Patent Grant
8376273
The present application is based on International Application Number PCT/GB2006/004206 filed Nov. 10, 2006, and claims priority from British Application Number 0523069.3 filed Nov. 11, 2005, the disclosures of which are hereby incorporated by reference herein in their entirety.
The present invention relates to aircraft and in particular to a method of maneuvering an aircraft on the ground.
It is desirable for aircraft, and particularly large aircraft, to be able to manoeuvre on the ground within a tight turning circle. To turn an aircraft in a tight turning circle it is known to typically perform a ‘braked pivot turn’. The braked pivot turn is typically effected by turning the aircraft nose wheel, applying differential engine thrust and applying the brakes to all the wheels of one of the landing gear, broadly speaking around which, the aircraft turns.
Such a manoeuvre generates significant torsion loads in the landing gear that is on the inside of the turn due to the scrubbing of the wheel tyres on the ground, and on many aircraft the torsion loads are sufficiently large to cause fatigue damage to the landing gear structure. Aircraft to which significant fatigue damage may occur may be banned from making the above-described pivot turn manoeuvre, and are therefore limited in their on-ground maneuverability.
The present invention seeks to provide a method of braked pivot turning an aircraft which generates lower torsion loads in the landing gear structure and/or mitigates at least some of the above-mentioned problems.
The present invention provides a method of braked pivot turning an aircraft on the ground, the aircraft comprising a fuselage and a landing gear assembly located to one side thereof, the landing gear assembly comprising a bogie with a plurality of wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie,
the method including the steps of:
A braked pivot turn in accordance with embodiments of the present invention may generate lower torsion loads in the landing gear than one in which all wheels on the landing gear are braked. It is thought that during a pivot turn according to embodiments of the present invention a primary torque is generated in the landing gear assembly by the turning motion of the aircraft and the scrubbing of the tyres on the ground. In addition however, it is thought that a secondary torque is generated in the landing gear assembly due to the differential braking force applied to either side of the bogie. By applying a greater braking force to the first side of the bogie of the landing gear assembly than to the second side in accordance with embodiments of the invention, the secondary torque is generated in the opposite direction to the primary torque. The net torque to which the landing gear is subjected is thereby reduced.
It shall be understood that the aircraft is usually symmetrical about its centre line and thus usually includes at least two landing gear assemblies, each located to one respective side of the fuselage. The aircraft may include more than two landing gear assemblies.
It will also be understood that the steps recited in accordance with method(s) of the present invention need not be performed in the order shown and may, in fact, be performed in any order.
The landing gear assembly may comprise a leg and the secondary torque in the leg may be in the opposite direction to the primary torque, the net torque in the leg thereby being reduced. The leg may be connected at a location offset from the first side of the bogie. The leg may be connected to the bogie at a location between the first and second sides. The location may be mid-way between the first and second sides.
The landing gear may be to one side of the fuselage, but at a spanwise location inside the widest point of the fuselage, but preferably the landing gear is located at a spanwise location outside the widest point on the fuselage.
The thrust may be a differential thrust suitable for turning the aircraft. It will be understood that the differential thrust may include a forward thrust (i.e. a thrust that urges the aircraft to move forward) on one side of the aircraft. The differential thrust may include a reverse thrust on one side of the aircraft. The differential thrust may be a combination of forward and reverse thrust. The differential thrust may comprise a net forward thrust. The thrust is preferably generated by at least one engine on the aircraft. The net thrust may act through a centre of thrust spaced apart from the centre line of the fuselage. The spanwise spacing of the centre of thrust from the centre-line of the fuselage may be greater than the spanwise spacing of the landing gear from the centre-line of the fuselage. The net thrust may, of course, act very close to, or substantially along, the centre line of the fuselage. This may occur, for example, on an aircraft having a rear fuselage nacelle (RFN) configuration.
Usually the net thrust is a forward thrust, and the centre of turning is located outside the landing gear assembly (i.e. the spanwise spacing of the centre of turning from the centre line of the fuselage, is greater than the spanwise spacing of the landing gear assembly from the centre line of the fuselage).
A greater braking force may be applied to one or more wheels on the first side of the bogie than the second side of the bogie. Usually, all wheels on the first side of the bogie are fully braked and all wheels on the second side of the bogie are free to rotate. Alternatively or additionally brakes may be applied to fewer wheels on the second side of the bogie than the first side of the bogie. At least one more wheel may be braked on the first side of the bogie than on the second side.
The aircraft may be travelling at low speed during the manoeuvre. Preferably the aircraft is travelling at less than 40 knts. More preferably the aircraft is travelling at less than 20 knts. The aircraft may be travelling at less than 10 knts. As the aircraft tends to rotate about a given point, the speed at different points on the aircraft varies in dependence on their distance from the centre of turning. It will be understood that reference herein to the speed of the aircraft during the manoeuvre, refers to the speed of a point in the fore of the aircraft and more preferably to the speed of a point along the centre line of the aircraft which lies on a landing gear supporting a nose wheel on the aircraft.
