The SM-47 SUPER MACHETE is a highly maneuverable, supersonic Light Strike Fighter (LSF) derived from the SM-27J/L Turbofan Machete. The most significant evolution of the Machete series, the Super Machete marries a Turbofan Machete derivative fuselage to a Forward Swept Wing (FSW) augmented by custom canard foreplanes and a distinctive empennage and an engine bay which accommodates a 22,000 to 25,000 static thrust class turbofan. Presenting greater capabilities than the standard turbofan Machete, the SM-47 is oriented toward fulfilling both Fighter, Attack and Advanced Pilot Trainer roles.

supersonic aircraft envisioned to succeed F-5 and A-4 types in intercept, aggressor and precision attack roles, the Super Machete benefits from overall economics of the Machete family while providing true air-to-air combat ability. Of dissimilar arrangement, in addition to satisfying Light Strike and Fighter capabilities, the SM-47 is an aggressor type aircraft with substantially lower operating costs than current fast jets, including the F-16s and F/A-18s now used in the aggressor role.

The SM-47 will be produced in manned, as well as unmanned/remote pilot-in-the-loop and unmanned autonomous configurations. The manned SM-47 will be produced in two variants: The single seat SM-47S and two seat tandem SM-47T. The SM-47S will satisfy strike, intercept, Air Defense Fighter and Aggressor Missions while the SM-47T will serve as a two seat strike fighter or as a mission capable, high performance supersonic trainer/Advanced Pilot Trainer (APT).

Power for the SM-47 is provided by a single 22,000 lb st to 25,000 lb st class turbofan powerplant including a single Afterburning GEAE F414-GE-400 derivative engine mounted within a custom engineered, modular engine bay. Powerplant airflow is supplied by laterally mounted, bifurcated fuselage normal shock pitot inlets. An aft fuselage/exhaust duct mounted axisymmetric, lower observability variable geometry thrust vectoring exhaust nozzle may be fitted for improved engine performance.

A single piece bubble canopy and pressurized cockpit with zero-zero crew-member escape capability is provided. Flight controls are of four-channel, Fly-By-Wire, artificial force-feedback type with yaw dampening. Tricycle landing gear consisting of a forward retracting oleo-pneumatic nose strut and inboard wing/fuselage retracting oleopneumatic main gear is employed.

A comprehensive integrated avionics suite, including Electronic Warfare/Electronic Counter Measures (EW/ECM) is featured. Stores and ordinance is carried on eight wing hardpoints. Typical fixed internal armament includes a nose mounted 20mm cannon with up to 1,000 rounds of ammunition for the Fighter role and 500 rounds in the Advanced Pilot Trainer role. A ventrally mounted conformal fuel tank may be fitted to the aircraft fuselage, incorporating a total of four weapons hardpoints, increasing the total number of available external stores hardpoints to twelve. Standard SM-47S/T external armament include wing-tip rail mounted AIM--9 X Sidewinders augmented by a host of wing mounted AIM-120s or precision guided ordinance.

The SM-47S/T will be qualified at the AFFTC at Edwards, AFB. The SM-47 will be certified to applicable FAA type and production certification standards (FAR 25, etc.) as a fully qualified Day/Night VFR and IFR (VMC/IMC) aircraft.


The SM-47 cockpit is designed to accommodate a wide spectrum of male and female crewmembers encompassing the 1st percentile female through the 99th percentile male (NATO) population range. This population range corresponds to crewmembers ranging from 5 ft 4in/100 lbs through 6 ft 4 in/250 lbs. For planning and engineering development purposes, assumed standard crew-member weight is 260 lbs, including survival equipment.

The SM-47S flight crew consists of a single pilot seated on a Martin Baker MK.16E zero/zero ejection seat. The SM-47T flight crew consists of a pilot and Weapon Systems Officer (WSO)/Observer seated in tandem (fore and aft crewstations respectively) on Martin Baker MK.16E zero/zero ejection seats in satisfaction of the strike role. In satisfaction of the Supersonic Trainer role, the SM-47T flight crew consists of a student and instructor seated in tandem (fore and aft crewstations respectively) in on Martin Baker MK.16E zero/zero ejection seats. Total standard SM-47T crewmember weight, including survival equipment, is 520 lbs.


