AIRCRAFT CONTROL SYSTEM

Abstract

The present invention provides a pod (100) for an aircraft (1000), comprising: a housing (1); a unit (2) comprising a propulsion system, the unit comprising at least one attachment point (5) for coupling the unit to the housing (1), wherein the position of the unit relative to the housing is selected from a plurality of positions based on the centre of gravity of the aircraft, such that deflection of control surfaces required for the aircraft to maintain a constant angle of attack is minimised. The invention also provides an aircraft (1000) having the pod (100) and a method of balancing the aircraft (1000).

Claims

1. A pod for an aircraft, comprising: a housing; a unit comprising a propulsion system, the unit comprising at least one attachment point for fixing the unit within the housing, wherein the position of the unit relative to the housing is selected from a plurality of positions based on the centre of gravity of the aircraft such that deflection of control surfaces required for the aircraft to maintain a constant angle of attack is minimised.

2. The pod according to claim 1, wherein the unit is slidable within the housing in order to be moved to the selected position.

3. The pod according to claim 1, wherein the position of the unit is selectable from one of a plurality of positions along a longitudinal axis of the housing.

4. The pod according to claim 1, comprising a processor configured to: calculate the centre of gravity of the aircraft while the aircraft is in flight; select a position of the unit relative to the housing based on the calculated centre of gravity; and actuate a control mechanism to move the unit to the selected position.

5. The pod according to claim 1, wherein a spacer of a predetermined thickness is disposed between the attachment point and the housing, and wherein the thickness of the spacer is selected such that the unit is attachable to the housing such that the unit is disposed at the selected position relative to the housing.

6. The pod according to claim 1, wherein the unit comprises: a control system for controlling aircraft systems; a motor, motor controller and a propeller extending from the unit for providing thrust to the aircraft; a power storage system for storing power to power the aircraft; and a frame for holding the control system, propulsion system and power storage system.

7. The pod according to claim 6, wherein the power storage system comprises a plurality of batteries arranged in layers.

8. The pod according to claim 1, wherein the unit is replaceable.

9. An aircraft comprising at least one pod according to claim 1, wherein a longitudinal axis of the pod is substantially parallel with a longitudinal axis of the aircraft.

10. The aircraft according to claim 9, wherein the at least one pod is coupled to or integrated with a wing of the aircraft.

11. The aircraft according to claim 9, comprising an interchangeable payload attached to the nose or tail end of the aircraft.

12. The aircraft according to claim 9, wherein the aircraft is an unmanned solar powered aircraft.

13. A method of balancing an aircraft such that deflection of control surfaces required for the aircraft to maintain a constant angle of attack is minimised, the aircraft comprising at least one pod according to claim 1, the method comprising: calculating a first centre of gravity of the aircraft in a predetermined configuration; calculating a second centre of gravity of the aircraft in a present configuration; if the difference between the first centre of gravity and the second centre of gravity is greater than a threshold, selecting a position of the unit relative to the housing to move the second centre of gravity closer to the first centre of gravity; and fixing the unit within the housing, such that the unit is disposed at the selected position relative to the housing.

14. The method according to claim 13, comprising selecting a thickness of a spacer to dispose between the housing of the pod and an attachment point of the unit, the thickness of the spacer being selected such that the unit is attachable to the housing such that it is disposed at the selected position relative to the housing.

15. The method according to claim 13, wherein the unit comprises: a control system for controlling aircraft systems; a motor, motor controller and a propeller extending from the unit for providing thrust to the aircraft; a power storage system for storing power to power the aircraft; and a frame for holding the control system, propulsion system and power storage system.

16. The pod according to claim 2, wherein the position of the unit is selectable from one of a plurality of positions along a longitudinal axis of the housing.

17. The pod according to claim 2, comprising a processor configured to: calculate the centre of gravity of the aircraft while the aircraft is in flight; select a position of the unit relative to the housing based on the calculated centre of gravity; and actuate a control mechanism to move the unit to the selected position.

18. The pod according to claim 3, comprising a processor configured to: calculate the centre of gravity of the aircraft while the aircraft is in flight; select a position of the unit relative to the housing based on the calculated centre of gravity; and actuate a control mechanism to move the unit to the selected position.

19. The pod according to claim 2, wherein a spacer of a predetermined thickness is disposed between the attachment point and the housing, and wherein the thickness of the spacer is selected such that the unit is attachable to the housing such that the unit is disposed at the selected position relative to the housing.

20. The pod according to claim 3, wherein a spacer of a predetermined thickness is disposed between the attachment point and the housing, and wherein the thickness of the spacer is selected such that the unit is attachable to the housing such that the unit is disposed at the selected position relative to the housing.

Description

[0072] The invention is described by reference to two embodiments and the accompanying drawings in which:

[0073] FIG. 1 shows the assembled pod integrated into the airframe.

[0074] FIG. 2 shows the AIB and how it is installed into the outer housing of the pod.

[0075] FIG. 3 shows an arrangement of power storage, propulsion & avionics system within the AIB of the pod.

[0076] FIGS. 4 a & b show two cross sections of the thermal insulation within the outer casing of the pod.

