REDUNDANCIES AND FLOWS IN VEHICLES

• US 20100270419A1
• Filed: 12/15/2008
• Published: 10/28/2010
• Est. Priority Date: 12/14/2007
• Status: Abandoned Application

• Current Assignee: Urban Aeronautics Ltd.
• Original Assignee: Urban Aeronautics Ltd.
• Inventors: Yoeli, Raphael
• Application Number:
  US12/747,830
• Publication Number:
  US 20100270419A1
• Time in Patent Office: Days
• US Class Current: 244/12.100
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage

Abstract

A control system for a vehicle having plural control elements actuated at a single actuation point including a redundant electric actuator assembly including a control rod moveable linearly in two opposite directions mounting n electric motors, each motor having a controller and a feedback sensor for controlling linear movement of said rod, each motor contributing approximately 1/n of total control power required for adjusting one or more of said plural control elements, such that failure of any of said motors controllers or feedback sensors leaves sufficient predetermined minimum control power available for operating said control system.

Claims

1. A control system for a vehicle having plural control elements actuated at a single actuation point comprising:

a redundant electric actuator assembly including a control rod moveable linearly in two opposite directions mounting n electric motors, each motor having a controller and a feedback sensor for controlling linear movement of said rod, each motor contributing approximately 1/n of total control power required for adjusting one or more of said plural control elements, such that failure of any of said motors controllers or feedback sensors leaves sufficient predetermined minimum control power available for operating said control system.

2. The control system of claim 1 wherein said rod comprises a non-rotatable threaded ball screw and wherein each of said plurality of motors includes a threaded nut engaged with said ball screw.

3. The control system of claim 2 wherein said feedback sensors are engaged with said ball screw at a location axially spaced from said motors.

4. The control system of claim 1 wherein n=4.

5. The control system of claim 1 wherein said vehicle comprises a VTOL vehicle having at least a pair of ducted lift fans, and wherein said plural control elements include a variable pitch propeller and a plurality of adjustable directional vanes associated with each of said ducted lift fans.

6. The control system of claim 1 wherein said rod comprises a rotatable rod connected to a linear output.

7. A redundant actuator assembly for controlling a linear output in a vehicle control system comprising:

n actuators divided into two groups, each group including n/2 single-channel actuators, each adapted to control specified control elements of said vehicle control system, said plural, single-channel actuators of each group arranged in series;

one actuator of each group connected to a chassis of the vehicle, and another actuator of each group connected to a rocker arm pivotally secured to the linear output, wherein movement of the linear output is affected by movement of any one of said single-channel actuators.

8. The redundant actuator assembly of claim 7 wherein each of said actuators is a linear actuator, and wherein actuators of each group are connected at linearly-moveable joints.

9. The redundant actuator assembly of claim 7 wherein said vehicle comprises a VTOL vehicle having at least a pair of ducted lift fans, and wherein said control elements include a variable pitch propeller and a plurality of adjustable directional vanes associated with each of said ducted lift fans.

10. A power distribution system for a VTOL vehicle having forward and aft lift fans comprising:

a pair of engines connected to respective associated transmissions arranged to distribute power to an aft lift fan gearbox, each transmission also connected to a respective intermediate gearbox which, in turn, is connected to a forward lift fan gearbox, thereby establishing a redundant load path to said forward lift fan.

11. The power distribution system of claim 10 wherein each intermediate gearbox is a 90°

gearbox, and wherein a pair of substantially parallel shafts connect said respective associated transmissions to said intermediate gearboxes, and wherein a pair of substantially coaxial shafts, arranged substantially perpendicular to said substantially parallel shafts, connect said intermediate gearboxes to said forward lift fan gearbox.

12. The power distribution system of claim 10 wherein each intermediate gearbox is an angled gearbox, and wherein a pair of substantially parallel shafts connect said respective associated transmissions to said intermediate gearboxes, and wherein a pair of angled shafts connect said intermediate gearboxes to said forward lift fan gearbox.

13. A VTOL vehicle comprising:

a fuselage supporting forward and aft lift fans;

a section of said fuselage having a substantially airfoil-shaped body with upper and lower surfaces; and

at least one hollow passage having an inlet along a trailing end portion of said lower surface of the body and an outlet along a trailing end portion of said upper surface of the body, such that, in flight, a pressure differential between an upper surface zone and a lower surface zone will generate suction along said lower surface sufficient to attach a boundary layer flow stream to said lower surface.

14. The VTOL vehicle of claim 13 wherein said at least one said inlet and said at least one outlet are connected through one or more larger intermediate passages.

15. The VTOL vehicle of claim 13 wherein said at least one inlet comprises plural inlets and said at least one outlet comprises plural outlets, and wherein said plural inlets and said plural outlets connect to respective manifolds that are, in turn, connected to one or more intermediate passages.

16. The VTOL vehicle of claim 13 wherein said at least one inlet comprises plural inlets and said at least one outlet comprises plural outlets, each inlet connected to a corresponding outlet by a single discreet passage.

17. A method of controlling separation of a flow stream at a boundary layer along a surface of a VTOL vehicle fuselage in forward flight, the fuselage supporting a forward lift fan and an aft lift fan, the method comprising:

(a) shaping a portion of the fuselage to have a substantially airfoil-shape with upper and lower surfaces; and

(b) creating a suction force along the lower surface of said center portion by utilizing a low-pressure source generated at another portion of the fuselage to thereby attach the flow stream at the boundary layer to the lower surface.

18. A method of operating a VTOL vehicle in forward flight, the vehicle having a fuselage supporting a forward lift fan and an aft lift fan, a center portion of the fuselage having a substantially airfoil shape, the method comprising:

(a) generating lift forces at the forward and aft lift fans and on said center portion of said fuselage; and

(b) reducing the lift at the forward lift fan relative to the aft lift fan to thereby lessen suction of air into the forward lift fan and thereby increase overall vehicle lift circulation and thus also the VTOL vehicle'"'"'s lift-to-drag ratio, while contributing to the reduction of separation of flow at a lower surface of said center portion of the fuselage.

19. The method of claim 18 wherein step (b) is carried out by one or more of (i) reducing rotational speed of the of the forward lift fan;

(ii) changing blade pitch of the forward lift fan;

or (iii) blocking air flow through the forward lift fan.