The GEAE F414-GE-400, F414G or F414 EDE will power the SM-47, providing between 22,000 lbs to over 25,000 lbs of static thrust at sea level. The F414-GE-400 powers the F/A-18E/F Super Hornet while the F414G will power the Saab JAS 39C Gripen. With an engine bay designed to accommodate current and future members of the F414 family, the SM-47 benefits from a proven, reliable powerplant with over 900,000 accumulated flight hours worldwide.

The F414-GE-400 delivers 35% more thrust than the F404 from which it was derived, producing 22,000 lbs static thrust at SL in maximum AB. Featuring a Full Authority Digital Electronic Control (FADEC) and improvements in component materials which allow higher operating temperatures, the F414 benefits from long-chord blisk fan technology.The F414-GE-400 produces over 22,000 lbs maximum thrust with afterburner and 14,756 lbs maximum military thrust. The F414-GE-400 has a three stage fan, a seven stage high temperature compressor and a two stage turbine with one low pressure and one high pressure turbine stage.

Turbofan airflow is supplied via twin, rectangular, bifurcated fuselage side mounted air intakes which are raked aft 48 degrees. Spaced apart from the fuselage by an integral boundary layer diverter, the air inlets are of fixed, pitot type offering a capture area of 640 sq in for mass flows over 150 lbs/s. Designed for high pressure recoveries through the transonic and low supersonic regimes, the air inlets permit theoretical operations beyond Mach 2.0. The air inlets are heated to prevent icing. U.S. domestic SM-47s will feature air inlet RAM to reduce engine/intake radar signature.

To permit supersonic flight, the SM-47 is equipped with a variable geometry, axisymmetric exhaust nozzle standard to the F414-GE-400 powerplant. To further enhance maneuverability, thrust vectoring may be incorporated into the exhaust nozzle to enhance both pitch and yaw and enable Post Stall Maneuvering (PSM). This thrust vectoring nozzle will be based upon the GEAE AVEN Multi-Axis Thrust Vectoring Nozzle.


SM-47S/T Super Machete armament includes both fixed internal and expendable, external carried weapons.

SM-47S/T fixed internal armament includes one nose mounted 20mm cannon. The 20mm cannon is mounted dorsally within the aircraft nose on a vibration dampening mount. 20mm cannon ammunition is fed through a link-less feed system supplied by a fuselage located armored ammunition drum. Ammunition is loaded/serviced through a ventral fuselage loading hatch. The cannon provides the aircraft with anti-aircraft capability.

The standard SM-47S/T cannon is the General Dynamics M61A2 20mm Vulcan cannon. The M61A2 is a six-barrel, hydraulically driven cannon with a rate of fire of 6,000 rds/min to 6,600 rds/min. The M61A2 employs standard 20mm PGU-28/B ammunition with a muzzle velocity of 3,450 ft/sec.

The single seat SM-47S is armed with 1,000 rds of 20mm ammunition contained within an armored ammunition drum located in the aircraft fuselage. The two seat SM-47T carries 500 rds of 20mm ammunition contained within an armored ammunition drum located below the two seat tandem cockpit module.

For those aircraft dedicated primarily to the Air-to-Ground mission, Super Machetes may be equipped with a 25mm GAU-12/U cannon with 975 rounds 20mm M61A2 in lieu of the 20mm M61A2. Either the GAU-12/U or the M61A2 will be mounted as fixed, internal armament within the aircraft nose.

The SM-47 will carry up to 11,000 lbs of external stores on a total of eight external, wing-mounted hardpoints equipped with NATO suspension lugs

The hardpoints include four underwing mounted hardpoints rated to 2,500 lbs maximum external carriage capacity at a +7.5 g load factor. The underwing hardpoints are plumbed for external fuel tanks, including the Sargent Fletcher #401315 150 USG tank as shared by the T-50. The two remaining hardpoints are featured on the SM-47 wing-tips for the carriage of AIM-9 and AIM-120 AAMs with a maximum rating of 500 lbs at +7.5 g load factor.

The Super Machete is designed primarily for air-to-air and air-to-ground missions, employing ordinance such as the AIM-9, AIM-120, AGM-65, GBU-39/B Small Diameter Bomb, GBU-31 JDAM, GBU-32 JDAM, GBU-38, CBU-97, CBU-59, BLU-107, AGM-154 JSOW, AGM-84E SLAM and additional stores.

