{ "source": { "document": "docs/reviews/CDR/CDR_2026_DESIGN_REVIEW.md", "document_id": "SQSO-REV-CDR-002", "revision": "B", "section": "§3.3", "url": "https://github.com/cheesejaguar/SMART-QSO/blob/main/docs/reviews/CDR/CDR_2026_DESIGN_REVIEW.md" }, "rows": [ { "quantity": "Mass", "requirement": "≤ 2.00 kg (design), 2.5 kg Nova", "predicted": "MEV 1.755 kg, CBE 1.520 kg (ballast, harness 85.6 g with the real splices and tabs, cell retention)", "margin": "+14.0 % (+42.5 % to the Nova)", "source": "MASS_BUDGET 3.3" }, { "quantity": "CG, stowed", "requirement": "±20 mm", "predicted": "(+0.1, −0.3, −1.4) mm CBE (CAD)", "margin": "> 18 mm", "source": "MECHANICAL_DESIGN B" }, { "quantity": "Deployed inertia", "requirement": "Iyy ≥ 1.03 × max, axis within 5° of +Y", "predicted": "1.056 / 1.047 (CBE / MEV, four AntS elements, C-13 ballast, harness), 0.9° / 1.0°; MEV 5th percentile 1.036 at 2 mm placement scatter", "margin": "Met", "source": "MECHANICAL_DESIGN B §5" }, { "quantity": "First mode, stowed", "requirement": "> 40 Hz", "predicted": "170 Hz CBE / 162 Hz MEV (FE, 2.0 mm EPS, rod on the −X wall)", "margin": "× 4.0–4.3", "source": "STRUCTURAL_ANALYSIS" }, { "quantity": "Strength", "requirement": "MS ≥ 0 (NASA-STD-5001B protoflight factors at MPE + 3 dB)", "predicted": "Lowest +0.97 (+0.86 at MEV masses)", "margin": "Positive", "source": "STRUCTURAL_ANALYSIS" }, { "quantity": "PCB fatigue (Steinberg)", "requirement": "MS ≥ 0", "predicted": "+0.42 to +0.72 at CBE, +0.14 to +0.51 at MEV (2.0 mm EPS and carrier)", "margin": "Positive", "source": "STRUCTURAL_ANALYSIS" }, { "quantity": "Wing deployment torque", "requirement": "NASA-STD-5017B torque margin ≥ 0 at end of travel, at −55 °C", "predicted": "+0.08 (one spring out +0.07); release-energy ratio 1.90 with the 10 s burn (C-17)", "margin": "Positive; resistive torque below −40 °C verified at −55 °C (VI-MECH-01..03)", "source": "MECHANISMS_ANALYSIS E" }, { "quantity": "Power, EOL, sun-pointed", "requirement": "≥ 20 %", "predicted": "3.84 W delivered with the photodiode-and-albedo pointing of C-23 (3.79 W in the worst trial; 3.92 W with +Y held on the Sun) against the bottom-up ACTIVE load 2.60 W with the heater and the transponder", "margin": "+45 % (+43 % worst trial), PBA method; +70 % on the 2.26 W allocation by the BASELINE method", "source": "POWER_BUDGET_ANALYSIS 2.5 §4; ADCS_DESIGN 1.9 §11.6; BASELINE §5" }, { "quantity": "Power, EOL, tumbling", "requirement": "≥ 20 %", "predicted": "2.48 W against the bottom-up ACTIVE load 1.91 W with the heater and the transponder", "margin": "+27 %, PBA method; +33 % on the 1.86 W allocation by the BASELINE method", "source": "POWER_BUDGET_ANALYSIS 2.5 §4; BASELINE §5" }, { "quantity": "Depth of discharge", "requirement": "≤ 10 % per eclipse", "predicted": "≤ 3.5 % as flown (SIL G, 475 km); 2.8 % worst contingency (PBA 2.2)", "margin": "× 2.9", "source": "SIL_MISSION_SIMULATION G §7; POWER_BUDGET_ANALYSIS" }, { "quantity": "Battery