Unmanned multimode helicopter

• US 4,163,535 A
• Filed: 12/13/1972
• Issued: 08/07/1979
• Est. Priority Date: 12/13/1971
• Status: Expired due to Term

• Current Assignee: Westland Aircraft Limited
• Original Assignee: Westland Aircraft Limited
• Inventors: Austin, Reginald G.
• Primary Examiner(s): Pendegrass, Verlin R.
• Application Number:
  US05/314,494
• Time in Patent Office: 2,428 Days
• Field of Search: 244/17.11, 244/17.13, 244/17.15, 244/17.17, 244/17.19, 244/17.23, 244/17.25
• US Class Current: 244/17.23
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/24 Coaxial rotors

Abstract

An unmanned helicopter capable of controlled free flight comprises a plurality of separable modules arranged in a substantially vertically stacked assembly symmetrical about a vertical axis. The modules include an uppermost propulsion module, a central fuel tank module and a lowermost control and payload module.

Claims

1. A helicopter comprising in combination,

a plurality of separable modules arranged in a substantially vertically stacked assembly,

the modules including an uppermost propulsion module, a central fuel tank module and a lowermost control and payload module, a collar supporting the propulsion module, attachment means on said collar and suspending the fuel tank module,

a tripod undercarriage means attached to and equispaced around the collar, said tripod means comprising three legs extending downwardly and outwardly, whereby during operation, all flight and landing loads are transferred to said collar.

2. A helicopter as claimed in claim 1, wherein each undercarriage leg is constructed of glass reinforced plastics material in a tubular configuration of constant wall thickness and tapering towards each end.

3. A helicopter as claimed in claim 1, wherein the propulsion module comprises a co-axial contra-rotating rotor system and an engine and gearbox for driving said rotor system, the engine being suspended from the collar, the propulsion module further including control means for effecting cyclic, collective and differential collective pitch changes of the rotor system.

4. A helicopter as claimed in claim 1, wherein the fuel tank module comprises a casing of generally truncated cone shape having an annular fuel tank arranged to surround the engine when the module is suspended from the collar, and having attachment means from which the control and payload module is suspended.

5. A helicopter as claimed in claim 3, wherein the control and payload module comprises an upper control sub-module and lower payload sub-module, the upper control sub-module containing electronic control units for operating said control means of the propulsion module and an externally mounted antenna for transmitting control signals from a ground station.

6. A helicopter as claimed in claim 5, wherein gimbal mounted television and still cameras are disposed in the lower payload sub-module and said cameras operative through a window section and control means in the upper control sub-module for controlling said cameras and means for rotating the payload sub-module about a generally vertical axis.

7. An unmanned free-flying helicopter comprising in combination,

a plurality of separable modules arranged in a substantially vertically stacked assembly,

the modules including an uppermost propulsion module, a central fuel tank module and a lowermost control and payload module, a collar arranged to support the propulsion module and attachment means on said collar for suspending the fuel tank module,

the propulsion module comprising a co-axial contra-rotating rotor system, an engine and gearbox for driving said rotor system, the engine being suspended from the collar, the propulsion module further including control means for effecting cyclic, collective and differential collective pitch changes of the rotor system,

the fuel tank module comprising a casing of generally truncated cone shape having an annular fuel tank arranged to surround the engine when the module is suspended from the collar, and having attachment means from which the control and payload module is suspended,

the control and payload module comprising an upper control sub-module and a lower payload sub-module, the control sub-module containing electronic control units for operating said control means of the propulsion module and an externally mounted antenna for transmitting control signals from a ground station, the payload sub-module containing television and still cameras operative through a window section and control means in the upper control sub-module for controlling said cameras,

a tripod undercarriage means attached to and equi-spaced around the collar, said tripod means comprising three legs extending downwardly and outwardly, whereby during operation, all flight and landing loads are transferred to the collar.