The Super Machete is capable of LANTIRN, LITENING and ECM pod carriage and employs a MIL-STD-1760 Weapon Interface Data Bus. Weapons release is conducted through a control column gun trigger switch and weapon release button for air-to-air/air-to-ground. An abridged SM-47 stores loading chart is provided:


SM-47 avionics are integrated about a MIL-STD-1553B Interface/Data Bus with Data Bus Wiring used throughout the system architecture to reduce wiring bundles. The SM-47 features a comprehensive navigation/communications suite. The philosophy driving the SM-47 avionic configuration emphasizes mission completion, reliability, flexibility and ease of serviceability. Avionics may be of a variety of types including either COTS or MOTS. Wherever possible, avionics are of modular LRU type with BIT. Principal avionics and sensors are contained in two to three bays including the nose radome/sensor bay, forward fuselage avionics bay and aft cockpit avionics bay as available in the SM-47S.

The avionics/sensor suite is designed and integrated by Stavatti based upon customer specifications. Stavatti has developed a STANDARD (NATO EXPORT) AVIONICS/SENSOR CONFIGURATION which includes a variety of proven, reliable systems from which NATO end-users may select a specific Super Machete configuration. This STANDARD configuration is optimized to permit unrestricted export of the Super Machete via Direct Commercial Sales (DCS) to the majority of NATO members, although specific avionics, including GPS with PPS, as well as particular COMSEC/TEMPEST equipment, must be procured via FMS or on a government-government basis. Principal sensors and avionics included in the Standard Configuration are:

• Lockheed Martin AN/APG-67 Multi-Mode Pulse Doppler Radar mounted in the forward Radome

A detailed listing of principal avionics and sensors which are included in the STANDARD Super Machete configuration is provided on the SM-47 Super Machete Performance & Specifications webpage.

The cockpit is equipped with a Cockpit Video Recording (CVR) system capable for recording at least 120 minutes of HUD symbology, the external HUD field of view, cockpit LCD MFD symbology and all aircraft communication system audio. The aircraft is also equipped with a crash survivable Flight Data Recorder (FDR) capable of storing the last 90 minutes of flight data for post-crash flight reconstruction. The aircraft is fitted with a Crash Position Indicator (CPI) and a survivable Underwater Locator Beacon (ULB). Halon 1301 is employed for avionic system fire suppression within sealed avionic bays.


The cockpit is available in two configurations: the single seat SM-47S and the two seat tandem SM-47T. Each configuration is designed for reduced workload operations with crewmembers seated on unreclined Martin Baker MK.16E ejection seats. To increase G-tolerance SM-47 ejection seats are mounted in a reclined position. Both Super Machete models incorporate pilot selectable auto-eject and auto-eject sequencing. The cockpit is pressurized to 8,000 ft and air-conditioned. Standby crew oxygen is provided by a Carlton OC1132 Molecular Sieve Oxygen Generating System (MSOGS).

The cockpit for SM-47 is a completely modular unit, produced as a unitized, self contained system external to the fuselage. Incorporating distinct, armored and EM hardened quick interconnects for flight controls, electrical junctions, avionics buses and environmental control, the Super Machete cockpit is installed and extracted vertically in the absence of the bubble canopy. Cockpits for either model attache to the CAM bath-tub structure through bolts in vibration damping fittings.

The CAM, featuring armor plate and Spectra® fiber significantly mitigates the penetrative effects of projectiles and spall. Cockpit modules are interchangeable, allowing a specific aircraft to be converted to either a single seat or two place tandem variant.

The aircraft bubble canopy is of large area, frame-less, single-piece clamshell type. The canopy is of advanced bullet resistant polycarbonate composition that is slightly thicker than the canopy of the SM-27. The SM-47 canopy can safely sustain the impact of a 4 lb bird at airspeeds exceeding 570 kts from any attitude. Visibility is 350° azimuthal with 13° over-the-nose and 25° over-the-side. The canopy is hydraulically lifted upward for cockpit access. The canopy is defrosted and purged of precipitation using a perimeter high pressure, powerplant bled, hot air system. An internally mounted, manual unlatch and hand-crank is provided.

All Super Machete models benefit from a HOTAS flight controls arrangement consisting of a right hand/starboard mounted Flight Control Grip (Mason Electric/F-16 derivative) right console mounted flight control column, limited deflection rudder pedals, and left console power control lever (Mason Electric/F-16 Grip Derivative). Stick and throttle flight control grips are provided by Mason Electric and are based upon current production articles for the F-16 Block 50+ to reduce tooling complexity. HOTAS provides toggles for aircraft trim, sensors, weapons release, microphone, etc. Rudder pedals are fully adjustable.

