EuLISA. Mechanisms. Final Internal Presentation ESTEC, 8th July Prepared by the ICPA / CDF* Team. (*) ESTEC Concurrent Design Facility
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1 EuLISA Mechanisms Final Internal Presentation ESTEC, 8th July 2011 Prepared by the ICPA / CDF* Team (*) ESTEC Concurrent Design Facility
2 Mechanisms OPTION 1 Dual Soyuz Launch <Mechanisms> - 2
3 Mechanisms - Option 1 Mother S/C (MSC) Payload, assumptions: as per LISA MF, masses included into Instrument / payload mass. Telescope Tracking + hrms + electronics Point ahead+fsu+ <Mechanisms> - 3
4 Mechanisms - Option 1 HGA antenna preliminary design (heritage Rosetta, BC ): X-band, <1.0m dish (0.75 m baseline), two axis Azimuth based on classical Rosetta / BC APM. Depending on the final antenna configuration and accommodation, the deployment of a short boom might be necessary to provide adequate clearance from the S/C body. This Antenna Deployment Mechanism (ADM) will include: Spring based deployment hinge Radio frequency rotary joint (one axis) Short boom (0.6m) to achieve required clearance Associated thermal hardware (passive type). <Mechanisms> - 4
5 Mechanisms - Option 1 To avoid antenna re-orientation (flip-over) each orbital year, the Rosetta and BC azimuth twist capsule will be replaced by slip rings (unlimited rotational range). Due to induced self-gravity reqs (see critical areas), elevation axis by means of virtual rotation axis, based on converging flexible blades, plus flexible W/ G, limited to 14 deg tot angular range. This would require some limited technological development. <Mechanisms> - 5
6 Mechanisms - Option 1 Antenna deployment is typically done with elevation stage. In the present case a separate deployment mechanisms should be implemented ( virtual rotation axis concept would be difficult to implement for large deployment angles). One additional section of flexible W/G sould be necessary In that case, unless possibilities to deploy the reflector dish only exist (and then a simple spring based mechanism would be implemented) An alternative to the virtual rotational axis concept would be constituted by a particularly dedicated study on an antenna configuration that would minimize COG distance from APM axis, and some additional masses to fine balance the moving masses / inertia. <Mechanisms> - 6
7 Mechanisms - Option 1 Overall mass approx: APM 10Kg, including motorized hinges, RF RJ, flex W/G, HRMs, electronics, Thermal hardware. ADM 6.0Kg, including motorized hinges, RF RJ, flex W/G, HRMs, electronics, Thermal hardware. Power: 14 W (peak) Op temp, approx: -20C +60C <Mechanisms> - 7
8 Mechanisms Option 1 Telescope cover & ejection mechanisms, assumption: derived from LISA MF study. Mass includes Cover + Spring based hinge + non explosive HRM Mass (all included): 4.5 Kg each, total for two telescopes: 9.0 Kg. S/C separation mechanisms provided by launcher in standard adaptor and included in separation system mass. <Mechanisms> - 8
9 Mechanisms Option 1 Daughter S/C DSC: Only one telescope / optical bench, thus half payload mechanisms mass each DSC. HGA antenna: same as MSC Telescope cover ejection mechanism: same as MSC, but only one: mass 4.5 kg S/C separation system: based on similar concept as ASD alternative stack configuration, i.e. four hold down release point at structure corner, plus release springs. Mass estimate: 4.0 Kg each point, 16.0 Kg total per each daughter. Not included launcher I/F adaptor. <Mechanisms> - 9
10 Mechanisms Option 1 Design criteria Max level of communality MSC-DSC Use as much as possible high TRL level technologies and LISA pathfinder / MF already developed technologies. Review and use, only if appropriate, technical solution derived from LISA MD studies. <Mechanisms> - 10
11 Mechanisms Option 1 Critical areas 1)Antenna pointing induced back-action 2)Self gravity and antenna COG motion <Mechanisms> - 11
12 Mechanisms Option 1 Critical areas Antenna pointing induced back-action HGA movements generate reactions on MSC / DSC, which might disrupt or degrade laser links, e.g. ), to 6 deg antenna rotation correspond about 6500 nrad of S/C counter-rotation, which is unacceptable, since to maintain laser link a max of 10 to 100 nrads are required. Pointing approach based on similar concept as proposed by ASD, i.e. pointing achieved by series of small angular antenna motion, followed by stabilization phase performed by DFACS. Assuming similar mass/inertia for S/C HGA as per previous LISA MF study (which is not strictly true, also because MSC is heavier than DSC, but reasonable as a starting point and conservative, since both MSC and DSC show higher masses than in LISA MF <Mechanisms> - 12
13 Mechanisms Option 1 Critical areas Antenna pointing induced back-action Based on ASD analyses (ref. LISA-ASU-TN-4003), the following table can be reported: Since stabilization time is given to be proportional to back-rotation to be compensated, total travel time is independend from selected minimum step size (about 22 min for 6 deg antenna rotation). <Mechanisms> - 13
14 Mechanisms Option 1 Critical areas Antenna pointing induced back-action Selected pointing mechanism, as derived from Rosetta / BC HGA APMs with due design modifications, can achieve resolution down to approx 0.05 deg (approx 50 nrads), thus approx 10.0 sec would be required by DFACS to stabilize after each step. It has to be noted that under above circumstances the max antenna pointing or repointing speed would be 6/22 deg/min (<3 deg /min, ~0.05 deg/sec). Conservative ~0.01 deg/sec <Mechanisms> - 14
15 Mechanisms Option 1 Critical areas Self gravity and antenna COG motion Requiremnt from self-gravity demand that antenna COG should remain within approx 50.0 mm off-set from rotation axis. Previous LISA MF configuration assumes only one antenna pointing axis (azimuth), whilst for this study two axes are necessary. To maintain the COG at a reduced off-set from two rotational axes requires a detailed study of possible antenna / APM configuration, or ad-hoc to be developed APMs with virtual rotational axes going across antenna mobile parts COG. <Mechanisms> - 15
16 Mechanisms Option 1 Critical areas Self gravity and antenna COG motion In the case of two axes with virtual rotation axes for elevation (going through antenna COG), dedicated antenna mechanisms configuration shall be studied, and RF should be most likely transmitted through the elevation axis by means of flexible waveguides. Limited elevation angle (baseline 14 deg total) is important for implementation of above concept, but some technology development should be performed (approx KEuros ROM). <Mechanisms> - 16
17 Mechanisms Option 1 Critical areas Self gravity and antenna COG motion Need for dedicated deployment mechanisms, additional flex W/g, or alternative means to balance the antenna inertia, associated with dedicated antenna configuration study and or implementation of a dish only antenna deployment system have been quickly described in baseline design. <Mechanisms> - 17
18 Mechanisms OPTION 2 <Mechanisms> - 18
19 Mechanisms - Option 2 Payload mechanisms unchanged HGA pointing / HRMs mechanisms unchanged (TBC) Separation mechanisms (between each of the three S/Cs, but excluding any standard adaptor and asociated mechanism) depending on configuration, but in first approximation ( tuna can ref. concept), approx 32.0 Kg mass separation system (each) between II and III S/C on stack. <Mechanisms> - 19
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