GB2450482A

GB2450482A - Secondary wing arrangement

Info

Publication number: GB2450482A
Application number: GB0712177A
Authority: GB
Inventors: Michael Campbell-Jones
Original assignee: Individual
Current assignee: Individual
Priority date: 2007-06-25
Filing date: 2007-06-25
Publication date: 2008-12-31
Also published as: GB0712177D0

Abstract

A secondary wing 5, 6 is provided below a main wing of a flying object (such as a light aircraft, a motorized paraglider having a propeller 2 and a harness 1 attached to a primary wing (not shown), an unmotorised paraglider, a microlight aircraft, an unmanned aircraft or a model aircraft). The secondary wing is adapted to pivot and may be controllable independently of the primary wing to vary its angle of attack and thereby increase or decrease the wing loading. The secondary wing may be made from foamed materials, polystyrene, or honeycomb composite or ribbed structure, and may comprise two independently movable elements. The secondary wing may be provided with movable flaps.

Description

IMPROVEMENTS IN OR RELATING TO FLIGHT

The present invention relates to improvements in or relating to objects that fly and in particular to aircraft such as light aircraft including motorized paragliders and unpowered flight vehicles, such as unmotorized paragliders and model aircraft. The invention is particularly concerned with light weight flight vehicles such as microlights, power gliders, paragliders including motorized and unmotorized paragliders, unmanned aircrafts and the like.

The ability of motorized paragliders to take off and fly is determined by several factors.

The ability of the pilot to carry the system prior to take off; the system typically comprising an engine, a frame, a harness, a fuel tank and the fuel itself and the wing system. The total weight of the system including the wing and the pilot also determines the speed at which the motorized paraglider can fly and also the distance the motorized paraglider is capable of flight. Typically the maximum system weight that can be tolerated is from 20 to 30 kilograms (system weight comprising harness, engine and fuel tank) and such weight limits the speeds attainable by the paragliders to no more than 30 km/hr to 50 km/hr.

The maximum speed and maximum flying time for light aircraft and model aircraft are also dependent on the weight of the aircraft.

The ability to fly relies on an upward force on a wing whether it is created by the shape of a wing on an aircraft or by the wing of motorized or unmotorized paragliders. The wings are shaped to optimize the aero-dynamic effect which is dependent upon the size, shape and method of powering the object that is to fly. We have now found that the speed of flight particularly for light aircraft systems such as motorized and unmotorized paragliders, unmanned aircraft, light aircraft and model aircraft can be increased by the provision of a secondary wing system.

The present invention therefore provides a wing system comprising a primary wing and a secondary wing wherein the secondary wing is mounted to be below the main wing during flight and is adapted to pivot in a substantially horizontal plane and perpendicular to the flight axis be so as to interact with the air flow to create additional forces on the wing system.

Whilst the invention may be used with any object that flies it is particular useful with motorized or unmotorized paragliders, light aircraft and model aircraft. The construction and operation of the wing system of the present invention will now be described in relation to its use with motorized paragliders although similar principles apply to other objects that fly.

A motorized paraglider consists of a harness in which the pilot sits provided with a motor and a propeller which drives the paraglider. A fuel tank is usually included as part of the harness system. The harness is attached to the wing of the paraglider by means of cables, wires or stings which allow the upward aero dynamic forces exerted on the wing to enable the paragliders to become airborne. The cables, wires or strings also allow the pilot to control the orientation of the wing to the air flow and so to steer and control the speed and direction of the paragliders. We have found that the provision of a small wing, significantly smaller than the primary wing, below the primary wing of the paraglider which can be moved to vary its inclination to the direction of the air flow created by the flight of the paraglider according to the present invention can permit a significant increase or decrease in the speed of lift and the speed of travel of the paraglider and also with a motorized paraglider the maximum distance of travel for a given volume of fuel can be increased. The secondary wing may be mounted at any convenient location bellow the main wing providing its inclination to the direction of the air flow can be altered and controlled by the pilot and this can be accomplished independently of the primary wing system. In a particular preferred embodiment the secondary wing may be provided as attachments at either side of the harness.

Accordingly in a further embodiment the invention provides a harness for a paraglider provided with a wing system The secondary wing system should be such that the upward force created by the air flow on the secondary wing is always less that the upward force created on the primary wing.

The secondary wing should be mounted so that its location is close to or in line with the centre of pressure/lift of the primary wing and should be sufficiently remote from the primary wing that it does not adversely interfere with the air flow around the primary wing. The secondary wing is capable of movement independent from any movement of the primary wing, so that the primary wing can maintain the angle of attack which can therefore be controlled independently of the secondary wing.

The secondary wing may be made of any suitable material and is preferably as light as possible and may be made of reinforced and/or foamed materials such as honeycomb composite or ribbed structure. The secondary wing is preferably shaped like a conventional wing having a tapered cross section with a circular leading edge pointing in the direction of attack of the secondary wing relative to the line of attack of the main wing and the direction of flight.