The primary visual flight reference display is the CMC Night Hawk wide field-of-view HUD and HUD repeater system. Secondary flight reference instruments include five L-3 Communications Actiview 104P 6 x 8 in LCDs in the SM-47S and in the forward cockpit of the SM-47T. A VSI Integrated HMDS may be used as an alternative to the HUD for the forward crew station.

The aft panel of the SM-47T is largely identical to that of the forward panel, with exception of the HUD being replaced by a HUD repeater and the addition of a sixth LCD MFD. IFR certified, the cockpit is designed for Generation III night vision compliance and Helmet Mounted Cuing Systems/Integrated Helmet and Display Sighting Systems (HMCS/IHDSS). Forward and rear panels are complemented by a comprehensive warning annunciator panel.

The forward panel of the SM-47S/T smoothly integrates the Machete HUD, MFDs and standby flight reference instruments. A conceptual Cockpit Arrangement and layout drawing is provided to the left.


The SM-47 employs an internal Electronic Counter Measures (ECM) suite. The SM-47 EW system accommodates a wide variety of external jamming pods and countermeasures dispensers and includes Radar Warning Receivers, Laser Warning Systems, Self Protection Jammers and Advanced Missile Warning Sensors. The ECM suite is designed and integrated by Stavatti based upon customer specifications. Stavatti has developed a Standard (NATO Export) ECM/EW Configuration which includes demonstrated as well as next generation electronic warfare systems which may equip the Super Machete.

This Standard configuration is designed to satisfy the needs of the majority of potential NATO customers without export restriction, however, particular ECM systems must be procured on an FMS or government to government basis. Typical SM-47 ECM systems include:

• Ten (10) AN/ALE-47 Countermeasures Dispensers of USAF style
• The ATK AN/AAR-47 Missile Warning System

A complete listing of additional ECM systems which are included in the Standard Machete configuration is provided on the SM-47 Machete Performance & Specifications webpage.


SM-47 primary structure is an amalgamation of composite and advanced alloy materials. By weight, 33% of the aircraft structure is composite material, 55% is advanced alloy and 12% is polycarbonate and other non-metallic materials.

Approximately 31% of the aircraft structure is comprised of Hexcel IM9 graphite fiber suspended in a matrix of hi-temperature polyimide resin, also known as Graphite Reinforced Plastic (GRP). Graphite composite components include primary structural members such as fuselage skins, vertical stabilizer skins, horizontal stabilizer skins, flaps and flight control surfaces.

Nearly 4% of the aircraft structure consists of Dupont Kevlar® 149,129 or 29 aramid fiber suspended in a matrix of epoxy or polymer resin, refered to hereafter as Kevlar Reinforced Plastic (KRP). Approximately 2% of the aircraft structure is composed of Honeywell
Spectra® 2000 fiber of 650 and 1,200 denier employed in a ballistic capacity or suspended in a matrix of epoxy or polymer resin, hereafter referred to as Spectra® Reinforced Plastic (SRP). KRP and SRP composites are used within the aircraft fuselage structure as a secondary structure and as a discrete ballistic armor. KRP and SRP are used as the primary structural material for radome, antenna fairings, support and access panels, engine cowling and in discrete armor throughout the aircraft.

SM-47 alloy components include principal load-bearing elements and aero-structures such as wing and canard skins, spars, ribs, fuselage subframe, engine firewall and mounts, landing gear, electronic/ subsystems mounting chassis, electronics Faraday cage and as a component of all discrete armor.

Approximately 6% of the aircraft structure consists of Alcoa produced Aluminium alloys including 7150-T7751 Aluminum, 7075-T651 Aluminum, 7055-T7751 Aluminum and other high performance aircraft aluminum. Aluminum is used in the aircraft wing skins, canard skins, vertical stabilizer skins, fuselage and landing gear structure.

Nearly 49% of the SM-47 structure is composed of Titanium alloys including the general purpose Ti-6Al-4V Titanium, SP 700 Titanium, Ti-15V-3Cr-3Sn-3Al, and Ti-6Al-2Zr-2Sn-2Mo-2Cr-0.25Si (Ti-6222) Titanium for airframe structural elements.

