Tailboom-stabilized VTOL aircraft

• US 7,070,145 B2
• Filed: 01/24/2005
• Issued: 07/04/2006
• Est. Priority Date: 10/24/2003
• Status: Expired due to Fees

• Current Assignee: Baldwin G. Douglas
• Original Assignee: Baldwin G. Douglas
• Inventors: Baldwin, G. Douglas
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US11/042,666
• Publication Number:
  US 20060032971A1
• Time in Patent Office: 526 Days
• Field of Search: 244/7.R, 244/4.R, 244/137.4, 244/137.1, 244/7.B, 244/7.C, 244/17.23
• US Class Current: 244/7.00R
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/24 Coaxial rotors
• 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

Abstract

A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure'"'"'s second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

Claims

1. A method comprising:

(a) providing a lift unit including a propulsion subsystem and a tailboom;

(b) providing a payload unit pivotally coupled to the lift unit such that the tailboom and payload unit are free to independently pivot with respect to each other about a first axis;

(c) operating the lift unit in a first mode wherein its propulsion subsystem provides an aerial motive force predominantly countering gravity;

(d) during at least a portion of the first mode, latching the tailboom to the payload unit in a substantially vertical orientation;

(e) transitioning the lift unit to a second mode wherein its propulsion subsystem provides an aerial motive force predominantly parallel to the ground; and

(f) during at least a portion of the second mode, releasing the tailboom from the payload unit, thereby allowing it to pivot independently of the payload unit.

2. The method of claim 1 wherein providing the lift unit comprises providing a rotor as the propulsion subsystem.

3. The method of claim 2 wherein:

(a) providing the lift unit comprises providing a pair of blade sets as the rotor; and

(b) operating the lift unit comprises rotating the blades of one set in an opposite direction to blades of the other set.

4. The method of claim 2 further comprising, before operating the lift unit in the first mode, resting the lift unit on a support surface alongside the payload unit.

5. The method of claim 4 wherein:

(a) the lift unit is pivotally coupled to the payload unit through a rigid suspension structure; and

(b) the method further comprises, at the beginning of the first mode, moving the lift unit away from the support surface and about the payload unit in an arc until it begins to suspend the payload unit.

6. The method of claim 5 further comprising:

(a) providing a pair of wing panels pivotally coupled to the tailboom; and

(b) before moving the lift unit, unfolding the wing panels from (1) a stowed position substantially parallel to the tailboom to (2) a deployed position extending substantially orthogonal from the tailboom.

7. The method of claim 2 wherein suspending the payload further comprises constraining the payload from pivotal movement about all axes orthogonal to a first axis.

8. The method of claim 2 further comprising, before operating the lift unit, resting the payload unit on a surface with the tailboom latched thereto, wherein the lift unit is at least partially supported by the tailboom.

9. The method of claim 2 wherein releasing the tailboom includes permitting rotation of the tailboom, within an angular range, about a rotational axis orthogonal to an axis passing between the lift unit and the payload unit.

10. The method of claim 9 further comprising, after releasing the tailboom, pivotally driving the tailboom with respect to the lift unit.

11. The method of claim 9 further comprising, after releasing the tailboom, controlling pitch of the tailboom with a horizontal stabilizer and an elevator.

12. The method of claim 9 further comprising, after releasing the tailboom, controlling yaw of the tailboom with a vertical stabilizer and a rudder.

13. The method of claim 2 wherein providing the lift unit further comprises providing a pair of wing panels pivotally coupled to the tailboom, the method further comprising:

(a) while the tailboom is latched to the payload unit, having the wing panels oriented substantially parallel to the tailboom; and

(b) while the the tailboom is released from the payload unit, having the wing panels extending substantially orthogonal from the tailboom.

14. The method of claim 2 further comprising:

(a) permitting the lift unit to freely rotate, within at least a predetermined angular range, about a rotational axis orthogonal to an axis passing through the first and second ends of the suspension structure; and

(b) substantially constraining the lift unit from movement relative to the first end of the suspension structure in a direction parallel to the rotational axis.

15. A method comprising:

(a) in a flying craft having a tailboom and a payload support structure free to pivot with respect to each other about a first axis, generating an aerial motive force predominantly countering gravity;

(b) during at least a portion of part (a), having the tailboom latched to the payload support structure, thereby arranging the tailboom in a substantially vertical orientation;

(c) in the flying craft, generating an aerial motive force predominantly parallel to the ground; and

(d) during a transition between parts (a) and (c), releasing the tailboom from the payload support structure, thereby allowing the tailboom and the payload support structure to pivot independently of each other about the first axis.

16. The method of claim 15 wherein, when not latched to the payload support structure, the tailboom is free to pivot about the first axis and only the first axis.

17. The method of claim 15 wherein generating the aerial motive force comprises operating at least one rotor of a lift unit to which the tailboom and the payload support structure are both attached.

18. The method of claim 15 wherein releasing the tailboom includes permitting the tailboom to rotate about the first axis, but only within a predetermined angular range.

19. A method comprising, in a flying craft having (1) a tailboom and a payload unit free to pivot with respect to each other about a first axis and (2) a plurality of airfoil blades held by a central hub and moveable between a stowed position and a deployed position:

(a) spreading the blades to form a pair of rotors coaxial with each other and a second axis perpendicular to the first axis;

(b) orienting the hub in a substantially vertical direction and rotating the rotors in opposite directions about the second axis, thereby generating an aerial motive force predominantly countering gravity;

(c) during at least a portion of part (b), keeping the tailboom latched to the payload unit, thereby arranging the tailboom in a substantially vertical orientation;

(d) transitioning the hub to being oriented in a direction predominantly parallel to the ground while continuing to rotate the rotors in opposite directions; and

(e) during part (d), releasing the tailboom from the payload unit, thereby allowing the tailboom and the payload unit to pivot independently of each other about the first axis.

20. The method of claim 19 wherein:

(a) when not latched to the payload unit, the tailboom is free to pivot about the first axis and only the first axis; and

(b) releasing the tailboom includes permitting the tailboom to rotate about the first axis, but only within a predetermined angular range.