[0077] FIGS. 5 a & b show two cross sections of the thermal insulation within the AIB of the pod.

[0078] FIG. 6 shows the assembled removable pod and the mounting arrangement connecting the pod to the airframe.

[0079] FIG. 7 shows a perspective view of an aircraft according to embodiments of the present invention.

[0080] FIG. 1 shows a pod 100 (or nacelle, or fairing) according to an embodiment of the present invention which is permanently attached to a wing of a solar powered high altitude unmanned aircraft. The pod 100 consists of an outer housing 1 and an inner unit, the AIB 2. The pod 100 may include other components, as explained below. The housing 1 is aerodynamically shaped to fit the AIB 2 and to reduce drag on the wing. This represents a compromise between a spherical shaped housing which is the optimal shape for maintaining the thermal state of the pod for a given volume of batteries and a long thin pod which is an optimal shape for decreasing aerodynamic drag.

[0081] In this embodiment the pod 100 is integrated into the aircraft wing 3, which transfers the structural load of the pod 100 mass to the aircraft structure. The attachment mechanism itself may be a low temperature adhesive or sealant.

[0082] FIG. 2 shows the removable AIB 2 within the housing 1. The housing 1 has a number of locating guides 4 and attachment points 5 that allow the AIB to be slid into the housing and secured. The AIB 2 is mounted on locating guides inside the housing which allow the AIB 2 to be slid horizontally into the housing. The AIB 2 can therefore be fitted quickly and easily into the pod 100.

[0083] The locating guides 4 allow the longitudinal position of the AIB to be changed to balance the centre of gravity of the aircraft. This would be required whenever the payload mass or location change. Suitable sized spacers may be placed between the housing and the AIB at the attachment points 5. The AIB can be attached to the housing 1 at the attachment points 5 by a securing device, such as a screw, bolt or clip.

[0084] FIG. 3 shows the internal structure of the AIB 2 in detail. It consists of a structural frame 6 which holds the batteries 8, the power control electronics board 7, the electronics used to control the aircraft 12 (avionics) and the propulsion system, comprising a motor 10, a motor controller 11 and a propeller 9. Electrical connectors are provided to link the power 13 and control systems 14 in the AIB to the solar array, actuators, sensors and equipment on the rest of the aircraft.

[0085] The structural, control and power interfaces are independent of the batteries used enabling the aircraft design to remain unchanged even when the batteries or other systems are changed when improved battery technology is available. The same would be true of changes to the avionics and propulsion systems as well.

[0086] Since the AIB contains all the aircraft systems required to operate components of the aircraft the AIB can be tested as a single, small unit then mass produced. The AIB can be removed and replaced quickly thereby reducing the turn round time between flights.

[0087] FIGS. 4a & 5a show the thermal control system that is fitted within the pod 100. Heat is generated within the pod 100 as a by-product of the operation of the motor 10, the power control 7, avionics 12, and propulsion control 11. This energy recovery maintains a higher temperature inside the housing 1 and the AIB 2.

[0088] Within the housing 1 the thermal insulating material 15 is permanently applied to the inner wall of the housing. A cross section view showing the composition of the housing is shown in FIG. 4b. This provides a thermal layer capable of retaining heat within the pod 100.

[0089] The AIB's thermal control system, shown in FIG. 5a, consists of one or more layers of thermal insulation 17, one or more heater elements 16 and temperature sensors located between or adjacent to the layers of batteries 8 which are the most temperature sensitive components in the AIB in this embodiment. The thermal control system is held between the structural frame 6 and the batteries 8 as shown in FIG. 5b such that a tolerance gap 18 is allowed between the frame 10 and thermal insulation 15 to account for changes in battery. Heat is generated within the AIB by the power control 7, avionics 12, and propulsion control 11 systems. Sensors interleaved within the stacks of batteries are connected to the power control equipment 7 which monitors the temperature against an optimal operating temperature for the batteries and activate/deactivate the heater elements 16 as required.

[0090] The thermal insulation is chosen to suit the thermal characteristic of the contents of the AIB. It is designed so that it maintains the batteries, electronics and propulsion system within their acceptable operating temperatures. As the thermal characteristics change, so may the thermal material used or its thickness.

[0091] One or more pods 100 may be integrated (i.e. integrally formed) into each wing 3 or the fuselage of the aircraft as required. The additional pods may have different configurations of aircraft system or thermal insulation within the AIB.

[0092] A second embodiment for a pod 100 (or nacelle) is shown in FIG. 6. This pod can be detached from the airframe.

[0093] The pod 100 contains (i.e. includes) a housing 1 and an AIB 2 as described in the preceding embodiment. The housing 1 has a number of attachment points 20 which fasten to corresponding points 19 on the airframe. Other forms of attachment are also possible such as, but not limited to, clips, screws, locking hooks, adhesive or latches.

[0094] The pod 100 can be easily removed, replaced or substituted for another pod without any change to the airframe itself.