Titanium primary structures include wing spars, ribs and fuel tanks, canard spars and ribs, empennage spars and ribs, fuselage subframe, empennage stabilizer booms, canopy frame, landing gear struts and hardware, aircraft firewall and engine bay and in discrete armor. Titanium components are produced using laser forming, laser machining and traditional aerospace Titanium part production methodologies. Titanium components are fastened to the aircraft structure via laser welding, Titanium Bolts and Huck Ti-Matic rivets as appropriate. Additional alloys used throughout the SM-47 include 2090-T83 Aluminum Lithium, and PH 15-7 Stainless Steel.

Additional composite materials used throughout the aircraft include Hexcel IM7/polyimide, Kevlar®-49/epoxy, Kevlar®-29/epoxy, Kevlar®-129/epoxy and Spectra® 1000/epoxy. These and other alloys and composite materials constitute over 6% of the SM-47 structural weight. Nearly 7% of the remaining SM-47 structural composition consists of the transparent polycarbonate material used in the thicker and sturdier Super Machete clamshell bubble canopy.

The SM-47 is designed for an operational service life of 15,000 hours, accumulating an average of 750 hours per annum. Aircraft fatigue life will be based upon 30,000 takeoffs and landings (cycles). The aircraft maximum design load factor limit is +7.8g and -3.9g at Maximum Gross Takeoff Weight (MTOW) with maximum external stores. The SM-47 will regularly "pull" up to +13.0gs as an unmanned autonomous aircraft armed with 2 x AIM-9 and 4 x AIM-120 in the air intercept configuration.


The Super Machete fuselage is a compact unit consisting of the fuselage core, radome and engine cowling. The fuselage is largely similar to that of the SM-27J/L thru Fuselage Station F.S. 172. The fuselage core is a unitized structure consisting of a Titanium and Aluminum sub-frame. This subframe employs the structural principals pioneered in highly survivabile aircraft including the B-17 and A-10 as well as efficiencies pioneered in the F-16, B-1, F/A-22 and F/A-35. The alloy subframe is a laser welded and built-up structure which serves as a rigid chassis for the integration of all alloy frames, primary bulkheads, mounts and the firewall. All fuselage contained systems, including avionics, electrical, armament hydraulic and the CAM, are secured to subframe integrated alloy mounts. The subframe is skinned in an alloy film to ensure all TEMPEST sensitive avionic and electrical systems are contained within a Faraday cage.

The fuselage core is skinned with a unitized sandwich structure consisting of a Hexcel IM9 graphite/polyimide external skin and and finely woven Kevlar® (KRP) and Spectra® (SRP) internal skin, separated by a proprietary thin core optimized for improved ballistic projectile threat protection.

The Super Machete fuselage features the Cockpit Armor Module (CAM) for integrated cockpit protection. The Super Machete fuselage features an integrated armored ammunition cell and rigid internal fuel tanks. The fuselage incorporates discrete armor throughout. The fuselage features a starboard located downward hinged door with integral steps for crew ingress/egress.

The radome is composed of bandpass
Spectra® (SRP) and hinges to the port for radar/avionics access. The engine cowling is of three-part clamshell type and is composed of a Kevlar® (KRP) composite sandwich.


Of supersonic design, the SM-47 Forward Swept Wings have a leading edge sweep of -30º. With a 4% to 6% thick supersonic airfoil, SM-47 wings benefit from computer selected variable camber, including wing slats and trailing edge flaperons. Wing span is 36 ft 0 in. Reference wing area is 280 sq ft. Wing aspect ratio is 4.63. Of thin section, the SM-47 wing is of multi-spar construction with titanium ribs and spars. To provide the stiffness necessary to counter aeroelastic effects, the SM-47 wing is skinned in hi-tensile strength IM-9 carbonfiber suspended in a matrix of high temperature Polyimide resin to permit sustained supersonic flight. SM-47 wings feature four underwing hardpoints for external stores and provisions for optional wing-tip launch rails for the carriage of AAMs including the AIM-9 and AIM-120.

The Super Machete wing is a modular, three-piece, fail-safe structure consisting of an integrated center section. The center section consists of four sine wave Ti-6222 spars which form the basis of a rigid, laser welded, Titanium carry-through box. This carry-through box serves as mount and armored housing for the main landing gear. The carry-through box is also the principal mount and interface for port and starboard Titanium monocoque empennage support booms which serve as the structural interface for the vertical and horizontal stabilizers. The center section has Titanium ribs, stringers and skins. All alloy components are fastened via laser welding, friction stir welding and rivets.