The secondary wing is provided with means whereby it is possible for the pilot to vary the angle of attack of the secondary wing relative to the line of attack of the main wing and the direction of flight of the flying object. In this way the secondary wing can be moved to be at a positive angle to the line of attack which creates a positive lifting force effectively reducing the payload and increasing the rate of climb. Conversely if the secondary wing is moved to be at a negative angle to the line of attack this will create a downward force effectively adding to the payload and increasing the speed of travel by increasing the wing load. If desired, the secondary wing can be maintained in the neutral or parallel position where it will have little if any effect on the effective payload.

Any suitable means may be employed for varying the angle of inclination of the secondary wing. For example in the case of a paraglider where the secondary wing is attached to the harness a manual lever control or stick may be used and it may be such that the two elements that make up the secondary wing are moved together or independently of each other. Independent movement of the two elements can provide the added benefit of controlling the direction of flight of the paraglider. In other flight systems such as unmanned aircraft or model aircraft the angle of the secondary wing may be controlled automatically through a flight planner and/or remote control. The secondary wing can also be provided with small moveable flaps and in this embodiment a rising or descending force can be obtained by moving the flaps on the secondary wing rather than moving the complete wing. In the embodiment when the secondary wing system is be provided with flaps and electric motors can be provided to control the operation of the flaps.

The present invention is illustrated but in no way limited by reference to the accompanying drawings in which Figure 1 shows a motorized paraglider fitted with a secondary wing according to the present invention.

Figure 2 show how the system can be applied on any aircraft.

Figure 3 shows diagrammatically how a pilot can be positioned in the harness relative to the secondary wing.

Figures 4, 5 and 6 thus how the secondary wing system can be moved to cause the load or unload the paraglider.

Figure 7 shows a manual operation system to enable the pilot to control the angle of inclination of the secondary wing.

Figure 8 show flap alternative Figure 10 show a stabilized main lifting wing and a secondary wing system in the neutral position, pendular stability is combined with variable payload.

Figures 11, 12 and 13 are a similar diagrammatic illustration showing the secondary wing in the neutral position (figure 11), in the positive position (figure 12) and the negative position (figure 13), pendular stability is combined with variable payload.

Figure 1 shows a harness (1) positioned in front of the propeller system (2) and wires are attached to the handles of the harness (4) and which are attached to the primary wing system (not shown). A secondary wing system is shown having two limits (5) and (6) extending from the harness. Figure 2 is a view looking down on the harness shown in Figure 1. Figure 3 shows a pilot (7) positioned in the harness of Figure 1. Figure 4 shows how the two limits (5) and (6) of the secondary wing system of Figure 1 can be moved into a positive or negative position in relation to the directions of attack and Figures 5 and 6 show how the movement in the positive or negative direction as illustrated in Figure 4 can cause the paraglider to ascend or descend.

Figure 10 is an illustration of the combined wing assembly and shows the central section of the primary wing (10) and how it is located relative to the secondary wing system (11).

Figures 11, 12 and 13 are similar to Figure 10 and are included to illustrate the secondary wing in three different locations (neutral, positive and negative) relative to the primary wing.

Claims

1. A wing system for flying objects comprising a primary wing and a secondary wing wherein the secondary wing is mounted to be below the main wing during flight and is adapted to pivot in a substantially horizontal plane and perpendicular to the flight axis be so as to interact with the air flow to create additional forces on the wing system.

2. A wing system according to Claim 1 in which the flying object is a motorized or unmotorized paraglider, a light aircraft or a model aircraft.

3. A wing system according to Claim 1 or Claim 2 in which the secondary wing is mounted so that its location is close to or in line with the centre of pressure/lift of the primary wing.

4. A wing system according to any one of the primary claims in which the secondary wing is located at a position sufficiently remote from the primary wing that it does not adversely interfere with the air flow around the primary wing.

5. A wing system according to any of Claims 1 to 4 in which the secondary smaller wing is able to change its angle of attack through positive to negative, relative to the center of lift and has to be maintained or controlled independently

6. A wing system according to any of the preceding claims in which the secondary wing is made of reinforced and/or foamed materials.

7. A wing system according to claim 6 in which the material is polystyrene or a honeycomb composite or ribbed structure.

8. A wing system according to any of the preceding claims in which the secondary wing has a tapered cross section with a circular leading edge which is pointing in the direction of airflow of the secondary wing. 6 L

9. A wing system according to any of the preceding claims in which means are provided whereby it is possible for the pilot to vary the angle of attack of the secondary wing.

10. A wing system according to claim 9 in which the means comprises a stick or any control system.

11. A wing system according to any of the preceding claims in which the secondary wing is made of two elements which can be moved together or independently of each other.

12. A wing system according to any of the preceding claims in which the angle Of the secondary wing may be controlled automatically or from a remote control.

13. A wing system according to any of the preceding claims in which the secondary wing is provided with moveable flaps.

14. A wing system according to any of the preceding claims in which the flying object is a motorized paraglider and consists of a harness provided with a motor and a propeller.

15. A harness for a paraglider provided with a wing system.

16. A wing system according to Claim 15 in which the secondary wing system is provided as attachment at either side of the harness