초록 ▼

A miniature, unmanned aircraft having interchangeable data handling modules, such as sensors for obtaining digital aerial imagery and other data, and radio transmitters and receivers for relaying data. The aircraft has a microprocessor for managing flight, remote control guidance system, and electri

A miniature, unmanned aircraft having interchangeable data handling modules, such as sensors for obtaining digital aerial imagery and other data, and radio transmitters and receivers for relaying data. The aircraft has a microprocessor for managing flight, remote control guidance system, and electrical supply system. The data handling modules have an aerodynamic housing and manual fasteners enabling ready installation and removal. One or more data acquiring sensors or data transferring apparatus and support equipment such as batteries and communications and power cables are contained within the module. A plurality of different modules are preferably provided. Each module, when attached in a preferred location below the wing, does not significantly alter the center of gravity of the airframe. Preferably, each module contains the supervisory microprocessor so that the microprocessor need not be part of the airframe.

대표청구항 ▼

1. A powered, miniature, unmanned aircraft, comprising:a) an elongated airframe including a reciprocating piston internal combustion engine, a fuselage having an upper surface and a lower surface comprising a stepped, cutaway region along a longitudinal portion thereof, said stepped, cutaway region

1. A powered, miniature, unmanned aircraft, comprising:a) an elongated airframe including a reciprocating piston internal combustion engine, a fuselage having an upper surface and a lower surface comprising a stepped, cutaway region along a longitudinal portion thereof, said stepped, cutaway region of said lower surface being adapted to receive an interchangeable data module; b) a unitary, fixed wing removably attachable to said upper surface of said fuselage at a substantially right angle thereto; c) a data module removably attachable to said fuselage at said stepped, cutaway region, a front end of said data module substantially abutting said fuselage at said step, a lower surface of said data module thereby forming an aerodynamically contiguous extension of a portion of said lower surface of said fuselage located forward of said step when said data module is attached to said fuselage; d) at least one control surface disposed on at least one of said wing and said fuselage, each of said at least one control surface comprising a servomechanism operably connected thereto; e) a remotely controlled guidance system having a radio frequency receiver carried aboard said airframe and operatively connected to at least said at least one control surface by means of said associated servomechanism associated therewith; said powered, miniature, unmanned aircraft weighing no more than fifty-five pounds with said data module attached thereto. 2. The powered, miniature, unmanned aircraft as recited in claim 1, further comprising a microprocessor disposed to manage flight thereof, wherein said radio frequency receiver is communicably connected to said microprocessor, and said microprocessor is in turn disposed to transmit control signals to said servomechanism operably connected to said at least one control surface.3. The powered, miniature, unmanned aircraft as recited in claim 2, wherein said airframe comprises a first opening at said stepped cutaway region of said fuselage, said data module comprises a second opening disposed in registry with said first opening when said data module is attached to said airframe, whereby at least one electrically conductive cable can pass from an interior region of said data module through said first and said second openings and into said airframe.4. The powered, miniature, unmanned aircraft as recited in claim 3, wherein said data module is removably attached to said fuselage such that said data module and said fuselage make surface contact with one another in a manner which seals said first and said second openings, thereby isolating said interior regions of said airframe and said data module from open communication with outside atmosphere.5. The powered, miniature, unmanned aircraft as recited in claim 2, wherein said microprocessor is disposed in said data module.6. The powered, miniature, unmanned aircraft as recited in claim 1, further comprising at least one manual fastener disposed and adapted for securing said data module to said fuselage.7. The powered, miniature, unmanned aircraft as recited in claim 1, further comprising means for locating disposed on at least one of said fuselage, and said data module, said means for locating facilitating locating said data module for attachment to said fuselage.8. The powered, miniature, unmanned aircraft as recited in claim 7, wherein said means for locating comprises at least one projecting pin disposed at least one of the locations: said step of said fuselage, and a forward-facing surface of said data module.9. The powered, miniature, unmanned aircraft as recited in claim 1, further comprising at least one electrical connector having a first portion, and a second portion adapted for removable electrical interconnection therewith, one of said first and said second portions being disposed on said fuselage and a corresponding other portion of said connector being disposed on said data module such that electrical interconnection of said first and said second portion results when said data module is attached to said fuselage.10. The powered, miniature, unmanned aircraft as recited in claim 9, wherein said data module comprises at least one electrically operated device, and wherein said at least one electrically operated device is operatively connected to said fuselage by said at least one connector.11. The powered, miniature, unmanned aircraft as recited in claim 9, wherein said fuselage has a first center of gravity measured without said data module attached thereto, and a second center of gravity measured with said data module attached thereto, and wherein said first and said second centers of gravity are located less than 5% of a length of said fuselage from one another.