability HP-253 GDI-70: All spacecraft equipment/subsystems of the same pa Identification & Marking HP-255 GDI-72: The equipment hardware shall be identified with a... HP-256 GDI-73: The equipment/subsystem identification nameplate s Accessibility/Maintainability & Ground Testing equirements HP-259 GDI-82: The design of the equipment/subsystem, the positio... HP-260 GDI-83: The equipment shall be designed to require a minim... HP-261 GDI-84: No field maintenance, servicing or adjustment shal... HP-262 GDI-3152: The design of the spacecraft shall be constrained... HP-263 GDI-3154: It shall be possible to access or remove equipment... HP-264 GDI-3156: Items to be removed before flight (red-tag items) Transportation, Handling and Storage Transport HP-267 GDI-77: The equipment/subsystems shall be transported usin... HP-268 GDI-78: The equipment/subsystem containers, covers (for op... HP-269 GDI-79: The equipment/subsystem transport container shall... HP-270 GDI-80: The equipment/subsystem storage container shall be... HP-271 GDI-3913: The IATA flight regulations shall be considered Equipment/Subsystem Packing HP-273 GDI-90: Where applicable blanking caps shall be fitted to... HP-274 GDI-91: All equipment shall be packaged to ensure that it... Verif. Method A, I I I I I Doc. No: BC.ASU.SP EADS Astrium Page 19 of 24

20 eq No. eference Applicabilit y HP-275 GDI-93: The specified item GSE shall follow as far as appr Handling Seals HP-279 GDI-100: Any seals used shall comply with all the applicabl... HP-280 GDI-101: Any seals requiring periodic replacement during gr Lubricants and Sealants HP-282 GDI-103: No lubricants or sealants shall be used without th Contamination Sensitive Items Structural Design General equirements HP-288 GDI-117: The following failure modes, for equipment/subsyst... HP-289 GDI-123: The equipment/subsystem shall be designed to withs... HP-290 GDI-134: Fasteners used in safe life applications, items fa... HP-291 GDI-135: Fasteners a. Fasteners shall be classified and ana... HP-294 GDI-140: The Flight equipment shall be able to survive 4 ti Stiffness requirements HP-296 GDI-154: Except otherwise specified, when equipment/subsyst... HP-539 GDI-2188: The units and associated transport containers shal... HP-540 GDI-2189: Vertical and horizontal loads shall be considered Design equirements Mounting equirements HP-299 GDI-219: The attachment points of the equipment/subsystem s... HP-300 GDI-220: The number of attachment bolts for an equipment sh Thermal equirements Thermal Design equirements System Interface Temperature Point (STP) Verif. Method I A A A A A T,A A A A Doc. No: BC.ASU.SP EADS Astrium Page 20 of 24

21 eq No. eference Applicabilit y HP-541 GDI-3876: The system interface temperature point (STP) if de... HP-542 GDI-3882: The equipment/unit supplier shall analyse the heat Thermal Interface equirements Conductive Interface HP-311 GDI-316: The mounting interface shall comply with the mecha... HP-312 GDI-317: Equipment/subsystem mounting areas shall not be pa... HP-313 GDI-318: All equipment/subsystems shall have a smooth and p Thermal Design equirements HP-315 GDI-3193: It shall be possible to demonstrate conformance of Thermal Control HP-317 GDI-331: All thermal hardware mounted on the equipment/subs Thermal Interface Control Documents HP-319 GDI-333: All equipment/subsystem thermal interfaces shall b Thermal Mathematical Model equirements Thermal Analyses 4 Unit/Equipment/Subsystem Level Environment Test equirements 5 Appendix A : MICD 6 Appendix B : TICD 6.1 Thermal Interface Control Document HP-328 GDI-2892: All unit thermal interfaces shall be described wit... Verif. Method T,A A A T,A Doc. No: BC.ASU.SP EADS Astrium Page 21 of 24

22 Doc. No: BC.ASU.SP EADS Astrium Page 22 of 24

23 HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP HP Doc. No: BC.ASU.SP EADS Astrium Page 23 of 24

24 Distribution Sheet Doc. No: BC.ASU.SP EADS Astrium Page 24 of 24