Rocket or ballistic launch rotary wing vehicle

• US 10,279,898 B2
• Filed: 05/23/2012
• Issued: 05/07/2019
• Est. Priority Date: 05/23/2011
• Status: Active Grant

• Current Assignee: Blue Bear Systems Research Limited (Cassima Ltd.)
• Original Assignee: Blue Bear Systems Research Limited (Cassima Ltd.)
• Inventors: Green, John, Geoghegan, Philip, Snook, Michael Alexander
• Primary Examiner(s): Dinh, Tien Q
• Assistant Examiner(s): Fabula, Michael A.
• Application Number:
  US14/122,045
• Publication Number:
  US 20140299708A1
• Time in Patent Office: 2,540 Days
• Field of Search: 244 1711, 244 1723, 244 1725
• CPC Class Codes: B64C 27/00 Rotorcraft; Rotors peculiar thereto
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 27/50 Blades foldable to facilitate stowage of aircraft
• CPC Class Codes: B64C 27/58 Transmitting means, e.g. interrelated with initiating means or means acting on blades means acting on blades B64C27/72
• CPC Class Codes: B64C 27/59 mechanical
• CPC Class Codes: B64C 27/605 including swash plate, spider or cam mechanisms
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 27/02 Aircraft characterised by the type or position of power plants fuselages specially adapted for mounting power plants B64C1/16; wings specially adapted for power plants B64C3/32
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64F 1/04 for launching aircraft
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/17 Helicopters flying platforms B64U10/13
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/16 movable along the UAV body
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/21 Rotary wings
• CPC Class Codes: B64U 30/29 Constructional aspects of rotors or rotor supports; Arrangements thereof
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/32 : generated by fuel cells
• CPC Class Codes: B64U 70/80 : Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

A rocket or ballistic launch rotary wing air vehicle may include a rocket or ballistic launch propulsion system for launching the vehicle, a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors, and a control system programmed to adjust the pitch of a rotor to anyh determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from a stowed position to a deployed position.

Claims

1. A rocket or ballistic launch rotary wing vehicle, the vehicle comprising:

a rocket or ballistic launch propulsion system for launching the vehicle,

a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors;

the rotary wing flight system comprising a pitch mechanism for controlling the pitch of a rotor of the dual counter rotating coaxial rotors, the pitch mechanism comprising a flap hinge having a flap hinge axis of rotation, and a pitch control arm having a pitch control arm axis of rotation;

the pitch control arm being, relative to a rotor axis of rotation, radially outwardly disposed of the flap hinge axis of rotation, the flap hinge being actuatable, via the flap hinge axis of rotation, over a range comprising a stowed position, in which the dual counter rotating coaxial rotors are folded, to a deployed position via a transition phase and wherein at least one of a cyclic and collective is variable during the transition phase; and

a control system programmed to adjust the pitch of the rotor to any determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from the stowed position to the deployed position.

2. The vehicle of claim 1, wherein the rotary wing flight system comprises a plurality of rotary wings for deployment following a rocket or ballistic phase of flight.

3. The vehicle of claim 1, wherein at least one of the cyclic and collective is variable to influence vehicle attitude.

4. The vehicle of claim 1, wherein the launch propulsion system comprises at least one of a ballistic system for launching the vehicle as a projectile and a rocket motor for launching the vehicle as a rocket.

5. The vehicle of claim 1, wherein the dual counter rotating coaxial rotors are in the stowed position having a predetermined pitch angle.

6. The vehicle of claim 5, wherein the predetermined pitch angle is at least one of (a) between 5°

and 15° and

(b) 8°

.

7. The vehicle of claim 1, wherein the pitch mechanism for controlling the pitch of the rotor comprises a rotor head, for rotation about a rotor axis of rotation, comprising the flap hinge to pivot about a flap hinge axis of rotation within a respective flap hinge plane of rotation and the pitch control arm mounted radially outwardly of the flap hinge;

the pitch control arm being to rotate about the pitch control axis of rotation within a pitch control arm axis plane of rotation; and

wherein the pitch control arm plane of rotation is substantially orthogonal to the flap hinge plane of rotation.

8. The vehicle of claim 1, wherein the dual counter rotating coaxial rotors comprise at least a first pair of rotors and the vehicle comprises head end and a tail end.

9. The vehicle of claim 8, wherein at least the first pair of rotors is disposed at the head end.

10. The vehicle of claim 9, wherein the rotary wing flight system for providing powered flight comprises at least a second pair of rotors disposed at the head end of the vehicle.

11. The vehicle of claim 8, wherein the dual counter rotating coaxial rotors comprise at least a second pair of rotors disposed at the tail end.

12. The vehicle of claim 8, wherein the dual counter rotating coaxial rotors comprise at least a second pair of rotors.

13. The vehicle of claim 1, wherein the vehicle comprises a central portion and the dual counter rotating coaxial rotors comprise one or more of a first pair of rotors disposed at the central portion and a second pair of rotors disposed at the central portion.

14. The vehicle of claim 1, wherein said at least one of the pitch, cyclic and collective is variable to transition the vehicle from a first angle of attack to a second angle of attack.

15. The vehicle of claim 14, wherein the first angle of attack is lower than the second angle of attack.