The port and starboard forward swept wing sections feature four Titanium sine-wave spars, four IM9/Polyimide sine-wave spars and one Titanium false spar for aileron/ flap attachment. Each wing section incorporates five Titanium ribs and twelve Titanium stringers. Wing sections benefit from aerolastically tailored IM-9/Polyimide skins that are fastened directly to wing spars, with all alloy components fastened by computer directed laser welding. Each wing contains rigid self-sealing fuel tanks.

Each wing section is equipped with 0.25c, 52% span variable camber flaperons for roll control and lift augmentation. Each wing section is also equipped with leading edge slat and spoilers. Trailing and leading edge flaperons/slats are Power-By-Wire actuated. Flapperons, slats, spoilers and speed-brakes are of GRP construction. Each wing tip is equipped with a LAU-128/A missile launch rail for carriage of AIM-9 and AIM-120 misssiles.

Wings are equipped with an Electro-Expulsive Separation System (EESS) for in-flight deicing. Wings are equipped with a total of eight external stores hardpoints, including four wing, two wing-tip and two canted hardpoints located on the wing center section tips fitted directly to the empennage support boom. Four hardpoints are rated to 2,500 lbs capacity at +7.5g, two hard points are rated to 1,000 lbs at +7.5g and the two tip wing hardpoints are rated to 500 lbs capacity at +7.5g. Four hardpoints per wing are plumbed for external fuel carriage. Standard external tanks include 100 through 230 USG types.


The aircraft canard foreplanes are all-moving, close-coupled cantilever type. The canards are of full deflection type and are used in conjunction with the horizontal stabilizer and optional thrust vectoring to enable Post Stall Maneuvering (PSM). Canards enhance aircraft low speed handling, maneuvering and short field performance through the generation of high energy vortices. The canards are of control type, yet add to aircraft gross wing area in some attitudes with aircraft pitch stability being maintained using the empennage. Leading edge canard sweep is 50°. Canard unit span is 4 ft 6 in. Total canard area and aspect ratio is 31.50 sq ft and 2.57 respectively. Canard mean airfoil is a 4% thick supersonic section.

Canard construction consists of four Ti-6222 spars, five Titanium ribs and IM9/Polimide skins. Canards benefit from laser formed components which are laser welded to form a smooth, high tolerance finish. Canards are of trunnion mounted, all moving type which operate collectively with the all moving horizontal stabilizer to enhance pitch rate.


The Super Machete empennage consists of an all-moving, mass balanced horizontal stabilizer for longitudinal stability and pitch control and twin vertical stabilizers. The empennage is close-coupled to the aircraft wing to improve instantaneous maneuverability and reduce aircraft physical dimensions. The empennage is mated to Super Machete via the wing mounted integrated empennage support boom structure and aerodynamically contoured fuselage braces which blend directly into the horizontal stabilizer. Both the horizontal and vertical stabilizers are equipped with EESS deicing.

The Super Machete horizontal stabilizer is of trapezoidal planform with a leading edge sweep of 30°. Horizontal tail unit span is 9 ft 7 in. Total horizontal tail area and aspect ratio is 86.07 sq ft and 1.59 respectively. Horizontal tail mean airfoil is a modified NACA 65A004.5 section. The horizontal stabilizer is composed of three Ti-6A1-4V Titanium sine-wave spars and five IM9/Polyimide ribs. Horizontal stabilizer skins are IM9/Polyimide. Maximum horizontal stabilizer deflection angle is +/- 40°.

The Super Machete vertical stabilizer consists of two independent units of trapezoidal configuration with dorsal fairings. Vertical stabilizer leading edge sweep is 40°. Vertical stabilizer span is 6 ft 6 in. Total vertical tail area and aspect ratio is 58.32 sq ft and 2.88 respectively. Vertical stabilizer mean airfoil is a modified NACA 65A006 section with dihedral of 90°.

The vertical stabilizer is composed of three Ti-6A1-4V Titanium sine-wave spars, five IM9/polyimide false spars, six titanium ribs and flush riveted IM9/polyimide skins. Each vertical stabilizer features a IM9/polyimide rudder. Rudders incorporate trim tabs and are capable of deflection angles of +/- 35°. Each vertical tail incorporates a SRP tip antenna fairing for vertical tail mounted antennas, EW and RWR.


