The Hamilton AeroSpace HX-322, is a two place tandem airplane. This airplane combines state of the art composite technology, high maintainability, and outstanding performance figures.

The Hamilton HX-322 was designed with the following major objectives:

  All composite airframe. Graphite, and glass with epoxy and aerospace foam
  Structural integrity, enabling rugged and austere operations
  Twin jet engine configuration.
  Design versatility to accept a number of engines.
  Excellent speed and maneuvering performance, while retaining business desirable range

The composite airframe is a basic tenet of Hamilton AeroSpace. This technology has several distinct advantages over the dated aluminum rigs, skin, and rivets approach including:

  Heretofore unachievable strength and rigidity in a lightweight structure
  Simple, low cost tooling, enabling low manufacturing costs, yet the ability to produce large, complex
     surfaces and near exact repeatability
  Simple repair procedures
  Freedom from airframe, salt water corrosion
  Very smooth surface for low parasite drag and laminar flow

The performance of this airplane, with twin jet configuration, is outstanding, and will prove a superb, fast executive airplane for a variety of general aviation uses.

The tandem seating arrangement, with front cockpit solo capability, was dictated by the performance goals. The nose section has ample space for avionics equipment, including weather radar if desired. Instrument panel and side consoles have adequate room for a normal complement of instruments, avionics, and controls. Conventional mechanical controls, with center mounted stick in both cockpits, will be used. The bubble type canopy will provide 300 degree visibility. Additional equipment/baggage space is available immediately aft of the rear cockpit bulkhead. Control linkage and electrical wiring pass through sealed access ports to provide for cabin pressurization if desired.

Maintainability of this sophisticated, but simple, airframe was enhanced by the desire to maintain structural unit integrity of the molded composite airframe. All controls, coaxial cable runs, and hard wiring, pass from the cockpit aft through wing root/empennage continuous fairings on either side of the fuselage external to the principal structural unit. The large main fuel cell will be the only item contained internal to the primary structure. Waist high access panels will allow easy inspection or maintenance on all engine/flight utility systems controls, connections, and wiring. All engine and engine accessory parts are outside of the primary fuselage structure. Total engine access is enabled by simple removal of the top and bottom cowl units. Avionics are totally contained in the nose section of the airplane, shelf mounted and accessible through quick opening access panels. Design data are tabulated as attached preliminary.