temperature", "requirement": "0 to +45 °C charging", "predicted": "≥ +4.4 °C at 14.0 V; +3.6 °C at the 12.0 V floor (0.70 W heater); +1.3 °C with a 0.10 W/K mount at 14.0 V; −1.5 °C with the wings stowed at 0.70 W (charging then inhibited in hardware)", "margin": "Met in operation; stowed-wing case THM-03", "source": "THERMAL_ANALYSIS 2.6" }, { "quantity": "Beacon link, 5°", "requirement": "≥ 6 dB (median gain)", "predicted": "+7.9 dB", "margin": "+1.9 dB", "source": "LINK_BUDGET 3.2" }, { "quantity": "Telecommand link, 10°", "requirement": "6 dB with interference allowance", "predicted": "≥ +8.4 dB at both variants' minimums (variant A +9.5 dB), receiver as designed, 10th-percentile gain, pointing included (≥ +6.6 dB at 5°)", "margin": "≥ +2.4 dB", "source": "LINK_BUDGET 3.5 (C-14)" }, { "quantity": "Sun pointing (C-23)", "requirement": "Pointing loss ≤ 5 % of sunlit generation and the Sun within 30° of +Y ≥ 95 % of sunlit time, every trial", "predicted": "2.0 % (3.2 % worst trial) and 100 % with the face photodiodes and Earth albedo; 5.0 % / 96.3 % worst at the 7 mA·m² residual-dipole limit (C-24); one wing at preset 0 ≤ 2.0 %", "margin": "Met", "source": "ADCS_DESIGN 1.9 §11.6" }, { "quantity": "Detumble and capture", "requirement": "≤ 3 orbits", "predicted": "≤ 1.8 h, the slowest in-specification trial (tip-off σ 10°/s, up to 30°/s; ≤ 1.2 orbits)", "margin": "× 2.5", "source": "ADCS_DESIGN 1.9 §11.4" }, { "quantity": "AI beacon energy (D5, C-20)", "requirement": "≤ 0.1 Wh per accepted beacon line", "predicted": "0.065 Wh (SIL G mean under assumed inputs; 0.090 Wh at a 30 % filter reject rate)", "margin": "× 1.5", "source": "SIL_MISSION_SIMULATION G §7; go/no-go VI-02 on the EM" }, { "quantity": "Total dose, 2 mm Al", "requirement": "design 10 krad, margin ≥ 2", "predicted": "4.69 krad at 475 km, 4.91 at the 485 km cap", "margin": "× 2.13 (× 2.04 at the cap); ≥ 2.1 mm kept (× 2.17 at the cap)", "source": "RADIATION_ANALYSIS F" }, { "quantity": "Orbital lifetime", "requirement": "≤ 5 yr after mission, P ≥ 0.9", "predicted": "P ≥ 0.997 at 475–485 km (planned-end reading); wings-failed probability 0.29 %", "margin": "Met; fallback 460 km", "source": "ODAR Draft D" }, { "quantity": "Casualty risk", "requirement": "≤ 1:10,000", "predicted": "No fragment > 15 J (nominal); 1:47,000 worst sensitivity", "margin": "Met", "source": "ODAR Draft D" }, { "quantity": "Reliability", "requirement": "(goals 0.95 / 0.80 / 0.60)", "predicted": "0.75 / 0.61 / 0.51 (L1 / L2 / L3); 0.86 / 0.71 / 0.59 with the burn-in and flatsat programme", "margin": "PI acceptance (REL-01)", "source": "RELIABILITY 2.1" }, { "quantity": "Schedule float", "requirement": "≥ 9.6 weeks (67 d, GOLD 1.06) to the integrator milestone for 2028-11", "predicted": "+71 days (10.1 weeks; layout re-estimated, reliability programme and the board firmware tasks included; −20 d with one layout designer)", "margin": "Met by 0.5 weeks", "source": "SCHEDULE Rev E; `schedule_cpm.py`" } ] }