[0095] The method of use of the invention is to design, and test a pod and one or more configurations of the AIB. When tested the pod and AIB can be mass produced and stored. Prior to a flight one or more pods are fitted to a solar powered HALE aircraft. The payload for the mission is also fitted and the AIB moved to adjust the aircraft's centre of gravity taking into account the payload's position. The aircraft is launched, executes its mission and lands. The AIB is removed and replaced with a new unit from the store. The payload may or may not be replaced. The aircraft is relaunched and executes its next mission. The discarded unit is refurbished by, for example replacing the batteries, and returned to storage.

[0096] When a technological upgrade of an aircraft system becomes available e.g. a higher capacity, lighter weight batteries or a new system is added to the aircraft a new AIB is designed, built, tested and manufactured. The thermal requirements of the new systems are assessed as part of the design process so that heating and insulation can be adapted to provide an optimal thermal environment for the systems within the AIB.

[0097] Existing aircraft can then be upgraded by fitted the new AIB 2 within the existing pod housing 1. There is no need to change the airframe to accommodate the technological advancement or the introduction of a new aircraft system.

[0098] FIG. 7 shows an aircraft 1000 having a pod 100 attached to each wing. Each pod 100 is orientated such their longitudinal axes substantially align with a longitudinal axis of the aircraft 1000 such as the central axis. In another embodiment, there may only be a single pod 100 coupled to the aircraft 1000, for example on the nose of the aircraft 1000. In another embodiment, there may be a plurality of pods 100 attached to each wing. The aircraft 1000 is a HALE aircraft, optimised for operating at high altitudes for long periods of time. Therefore, the aircraft is relatively lightweight and has wings 3 designed for generating large amounts of lift with little drag. The pod 100 contains a propulsion device, such as a tractor propeller or pusher propeller.

[0099] The aircraft 1000 includes a fuselage 23, tail surface 22, wings 3 and a payload 21. The payload 21 is attached to the aircraft 1000 at the end opposite to the tail surfaces 22. In other embodiments, a payload 21 may additionally or alternatively be disposed at the rear of the aircraft 1000. In another embodiment, the payload 21, or payloads, may be coupled to a wing 3 or wings of the aircraft 1000.

[0100] The payload 21 is interchangeable. In other words, the mass of the payload 21 may be different on each flight of the aircraft 1000 to accommodate different sensor or mission equipment. The payload 21 is for example a releasable satellite or weapon. The payload 21 may alternatively be designed not to be releasable, such as a sensor package. The length of fuselage between the payload 21 and wings 3 may also be different for each flight. The mass of the payload 21 and position of it relative to the rest of the aircraft 1000 generates a moment, counter balanced by the principal aircraft forces generated by the wings 3 and tail surface 22. The centre of gravity of the aircraft 1000 is calculated for each flight, which is dependent upon the payload 21 and its location.

[0101] Each pod 100 has a housing 1. An AIB 2 is disposed substantially within the housing 1, such that its propeller 9 protrudes from the housing 1. The AIB 2 is arranged to slide along a longitudinal axis of the housing 1 such that the propeller 9 protrudes further from the housing 1 or closer to the housing 1. It can then be fixed in the selected position. The AIB 2 may slide with the aid of a locating guide 4. There may be a plurality of locating guides 4. Additionally or alternatively, in some embodiments the AIB 2 is arranged to slide along a lateral axis of the housing 1. This tends to be desirable where a payload 21 is carried on a wing 3 of the aircraft 1000, which would induce a roll if the aircraft 1000 were not counterbalanced in some way.

[0102] When the desired position of the AIB 2 relative to the housing 1 is achieved, an attachment point 5 is used to couple the AIB 2 within or to the housing 1. In one embodiment, in order to retain the position of the AIB 2 relative to the housing 1, a spacer of a predetermined thickness is disposed between the attachment point 5 and the housing 1.

[0103] To improve the trim of the aircraft 1000, thereby reducing the elevator or aileron input (and thus drag) necessary to keep the aircraft 1000 flying straight and level, or at some other chosen angle of attack, the position of the AIB 2 in the housing 1 is adjusted using the spacer as previously described. A new centre of gravity can then be calculated to set the trim. By reducing drag, power consumption tends to be reduced.

[0104] The aircraft 1000 may be configured to release a payload 21 during flight. Releasing a payload 21, particularly where the payload 21 is heavy relative to the airframe of the aircraft 1000, can alter the aerodynamic performance of the aircraft 1000. This results in the trim of the aircraft 1000 having to be adjusted during flight to maintain a constant angle of attack. Therefore, in some embodiments, the pod 100 includes a processor for determining the new centre of gravity of the aircraft 1000, after the payload 21 has been released. The processor then determines a desired position of the AIB 2 within the housing 1 in order to alter the trim of the aircraft 1000, making it more balanced. A motor within the pod 100 can then be used to drive the AIB 2 to move to the desired position.

[0105] While the use of a spacer has been described as being used to set the distance to which the AIB 2 is inserted into the housing 2 in the embodiment above, in other embodiments, the spacer is not necessary, particularly where the position of the AIB 2 is adjustable during flight. For example, in some embodiments either the AIB 2 or the housing 1 are telescopic. In this latter case, reference to the position of the AIB 2, or propeller 9 of the AIB 2, relative to the housing 1, is in relation to the housing 1 prior to its extension.