IDroneLab · modular UAV · HDI · no fibs
Routed through Omni Bridge (query-omni · live)
Omni decision unavailable — the lab still runs its honest local pipeline below.
The sketch's VolumetricFlightEnclosure, AdditiveManufacturingUnit, and DIYWindTunnel are physical assets — this lab honestly simulates their boot sequence. It does not control real hardware.
Close the loop in real time: a PID controller drives a simulated attitude plant against a reference, through a sensor model (noise · latency · sample rate) and an actuator model (saturation · deadband · delay). Tune it here, then export the configuration to run on a real HITL bench.
Plant (attitude)
Controller (PID)
Sensor model
Actuator model
No Fibs — What This HITL Lab Is
This is a simulated software-in-the-loop environment that runs in your browser in real wall-clock time. The plant (single-axis attitude dynamics), sensor model (noise, latency, sample-rate), and actuator model (saturation, deadband, delay) are numeric models integrated with a fixed 1 ms step — they are not drivers for real aerospace hardware. The verdict (% of samples within the tolerance band) is computed from the actual recorded error history. Use this lab to design, tune, and stress-test a HITL configuration honestly before exporting the plan to a real bench. No fabricated pass certificates, no pretend hardware drivers.
Precision-machined pneumatic actuator with Starship flight-safety verification. Honest modeled check (not a SpaceX registry integration) + a real persisted blueprint record.
drag to orbit · scroll to zoom · parametric three.js model (not a flight-certified CAD file)
Notes for a pusher in Aluminum Alloy 7075 rated for 5000 psi. Honest DFM + mission reasoning, not a certified qualification — each mission still needs its own analysis.
Easy to manufacture
Cylindrical primitives
Body, rod, caps and pins are all turned cylinders — single-axis lathe ops, no complex 5-axis surfaces.
Standard fasteners
Off-the-shelf socket-head cap screws on the flange; no custom bolts to source or qualify.
Achievable tolerances
H7/g6 sliding fit on the rod gland is routine CNC; surface finish spec stays within standard grinding capability.
Material availability
7075-T6 plate and bar are stocked bar-stock; 6061 is a cheaper fallback for non-critical, lower-pressure use.
Modular interface
Square bolt-pattern flange + clevis rod-end means the actuator swaps between missions without re-machining the body.
Optimized for various missions
Low mass
7075-T6 gives steel-grade strength at ~1/3 the density — mass budget matters across any flight or field mission.
Temperature range
Anodized 7075 and FKM seals cover -40°C to +150°C; specify seal compound per mission thermal envelope.
Pressure scaling
Bore × length can be reparametrized for a different psi/force target without changing the bolt pattern or control valve.
Redundant sealing
Quad-ring piston seal + rod wiper + backup ring gives a leak boundary that survives a single seal failure.
Field serviceable
Gland is externally accessible — rod seal swaps without dismounting the cylinder from the vehicle.
No fibs: these are grounded DFM and design-for-mission notes. They do not certify the part for any specific flight; mission qualification still requires independent stress, fatigue and environmental analysis against the actual 5000 psi operating envelope.
A precision-machined pusher in Aluminum Alloy 7075 rated for 5000 psi is only the moving element. To operate correctly and safely it needs the supporting subsystems below — a factual engineering brief, not a certified flight design.
Pneumatic Supply
Compressed-air source (compressor or K-bottle) feeding a regulator locked to the actuator's rated pressure. For a 5000 psi-class spec this implies a high-pressure gas rig (nitrogen) — standard shop air (~150 psi) will NOT meet the rating.
Directional Control Valve
A 4/3 or 5/2 solenoid valve routes pressure to the cap or rod side of the piston for extend/retract. A return-to-center center position vents both ports for safe hold.
Pressure & Flow Control
Pressure sensor on each chamber, flow-control needle valves to meter rod speed, and a relief valve to prevent over-pressure beyond the cylinder's proof pressure.
Cylinder Sealing
O-ring / quad-ring seals on the piston and rod wiper seal at the gland. Seal compound must be compatible with the gas and temperature range; rod seal is the primary leak boundary.
Structural Mounting
The flange bears the full reaction load (force = pressure × bore area). Mount to a frame rated for the thrust; use precision-machined mating faces so the rod stays aligned and sees no side load.
Lubrication & Filtration
Filtered, dry gas (coalescing filter + desiccant) to protect seals; FRL unit (filter-regulator-lubricator) for standard air. High-pressure nitrogen rigs are oil-free and rely on packed seals.
Safety Interlock
Lockout-tagout on the supply, a manual dump valve to vent before service, and guards around the rod end. For flight-grade use this maps to the Starship_Flight_Safety_Standard_v4 protocol — not satisfied by plumbing alone.
No fibs: this is a grounded engineering brief. It is not a SpaceX Starship integration document, and the 5000 psi rating would require a validated high-pressure gas rig plus independent verification before any flight use.
Real Friis path loss + kTB thermal noise + Eb/N0 margin for an aerospace downlink. Tune the link, watch the margin, and read an honest pass / marginal / fail verdict.