The aircraft may further comprise a nose wheel. It will be understood that turning the nose wheel at an angle to the centre line of the fuselage, may improve the turning circle of the aircraft and/or reduce stresses in the aircraft landing gear and particularly the nose landing gear. The aircraft may of course, comprise a plurality of nose wheels, and references to the nose wheel shall be interpreted accordingly. The method according to embodiments of the present invention may further include the step of turning the nose wheel at an angle to the centre-line of the aircraft fuselage. The angle is preferably greater than 30 degrees. More preferably the angle is greater than 45 degrees. More preferably the angle is greater than 60 degrees.
It will be understood by the person skilled in the art that the nose wheel may be turned either towards or away from the direction of aircraft turning. Typically the nose wheel would be turned in the direction of the aircraft turn, such that the wheel is driven forward during the pivot turn manoeuvre.
The method may further comprise the steps of:
The method may further comprise the steps of:
Accordingly, embodiments of the present invention may be arranged to apply a greater braking force to the first side of the bogie of the landing gear assembly than to the second side, under only certain conditions. For example, a greater braking force may be applied to the first side of the bogie of the landing gear assembly than to the second side when the angle of the nose wheel to the centre line of the fuselage is greater than a threshold. The threshold may be predetermined.
The method may include the step of apportioning the braking force to either side of the bogie. The step of apportioning the braking force may be fully automated.
The method may include the step of receiving a signal relating to the application of brakes to the wheels of the aircraft landing gear (for example when the pilot applies the landing gear brakes) and applying the braking force according to the invention in dependence on this signal. Embodiments of the present invention may thereby provide a method which selectively controls the braking of wheels on an aircraft landing gear during an aircraft braked pivot turn, with a relatively low input from the aircraft pilot.
Embodiments of the present invention may also provide a brake control system for performing at least one step of the method described herein. Preferably the brake control system is arranged to brake at least one wheel on the landing gear assembly in accordance with the invention. The brake control system may be arranged to brake at least one wheel on the landing gear assembly in accordance with the invention in dependence on a signal, or more preferably a plurality of signals. For example, the brake control system may be arranged to brake at least one wheel on the landing gear when the speed of the aircraft is below a threshold value and the angle of the nose wheel is above a threshold value, the threshold values being determined by a signal or signals, received by the brake control system.
According to another aspect of the present invention there is provided a brake control system for selectively braking wheels on a landing gear assembly during an aircraft braked pivot turn, the aircraft comprising a fuselage and the landing gear assembly being located to one side thereof, the landing gear assembly comprising a bogie with a plurality of wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie,
The brake control system may comprise a brake input receiver for receiving a signal relating to the application of brakes to the wheels of the aircraft landing gear, wherein the brake control system is arranged to effect the braking force in dependence on the signal received by the brake input receiver. The brake input receiver may receive the signal when the pilot applies the landing gear brakes. Embodiments of the present invention may thereby provide a brake control system which selectively controls the braking of wheels on an aircraft landing gear during an aircraft braked pivot turn, with a relatively low input from the aircraft pilot.
The brake control system preferably further comprises a first receiver for receiving a signal relating to an aircraft parameter. The brake control system may comprise a plurality of receivers for receiving a signal or signals relating to a plurality of aircraft parameters. An aircraft parameter may, for example, be the speed of the aircraft. An aircraft parameter may be the angle of the nose wheel to the centre line of the aircraft fuselage.
The brake control system may be arranged to effect, via the braking of at least one wheel, and in dependence on the signal or signals received by at least one receiver, and more preferably in further dependence on the signal received by the brake input receiver, a greater braking force on the first side of a bogie of the landing gear assembly than on the second side.
The brake control system may further comprise a database for storing an aircraft parameter reference threshold. The brake control system may be arranged to compare the value of the aircraft parameter to the aircraft parameter reference threshold, and may be arranged to effect the braking of at least one wheel in dependence on the comparison of the aircraft parameter to the aircraft parameter reference threshold.
Embodiments of the present invention may therefore provide a method and a brake control system which selectively controls the braking of wheels on an aircraft landing gear during a braked pivot turn, with a relatively low input from the aircraft pilot. The method and brake control system may selectively control the braking of wheels on an aircraft landing gear during a braked pivot turn if the aircraft parameter(s) are outside certain thresholds. For example if the aircraft pilot attempts to manoeuvre the aircraft on the ground with the nose wheel at an angle of 70 degrees and with all wheels on a landing gear assembly (preferably the landing gear assembly on the inside of the turn) braked, the brake control system may selectively control the braking of wheels on an aircraft landing gear in accordance with the invention, such that the secondary torque is in the opposite direction to the primary torque.
