A-4 Wanderer: Difference between revisions
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[[Image:A-4.png|thumb|right|500px]] | [[Image:A-4.png|thumb|right|500px]] | ||
The [[A-4 Wanderer]] is a light scout [[:Category:Aircraft|aircraft]], capable of carrying one | The [[A-4 Wanderer]] is a light scout [[:Category:Aircraft|aircraft]], capable of carrying one [[ARJ]] or small [[:Category:Vehicles|vehicle]].<br /> | ||
=== Statistics === | === Statistics === | ||
{{AirVehicle | |||
|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 | |||
|landing_gear_type=Skids, three strut groups | |||
|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. Skids resist longitudinal and lateral movement through surface friction. Their design strength in both horizontal directions is twice that of equivalent wheeled gear at this vehicle’s own maximum gross mass. This multiplier does not increase the vertical touchdown design envelope. | |||
|cabin_pressurization=Pressurized — atmospheric gas intake | |||
|max_pressure_diff=2,100 mbar (210 kPa), cabin above surroundings | |||
|manufacturer=[[:Category:Trimbal-Kneers Aerospace|Trimbal-Kneers Aerospace]] | |||
|role=Light scout aircraft | |||
|cargo_bays=1 | |||
|stowage=1 MT | |||
|weapon_mounts=2 | |||
|avionics_bays=2 | |||
|bypass_ratio=20% | |||
|critical_altitude=6 [[kilometer|km]] [[MSL]] | |||
|service_ceiling=22 [[kilometer|km]] [[MSL]] | |||
|max_speed=225 [[meter|m]]/s | |||
|fuel=9 MT | |||
|weight=17,158 kg | |||
|max_weight=41,067 kg (takeoff) | |||
|price=5,411,199 [[CR]] | |||
|vtol=Yes | |||
|rain_protection=None | |||
}} | |||
===Standard Equipment=== | ===Standard Equipment=== | ||
* [[GPWS]] | * [[GPWS]] | ||
* [[Autoflyte]] | * [[Autoflyte]] | ||
* 320 [[kilometer|km]] [[LRS]] with [[TCAS]] | * 320 [[kilometer|km]] [[LRS]] with [[TCAS]] | ||
== Vertical thrust == | |||
The two main engines use opposing outlets that tilt down through '''54°'''. Hold '''F9''' to request upward thrust; forward or reverse thrust can be requested at the same time. No separate nozzle control is required. The A-4 has no aft engine. | |||
Main-engine nozzle vectoring has no altitude cutoff, including in vacuum. This does not remove the aircraft's flight-envelope limits or guarantee sufficient lift: power, engine condition, loading and balance determine the delivered force. Outside [[TVM#Vertical Landings|TVM ground-reference BCL descent control]], '''F8''' requests downward RCS. Downward RCS is much weaker than main-engine upward thrust, so allow time and distance to stop upward motion. See [[VTOL#Operating envelope|VTOL operating limits]] and [[TVM]] for control and transition details. | |||
== External Links == | == External Links == | ||
* [ | * [https://docs.google.com/spreadsheets/d/1LZlgMvasAq8s136n7vyUHRAif-GTyVNW9jFN70Lf7ug/edit?usp=sharing Detailed specifications] | ||
[[category:vehicles]] | [[category:vehicles]] | ||
[[category:aircraft]] | [[category:aircraft]] | ||
[[Category:Trimbal-Kneers Aerospace]] | [[Category:Trimbal-Kneers Aerospace]] | ||
Latest revision as of 16:27, 9 November 2026
The A-4 Wanderer is a light scout aircraft, capable of carrying one ARJ or small vehicle.
Statistics
| General | |||
|---|---|---|---|
| Manufacturer | Trimbal-Kneers Aerospace | Type / role | Light scout aircraft |
| Price / MSRP | 5,411,199 CR | Availability | Not specified |
| Restrictions | Not specified | IVR series | Not specified |
| Dimensions and weights | |||
| Length | Not specified | Width | Not specified |
| Height | Not specified | Empty / curb weight | 17,158 kg |
| Fuel capacity | 9 MT | Payload | Not specified |
| Maximum gross / takeoff weight | 41,067 kg (takeoff) | ||
| Capacity and equipment | |||
| Seats | Not specified | Passenger capacity | Not specified |
| Cargo bays | 1 | Cargo capacity | Not specified |
| Internal stowage | 1 MT | Avionics bays | 2 |
| Weapon mounts | 2 | Engine count | Not specified |
| Life support | |||
| Cabin pressurization | Pressurized — atmospheric gas intake | Rated pressure differential | 2,100 mbar (210 kPa), cabin above surroundings |
| Performance | |||
| Engine / propulsion | Not specified | Maximum speed | 225 m/s |
| Normal range | Not specified | Endurance | Not specified |
| Flight | |||
| Wingspan | Not specified | Effective wing area | Not specified |
| Cruising speed | Not specified | Service ceiling | 22 km MSL |
| Engine critical altitude | 6 km MSL | Bypass ratio | 20% |
| Thrust | Not specified | Maximum acceleration | Not specified |
| VTOL capability | Yes | Rain Protection Type | None |
| Flight controls and landing gear | |||
| Flight Spoilers | Not specified | Ground Lift Dump (GLD) | Not specified |
| Retractable Landing Gear | Not specified | Landing Gear Type | Skids, 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 |
The descent design value is a structural reference, not a target landing rate. Uneven contact, damaged gear and excess mass reduce the landing margin. Skids resist longitudinal and lateral movement through surface friction. Their design strength in both horizontal directions is twice that of equivalent wheeled gear at this vehicle’s own maximum gross mass. This multiplier does not increase the vertical touchdown design envelope.
Standard Equipment
Vertical thrust
The two main engines use opposing outlets that tilt down through 54°. Hold F9 to request upward thrust; forward or reverse thrust can be requested at the same time. No separate nozzle control is required. The A-4 has no aft engine.
Main-engine nozzle vectoring has no altitude cutoff, including in vacuum. This does not remove the aircraft's flight-envelope limits or guarantee sufficient lift: power, engine condition, loading and balance determine the delivered force. Outside TVM ground-reference BCL descent control, F8 requests downward RCS. Downward RCS is much weaker than main-engine upward thrust, so allow time and distance to stop upward motion. See VTOL operating limits and TVM for control and transition details.