Rocket or ballistic launch rotary wing vehicle

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.