The aircraft fuel system is of OBIGGS pressurized type, composed of nine rigid self-sealing fuel tanks and one feeder tank. The OBIGGS employed is the Carlton NC1029.

Four of the fuel tanks are located within the fuselage, while the remaining two tanks are located within the wings. The maximum useful internal fuel load for the SM-47 is 7,250 lbs, equivalent to approximately 1,082 gallons of JP-8 (at 6.7 lbs/gal) or 1,115 gallons of JP-4 (at 6.5 lbs/gal). SM-47 fuel tanks are sized for 1,115 usable gallons of JP-4, resulting in a total capacity of 1,125 gallons. Unusable internal fuel is 65 lbs.

A single point refueling interface is located on the starboard fuselage, while gravity refueling may be accomplished through three filler locations including one on each wing and a single fuselage point. A probe-and drogue in-flight refueling system may be installed within the fuselage nose section of SM-47Ts which do not feature a 20mm cannon. The refueling probe for the in-flight refueling system is of retractable type based upon technologies developed by Sargent Fletcher in their ART/S Aerial Refueling Tank System and will likely be produced by Sargent Fletcher.

A USAF flying boom compatable Universal Aerial Refueling Receptacle Slipaway Installation (UARRSI) is mounted on the dorsal fuselage immediately aft of the cockpit to enable in-flight refueling from USAF KC-135, KC-10 and KC-X tanker aircraft. The UARRSI is standard aircraft equipment.


Super Machete Airframe Systems include flight controls, hydraulics and electrical units. Benefiting from Relaxed Static Stability, the SM-47 flight control system is a full-authority, Digital Fly-By-Wire (FBW) flight control system permitting carefree handling and optimal combat performance. Ailerons, flaperons, rudders and stabilators are internally mass balanced. Ailerons and rudders feature electric trim tabs controllable through a control column rheostat. Stabilators feature electric trim, actuators for which are located in the support boom.

The Super Machete features two, independent, 4,000 psi hydraulic systems. Hydraulic functions include landing gear extension and retraction, trailing and leading edge flap extension and retraction, canopy extension and retraction, crew boarding ladder retraction, clamshell cowling actuation and ventral airbrake actuation.

Hydraulic pressure is maintained automatically. The hydraulic power package supplies hydraulic pressure and incorporates an electrically-powered variable displacement motor/pump, a reservoir and low pressure filter. A nitrogen-charged accumulator is used to minimize pressure loss while allowing for thermal expansion. The aircraft hydraulic system employs Spectra® filament wrapped titanium lines and non-flammable hydraulic fluid for survivability.

The SM-47 electrical system supplies 115 volt, three-phase, 400 cycle AC power and 28 VDC per MIL-STD-704D. Four independent sources are used for power generation including a Honeywell 36 series APU for engine starting and ground pneumatic, electric and hydraulic power, engine driven inverters, a secondary generator and two batteries. AC power is supplied by two engine driven static invertors rated at 125 volt amps, providing outputs of 26 VAC at 400 Hz and 115 VAC at 400 Hz. Power is normally supplied by one invertor with the second serving as a backup. DC power is supplied through one 24 VDC, 40 amp-hour, nickel-cadmium battery. The secondary generator is a 28 VDC, 130 amp generator. An external 28 VDC power connector is provided within the engine bay.


The Super Machete features hydraulically actuated, retractable tricycle landing gear. The main landing gear consists of wing mounted, single-strut, oelo-pneumatic, single wheel units featuring carbon disk brakes. Main wheels use 24 x 8.0-13 size tires including Goodyear Flight Eagle, 18 ply rib tread with a maximum inflation pressure of 285 psi. The main gear retracts 90° outward, with wheels stowed in the wing center section carry-through box upon retraction.

Nose landing gear retracts forward and is an oelo-pneumatic, fork-braced single wheeled unit. The nose wheel uses 19 x 6.75-8 size tires including 10 TL ply, Goodyear Rib tread with a maximum inflation pressure of 110 psi. Nose wheel steering, and main gear braking, is provided via rudder pedal inputs. Nose gear may be gravity extended in the event of hydraulic failure.

