End-to-End Mission Feasibility Wizard
Coupled preliminary sizing tool for PocketQube and CubeSat missions: orbit, solar power, battery ageing, UHF link margin, and 5-year deorbit rule.
Coupled Mission Verdict
Coupled preliminary sizing across orbit, power, battery cycle life, UHF link margin, daily ground contact, and FCC 5-year deorbit compliance.
PHASE 2 · MECHANICAL & ECAD TEMPLATES
Parametric PocketQube (1P–3P) & CubeSat (1U–6U) CAD / KiCad Generator
Generate PocketQube Standard Issue 1 (1.6 mm sliding backplates, 42×42 mm stack PCBs) and CubeSat Design Specification Rev. 14.1 (8.5 mm rails, 3D STEP envelopes, and 90×96 mm PC/104 boards).
1P sliding backplate (58.0 × 64.0 × 1.6 mm) with deployer tab margins.
3D AP214 mechanical keep-in envelope (50 × 50 × 50 mm) and 1.6 mm baseplate datum.
42.0 × 42.0 mm internal avionics stack PCB outline with 4× M2 standoff holes (35.0 mm pitch).
ENGINEERING DISCLAIMER: Generated .DXF, .STEP, and .kicad_pcb files are provided "AS IS" for preliminary sizing and educational reference only. Verify all tolerances and keep-out zones against your Launch Service Provider ICD before manufacturing.
DETERMINISTIC PHYSICS & DATA METHODOLOGY
How This Calculator Works
Source modules: lib/physics/{orbit,power,battery,link-budget,decay,torques,structures}.ts
Couples seven subsystem solvers into a single preliminary mission trade-study: Sun-synchronous orbit power balance, illustrative Li-ion cycle ageing, 437 MHz UHF link margin at 20° elevation, daily J2 ground-station data volume, Kennewell orbital decay, environmental disturbance torques, and backplate fundamental bending frequency.
Governing Equations & Physical Model
P_margin = P̄_sun(A_tot, h) − (P_base + d_tx·P_tx + d_pl·P_pl), DoD = (P_load · t_ecl) / E_battEvaluated at worst-case β = 0° cylindrical shadow with fixed bus quiescent (105 mW) and UHF TX DC draw (850 mW at 5% duty).
D_day = (t_contact,day · R_b · η_frame) / 8000 [kB/day]Propagates a 97.5° SSO over 5 days with J2 nodal precession above a 10° elevation mask and 65% AX.25/FEC framing efficiency.
τ_total = τ_gg + τ_aero + τ_srp + τ_mag, f₁ = (λ₁ / 2π) · ½(a⁻² + b⁻²) · √(D / ρ_eff)Identifies dominant LEO attitude disturbance source and checks Al 7075-T6 1.6 mm baseplate stiffness against launch acoustic/random loads.
Inputs, Parameters & Units
| Parameter | Unit | Physical definition |
|---|---|---|
| Form factor, m | 1P–3P / 1U, g | Envelope selection (setting A_tot and pack energy 8.5–38 Wh) and wet launch mass. |
| h, φ_gs | km, °N | Circular SSO altitude and ground-station geodetic latitude. |
| P_pl, d_pl | mW, % | Payload active power draw and orbital duty cycle. |
| P_tx, R_b | dBm, bps | Transmitter RF power and UHF non-coherent FSK bit rate into the 14 dBi / 500 K reference station. |
Assumptions & Validity Limits
- Battery cycle-life output uses the illustrative empirical ageing curve in lib/physics/battery.ts (for trade-study sensitivity only, not cell qualification).
- UHF link margin is evaluated against REFERENCE_DOWNLINK (3 dB pointing + 3 dB polarization + 1 dB atmospheric + 2 dB implementation loss) at 20° elevation.
- FCC 5-year compliance verdict checks passive lifetime ≤ 5.0 years under moderate solar activity (F10.7 = 140 sfu, Ap = 12).
Worked Default Reference Case
Power (+352 mW margin, 1.3% DoD) and FCC 5-year passive decay (2.6 years) close comfortably, while 22 dBm (158 mW) at 9600 bps shows a −2.2 dB deficit at 20° elevation—highlighting why 1P UHF links step down to 4800 bps or raise RF power toward 27 dBm.
- Orbit power margin / DoD
- +352 mW / 1.3% DoD
- UHF margin (20° el, 9600 bps)
- −2.2 dB (flagging rate/power trade)
- Daily contact data (41.45°N)
- 909 kB/day (19.4 min/d)
- Moderate lifetime & 1st mode f₁
- 2.6 years (PASS) · 1,997 Hz