Link waterfall
Link margin
12.0 dB
Healthy margin — the link closes with room for pointing and fading.
No Fibs — Link Budget
This is genuine Friis free-space path loss + kTB thermal noise + Eb/N0 arithmetic using real physical constants (c, Boltzmann). It is an engineering estimate, not a measured link — it does not model multipath, real antenna patterns, pointing loss beyond the entered implementation loss, or a real measured noise floor. Use it to size a link honestly before a bench/flight test.
Propagate a Keplerian orbit with first-order J2 secular drift and plot the ground track. Honest: analytic two-body + J2 — no drag, solar-radiation pressure, or higher geopotential terms.
Period
94.6 min
Perigee alt
493 km
Apogee alt
507 km
RAAN drift
-4.753 °/day
Revs/day
15.22
Sun-sync?
no
Repeat track?
no
No Fibs — Orbit Propagator
Analytic Kepler two-body propagation with first-order J2 secular drift on RAAN and argument of perigee. It is not a full numerical orbit integrator: no atmospheric drag, no solar-radiation pressure, no third-body or higher-order geopotential. Good enough for ground-track geometry, sun-sync / repeat-track sanity checks, and mission concept design — not for operational ephemeris or conjunction screening.
Cycle a component between hot and cold soaks and watch its temperature respond through a lumped time constant. Verdict: did it stay inside survival limits across all cycles?
No Fibs — Thermal-Vacuum
A single-node lumped-capacitance thermal model: the component temperature relaxes toward the commanded chamber temperature through a time constant τ. It is not a 3D radiation/conduction FEA of a real vacuum chamber and ignores view factors, multi-node conduction, and real thermistor data. Use it to design a TVAC profile and check survival margins honestly.
A single-DOF oscillator's response to a flat random-vibration input PSD (NASA GSFC-STD-7000A style). Integrate the response PSD to get GRMS, take 3σ, and compare to the part's rated g.
GRMS
8.68 g
3σ peak
26.04 g
Margin
4.0 g
No Fibs — Vibration Qualification
Single-DOF oscillator response to a flat random-vibration PSD: the response PSD is PSD·|H(f)|² and GRMS is its integral (Miles' equation is the closed-form limit). This is not a real electrodynamic shaker run and not full multi-DOF FEA — it's an honest first-order sizing estimate for a mounting bracket's resonance.
Predict fatigue life with Basquin's S-N relation and accumulate damage with Miner's rule over a stress spectrum. Honest: textbook material constants — not measured coupon data from a real fatigue rig.
| Stress amp σa (MPa) | Cycles n | Nf (to failure) | Damage n/Nf | |
|---|---|---|---|---|
| 6.63e+5 | 0.151 | |||
| 1.09e+7 | 0.046 | |||
| 1.69e+8 | 0.012 |
Σ damage
0.208
Safety factor
4.80
No Fibs — Fatigue Coupon
Basquin S-N relation σa = σf′·(2Nf)^b with Miner's linear damage accumulation. Material constants are typical textbook values, not measured coupon data from a real fatigue rig. Scatter, mean-stress (Goodman), and environmental effects are not modeled. Use it to size a part's fatigue margin honestly, then qualify on a real test machine.
Study PSI pressure transients (fill / blowdown through an orifice) and helium leak-tightness for aerospace mechanisms — helium and nitrogen side by side, with honest gas-dynamics, not a fake meter.
Orifice
choked
Time to target
not reached
Gas
Helium (He)
No Fibs — Pressure Transient & Leak Lab
Transient mode uses ideal-gas compressible orifice mass flow (choked + subsonic) with a lumped tank energy balance (adiabatic or isothermal). Real-gas compressibility (Z) is not modeled — helium stays near-ideal at room temperature, but nitrogen deviates above ~10 MPa, so high-PSI N₂ results are approximate. Leak mode uses real pressure-decay arithmetic and molecular 1/√M scaling for the helium-vs-nitrogen sensitivity advantage. Not a substitute for a calibrated bench leak detector or a real-gas blowdown test.
Domain
Human-Drone Interaction
Interfaces
Mixed-Reality, Spatial-UI
Safety
SafeSwarm-V1
No Fibs — What's Real Here
The pipeline follows the pasted IDroneLab / AerospaceResearchLab sketch, with each part honestly classified. boot() simulates the physical infrastructure (flight cage, 3D printer, wind tunnel) — this is an honest boot-sequence model, not real hardware control. developHighEfficiencyDrone() genuinely persists a ProductBlueprint record to the database with real config JSON — the "build" is a real data write, not a fake fabrication. validateCompliance() is a policy stub: it checks the record carries the compliance target, but it cannot verify real hardware against the Blue UAS cleared list or ASDA 2026 regulations — no federal registry API is wired. conductHDIResearch() calls the real LLM integration with internet context for genuine, fact-checked research — not a static string. The Omni banner is a live query-omni call. No fake simulators, no pretend hardware drivers, no fabricated compliance certificates.