AU2007202263A1 - Vectored thrust system contained within a wing - Google Patents

Description

18/05/2007 20:29 (+61 9587-2839 Hulpro Engineering Pty Ltd Tony-IP Australia 03/10 00 AUSTRALIA Patents Act 1990

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SCOMPLETE SPECIFICATION cI FOR A STANDARD PATENT

ORIGINAL

Name of Applicants: Jonathan Ariaratnam Tony Asplet Actual Inventor: Jonathan Ariaratnam Tony Asplet Address of Service: 57a Queen Victoria Street Bexley, NSW 2207.

Invention Title: VECTORED THRUST SYSTEM CONTAINED WITHIN A WING Details of Associated Provisional Application No: 2006902658 dated 18 May, 2006 The following statement is a full description of this invention, including the best method of performing it known to me/us:- COMS ID No: SBMI-07438749 Received by IP Australia: Time 20:32 Date 2007-05-18 if 18/05/2007 20:29 C+61 9587-2839 Hulpro Engineering Pty Ltd Tony-*IP Australia 04/10 11 Vectored Thrust System contained within a Wing This invention relates to a Vectored Thrust System contained within a wing. This 00 system is designed to propel a Vertical Take Off and Landing (VTOL) or Short Take Off and Landing (STOL) vehicle.

The Vectored Thrust System contained within a wing comprises of: A wing.

C"l Thrust devices i.e. propellers and their power plants.

C" Cylindrical ducts.

Thrust devices capable of manoeuvring within the ducts.

Actuators to move the thrust devices within the ducts.

A movable mass to alter the Centre of Gravity.

C"l The design comprises of Vectored Thrust Systems contained within a wing Figure 1.

The thrust devices 1 are positioned on the outer region of the wing within their ducts 2. Both thrust devices must be at an equal distance from the centre of the wing. Both thrust devices must be at an equal distance from the leading edge or trailing edge of the wing.

The duct 2 depth would be that of the wing sections depth, its intake would begin at the upper surface of the wing and the exhaust outlet would be located at the lower surface of the wing. The duct diameter would be smaller than the aerofoil's sections cord and slightly larger than the propellers 3 diameter. The area where the ducts meet the upper and lower surface of the wing 8 and 9 are contoured to the shape of an aerofoil thus increasing lift in forward flight.

Both thrust devices provide thrust in the vertical axis, horizontal axis and thrust in the transitional phase from vertical flight to forward flight. To accomplish this, the thrust devices are manoeuvred within the ducts without altering the orientation of the vehicle, Figure 1 vertical flight. Figure 2 transitional flight and Figure 3 forward flight.

The thrust devices are mounted on torque tubes 4 housed in bearings and connected to actuators within the wing. Actuators rotate the torque tubes and manoeuvre the thrust devices within the ducts.

The combined or independent manoeuvring of the thrust devices provide Pitch, Roll and Yaw directional control and stability to the vehicle.

When the Vectored Thrust System is configured for vertical flight Figure 1. the thrust devices are positioned in the vertical plane. Thrust is generated in the vertical direction, when the thrust is greater than the weight of the vehicle, the vehicle will ascend or hover. Pitch, Roll and Yaw control and stability are attained by the movement of the thrust devices.

When the Vectored Thrust System is configured for transitional flight Figure 2, the thrust devices are rotated forward. This configuration leads to wing borne operation, lift is provided by the thrust devices and the wing section. In this phase of flight the control surfaces 5 at the trailing edge of the aerofoil and with the combined movement of propulsion systems are used to provide pitch and roll direction control and stability.

COMS ID No: SBMI-07438749 Received by IP Australia: Time 20:32 Date 2007-05-18 S18/05/2007 20:29 (+61 9587-2839 Hulpro Engineering Pty Ltd Tony-*IP Australia 05/10 2 When the Vectored Thrust System is configured for forward flight Figure 3, the thrust devices are positioned in the same axis as the wings centreline only providing O forward thrust All vertical lift is now produced by the wing section. Control surfaces at the trailing edge of the wing provide pitch and roll direction control. Yaw axis control is provided by altering the thrust and position of the thrust devices and by the use of drag creating control surfaces at the trailing edge of the aerofoil 5. This feature removes the requirement for a vertical stabilizer to provide yaw stability.

C The three flight phases which comprise of vertical flight, transitional flight and forward flight combine to permit the vehicle to achieve Vertical Take Off and Landing (VTOL) Cl 15 or Short Take Off and Landing (STOL) performance.

STo counter the changes in the Centre of Gravity due to wing configuration or the Smanovering of the thrust devices in the three flight phases a weight 6 is mechanically l positioned along horizontal 7 axis to constantly trim the vehicle and provide the optimal Centre of Gravity.

COMS ID No: SBMI-07438749 Received by IP Australia: Time 20:32 Date 2007-05-18

Claims (7)

1. The Vectored Thrust Systems stowed and packaged configuration inside the 00 wing.

2. The Vectored Thrust Systems ability to reposition itself within the wing to provide thrust in the vertical axis, thrust in the horizontal axis and thrust in the transitional phase from vertical thrust to horizontal thrust without altering the orientation of the vehicle. C

3. The Vectored Thrust Systems ability to manoeuvre the vehicle in any direction. C 15

4. The Vectored Thrust Systems ability to provide Yaw axis control by altering the l thrust and or direction of the thrust devices. This feature removes the Srequirement for a vertical stabilizer to provide yaw axis stability.

Optimal Centre of Gravity provided in all phases of flight through the positioning of a mass along the horizontal axis.

6. The area where the ducts meet the upper and lower surface of the wing are contoured to the shape of an aerofoil thus increasing lift in forward flight.

7. The Vectored thrust system as herin described with reference to the accompanying drawings. Jonathan Ariaratnam 17 May 2007. Tony Asplet 17 May 2007. COMS ID No: SBMI-07438749 Received by IP Australia: Time 20:32 Date 2007-05-18