W-6 Manx: Difference between revisions
From Rise: The Vieneo Province
(Link the reconciled W-6 specification worksheet) |
(Document landing-gear design descent, grip behavior and unestablished crosswind limit) |
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|payload=43,009 kg | |payload=43,009 kg | ||
|max_weight=105,009 kg (gross) | |max_weight=105,009 kg (gross) | ||
|landing_gear_type=Wheels, three strut groups | |||
|touchdown_descent_design=10 ft/s (3.048 m/s; 600 ft/min), at maximum gross mass with healthy, fully deployed gear and balanced contact on a firm, level surface | |||
|crosswind_component_limit=Not established; this is not an unlimited-crosswind rating | |||
|notes=The descent design value is a structural reference, not a target landing rate. Uneven contact, damaged gear and excess mass reduce the landing margin. Braking and sideways tire forces share the available surface grip; skidding alone does not mean a strut has failed. | |||
|vtol=Limited | |vtol=Limited | ||
|orbital_capability=Capable of reaching [[orbit]] and [[escape velocity]] | |orbital_capability=Capable of reaching [[orbit]] and [[escape velocity]] | ||
Revision as of 16:24, 9 November 2026
W-6 Manx Class
The W-6 is a limited-VTOL-capable aerospace vehicle, in so far as it has conventional flight surfaces but is also capable of ascending beyond the atmosphere, maneuvering in orbit and re-entering under its own power.
The protected downward main-engine outlets are available on request wherever aerodynamic loading permits, including high altitude and orbit. Door protection uses dynamic pressure: downward flow is inhibited above 4,000 Pa, and can re-enable below 3,200 Pa. There is no separate speed, altitude or vacuum cutoff. The doors take about 0.6 seconds to open, and must be fully open before downward thrust starts. Forward, reverse and downward flow share each engine's existing thrust budget. See VTOL operating envelope for sequencing, pressure hysteresis and orbital braking considerations.
Statistics
| General | |||
|---|---|---|---|
| Manufacturer | Trimbal-Kneers Aerospace | Type / role | Aerospace vehicle |
| Price / MSRP | 3,989,373 CR | Availability | Not specified |
| Restrictions | Not specified | IVR series | Not specified |
| Dimensions and weights | |||
| Length | 44.9 m | Width | Not specified |
| Height | 9.4 m (with gear) | Empty / curb weight | 50,000 kg (BOW) |
| Fuel capacity | 12,000 kg (Iagreous) | Payload | 43,009 kg |
| Maximum gross / takeoff weight | 105,009 kg (gross) | ||
| Capacity and equipment | |||
| Seats | Not specified | Passenger capacity | 6 in Bay 0 instead of cargo |
| Cargo bays | 3 | Cargo capacity | Not specified |
| Internal stowage | 7 MT (Bay 0), or 6 passengers | Avionics bays | 4 |
| Weapon mounts | 1 | Engine count | 2 |
| Life support | |||
| Cabin pressurization | Pressurized — stored breathing gas | Rated pressure differential | 2,400 mbar (240 kPa), cabin above surroundings |
| Performance | |||
| Engine / propulsion | Not specified | Maximum speed | 94 m/s IAS at MSL |
| Normal range | Indefinite (capable of reaching orbit) | Endurance | Not specified |
| Flight | |||
| Wingspan | 50.1 m | Effective wing area | 640.965 m2 |
| Cruising speed | 539 m/s at 15 km | Service ceiling | Indefinite (capable of reaching escape velocity) |
| Engine critical altitude | Not specified | Bypass ratio | Not specified |
| Thrust | 1,029,779 N total forward/reverse in vacuum (514,890 N per engine); about 947,397 N total at reference sea-level density | Maximum acceleration | Main thrust alone at maximum gross: 9.807 m/s² in vacuum, 9.022 m/s² at reference sea-level density; before drag and gravity |
| VTOL capability | Limited | Rain Protection Type | Bleed air system |
| Flight controls and landing gear | |||
| Flight Spoilers | Not specified | Ground Lift Dump (GLD) | Not specified |
| Retractable Landing Gear | Not specified | Landing Gear Type | Wheels, three strut groups |
| Touchdown descent design limit | 10 ft/s (3.048 m/s; 600 ft/min), at maximum gross mass with healthy, fully deployed gear and balanced contact on a firm, level surface | Crosswind component limit | Not established; this is not an unlimited-crosswind rating |
| Leading Edge Flaps | Not specified | Trailing Edge Flaps | Not specified |
| Space operations | |||
| Orbital capability | Capable of reaching orbit and escape velocity | Interstellar capability | Not specified |
| Docking / interfaces | Not specified | ||
The descent design value is a structural reference, not a target landing rate. Uneven contact, damaged gear and excess mass reduce the landing margin. Braking and sideways tire forces share the available surface grip; skidding alone does not mean a strut has failed.
Standard Equipment
- GPWS
- VMU engine-failure warnings and flap-position confirmations.
- Trailing-edge flap detents at 0°, 8°, 20°, 30° and 40°. The default bindings are Shift+F8 to extend one detent and Shift+F9 to retract one detent; custom bindings may differ. The VMU confirms the selected detent when the flaps reach it, in either direction.
- Autoflyte
- VTOL
- 320 km LRS with TCAS