The landing gear is capable of unprepared, forward operations and sink rates of 15 ft/s enabling a high tolerance to hard landings. Maximum landing gear deployment airspeed is 250 Kts. Super Machete wheelbase is 16 ft 0 in. Super Machete wheel track is 10 ft 9 in. Landing lights are incorporated into the main gear struts and steerable taxi lights are mounted to the nose gear strut.


Substantial emphasis has been placed upon ensuring SM-47 survivability in the low-level, hostile environment. In so doing, significant quantities of both integral and discrete armor are incorporated throughout the airframe.

Integral Armor consists of primary aircraft structural elements that not only serve as load-bearing members, but also provide an element of armor protection by inherent design. Featuring fail-safe construction throughout, Super Machete wings and canards feature Titanium sine-wave spars and numerous titanium sine-wave ribs. These spars and ribs in-turn assist in shielding discrete, OBIGGS pressurized wing fuel tanks. Super Machete horizontal and vertical stabilizers feature sine-wave spars and multiple sine-wave ribs. This use of Titanium spars and ribs significantly improves aircraft survivability. Employing significant quantities of Titanium mated to
Spectra® ballistic material, the Super Machete fuselage is of inherently survivable and crash-worthy design.

Super Machete fuel is contained within discrete tanks located in the wings and fuselage. Each rigid tank consists of a Titanium fuel cell that provides both structural form and function as well as a degree of armor protection. Each cell is pressurized with an OBIGGS for explosion suppression. Whenever possible, fuel lines are contained within fuel tanks. All fuel lines, hydraulic lines and flight control lines are contained within Titanium or Spectra® filament jackets to ensure survivability. The aircraft flight control, electrical and hydraulic systems are duplicated and physically separated by more than 24 in to ensure redundancy.

Presenting a compact, close coupled arrangement, the Super
Machete configuration is directed toward survivability. The empennage, for instance, is configured such that the GRP skinned vertical stabilizers provide the aircraft propulsion system with a degree of profile shielding.

Learning from the A-10, the Super Machete empennage is slightly oversized to ensure continued control in the event of significant loss of stabilizer area during combat. Additional reductions in overall aircraft vulnerable area are derived from the use of a low-wing situated directly beneath the aircraft fuselage fuel tanks, ammo drum and to a degree, propulsion system, as shielding. The use of vertically sloped forward fuselage cross sections further improves survivability by ensuring that the majority of incoming ballistic projectiles will be received as deflection impacts met by Spectra® ballistic material.

Super Machete Discrete Armor consists of materials which function wholly as armor, serving no secondary structural purpose. The SM-47 employs no less than 500 lbs of Discrete Armor, strategically placed within critical vulnerable areas including around/about the aircraft powerplant (engine cowling case armor), electrical generation, environmental, hydraulic and control systems, as well as around the internal ammunition drum. To ensure crew survivability, the Super Machete cockpit is an integral unit contained within a unitized Cockpit Armor Module (CAM). The CAM is a laser welded, armored structure, conceptually identical to the A-10 crew protection structure. The Discrete Armor used throughout the Super Machete, including the CAM, is a Stavatti proprietary laminate of alloy and composite materials including a Molecularly Pure Alloy face sheet backed by multiple layers of Spectra® 2000/Spectra®Shield. Thickness of the Discrete Armor laminate varies based upon specific application, ranging from 0.25 in to more than 1.25 in.

Composed of advanced bullet-resistant polycarbonate, the SM-47 transparent bubble canopy is no less than 1.00 in thick throughout and provides impact protection against a 4 lb bird up to airspeeds in excess of 570 kts. Ensuring crew protection through small caliber small arms, the canopy benefits from technologies developed at USAF Rome Labs and Wright Research Labs-WPAFB.

Ensuring crew survivability, the SM-47 is equipped with the highly reliable and proven Martin Baker MK.16E zero-zero ejection seat. The ejection seat is provided with both sequential and auto-eject features. Incorporating a comprehensive internal electronic countermeasures suite, proven Radar Warning Receivers, Laser Warning Receivers, Missile Approach Warning Systems and Self Protection Jammers produced by Elisra, Elta and/or Raytheon are carried as customer selected, standard equipment.

The BAE Systems AN/ALE-47 electronic countermeasures system with ten (10) to twelve (12) aircraft integrated dispensers (ten empennage boom or fuselage) is standard equipment for the Super Machete.