Unmanned remotely piloted aircraft

• US 4,478,379 A
• Filed: 10/27/1983
• Issued: 10/23/1984
• Est. Priority Date: 05/28/1981
• Status: Expired due to Term

• Current Assignee: 125769 Canada Incorporated
• Original Assignee: Canadair, Inc. (Bombardier Incorporated)
• Inventors: Kerr, John P.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US06/545,609
• Time in Patent Office: 362 Days
• Field of Search: 244/17.11, 244/17.17, 244/17.23, 244/115, 244/116, 244/120, 244/138 A, 416/114, 416/115, 416/248, 416/204 R, 416/205
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/10 for stealth, e.g. reduction of cross-section detectable by radars
• CPC Class Codes: B64U 20/40 Modular UAVs
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 2201/202 using tethers for connecting to ground station
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/21 Rotary wings
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 60/50 with landing legs
• CPC Class Codes: B64U 70/00 Launching, take-off or landing arrangements

Abstract

An unmanned aircraft of the remotely piloted type that is characterized by its configuration and outline using rigid counter rotating propellers, positioned substantially at the height of its center of mass or slightly below to allow producing a sufficiently large control moment to use a tether line for landing the aircraft and to allow using two substantially spheroidal surfaces at the top and bottom respectively rather than a single one relatively larger and more detectable surface as when the propellers are at the top.

Claims

1. An unmanned, remotely piloted aircraft comprising:

a main body symmetrical about a vertical axis comprising three separable, vertically stacked body sections;

the uppermost one of said body sections including means to enclose and support a propulsive engine;

a propulsive engine contained within and supported by said uppermost body section;

a fuel tank in said uppermost body section arranged to laterally surround at least a major portion of said engine;

the intermediate one of said body sections including means to support a gear box connectable with said engine, a pair of vertically arranged counterrotating propeller hubs and propeller blades secured thereto, and pitch control means for the propeller blades;

a centrally located gear box enclosed within said intermediate one of said body sections and supported by said means to enclose and support said gear box;

a pair of vertically spaced counterrotating propeller hubs connected together for being jointly driven by said engine through said gear box enclosed within and supported by the intermediate body section;

variable pitch propeller blades secured to said hub through a rigid connection arranged to permit the pitch of the propellers to be changed;

pitch control means enclosed by and supported by said intermediate body section connected to the propeller blades and arranged to control the pitch of all the propeller blades simultaneously in a collective and/or differential sense;

the lowermost one of said body sections including means for containing and supporting a payload of known mass;

a payload of known mass contained within and supported by said lowermost body section;

said propeller hubs located substantially in the horizontal plane including the center of mass of the aircraft with said payload.

2. An aircraft according to claim 1, wherein said uppermost and lowermost body sections are connected to the intermediate body section by quick disconnect means, and the connection between the uppermost and intermediate sections is through said gearbox.

3. The aircraft according to claim 1 or 2, said engine including an exhaust conduit, said exhaust conduit disposed substantially centrally along the vertical axis of the aircraft and arranged to discharge exhaust gases generally vertically parallel to said axis.

4. An aircraft according to claim 3, including a landing gear secured to the lowermost body section.

5. An aircraft according to claim 3, including a spool for a coil of tether line, the spool releasably secured to the aircraft, with one end of the tether line secured to the body and the other end connected to the spool.

6. The aircraft according to claim 5, said tether line connected to the body by a rotatable ring rotatable about the body vertical axis.