According to another aspect of the present invention there is provided an aircraft for use in the method of the invention as described herein, wherein the aircraft is so arranged that a greater braking force can be applied to the first side of the bogie of the landing gear assembly than to the second side.
According to another aspect of the present invention there is provided an aircraft including a brake control system as described herein.
According to yet another aspect of the present invention there is further provided a method of braked pivot turning an aircraft on the ground, the aircraft comprising a fuselage, two landing gear assemblies, the landing gear assemblies being located either side of the fuselage and each comprising a bogie with a plurality of wheels mounted thereon, at least one wheel being located on an inner side of the bogie and at least one wheel being located on an outer side of the bogie,
The present invention is of greater application to larger aircraft. The aircraft is preferably heavier than 50 tonnes dry weight, and more preferably heavier than 200 tonnes dry weight. The aircraft is preferably of a size equivalent to an aircraft designed to carry more than 75 passengers, and more preferably more than 200 passengers.
Embodiments of the present invention may equally apply to other types of tight turns, such as a Jacobs manoeuvre.
It will be understood that aspects of the invention described with reference to the methods of the invention may equally be applied to any of the above-described apparatus of the invention, such as the aircraft and the brake control system, or to any of the other methods of the invention, and vice versa.
Various embodiments of the invention will now be described, by way of example only, with reference to the accompanying schematic drawings of which:
a to 1d show an aircraft performing a braked pivot turn,
a to 2c are images from a computer simulation, showing the loads in a landing gear assembly during three different braked pivot turns, and
a to 1d show a plan view of an aircraft 1 performing a braked pivot turn on a narrow runway 2. The aircraft comprises a fuselage 3 and wings 5, and four engines 7. Two landing gear assemblies 9, 10 are located under the wings 5 and either side of the fuselage 3. Each landing gear assembly comprises (referring to
In
As is known in the art, to effect a first type of braked pivot turn the pilot performs three steps. First the nose wheel 11 is turned to one side. Then the pilot applies the brakes to the wheels of one of the landing gear 9 as indicated by the crossed-circle in
The aircraft thus turns in a relatively small turning circle about a centre of turning 13 located close to the landing gear 9 on which brakes are applied. The landing gear travels, initially in a forward motion, in a tight circle 14 (the movement of the landing gear has been exaggerated for the sake of clarity). When the aircraft has turned through 180 degrees, the pilot reduces the outermost engine thrust to idle, straightens up the nose wheel and releases the brakes on the landing gear 9.
In braked pivot turns of the prior art, all the wheels on the landing gear 9 are braked during the manoeuvre. This creates a large torque in the leg of the landing gear assembly 9 due to the scrubbing of the tyres on the runway 2. According to the present embodiment of the invention however, only the wheels 19a, 20a on the side of the bogie 17 located closer to the centre of turning 13 are braked. As will now be described with reference to
a shows a manoeuvre in which all four wheels on the bogie are braked,
Referring first to
Referring now to
c shows the loads in a landing gear assembly during a braked pivot manoeuvre in which only the wheels 19a, 20a on the side of the bogie 17 that is closer to the centre of turning 13 are braked (i.e. in accordance with the method of embodiments of the present invention). As in the above-described maneuvers, as the aircraft 1 turns, the braked wheels 19a, 20a are subjected to considerable frictional loading due to the tyres scrubbing on the runway 2. This frictional loading generates a primary torque in the landing gear. The net torque 23 in the leg is approximately 0.5×108 Nmm throughout the time period measured however. This is significantly lower than that in
The skilled man will hence appreciate that performing the method of embodiments of the present invention generates significantly lower torque in the landing gear assembly than performing a braked pivot turns of the prior art. Large aircraft that were previously banned from making such a manoeuvre may thereby be allowed to perform braked pivot turns in accordance with embodiments of the present invention, and hence be able turn in a tight radius.
As shown in
According to a second embodiment of the invention (not shown) the aircraft is provided with a brake control system comprising a control unit, a ground speed receiver and a nose wheel angle receiver. The brake control system also comprises a brake input receiver which receives a signal when the pilot attempts to apply the brakes to the wheels of the landing gear.
The control unit is arranged to receive signals relating to the aircraft speed and the nose wheel angle via the ground speed receiver and a nose wheel angle receiver. The control unit is also arranged to compare the signal received from the ground speed receiver and the signal received from the nose wheel indicator, to parameter reference thresholds stored in a database within the brake control system. In the second embodiment, the aircraft speed is below the threshold value of 20 knots, and the nose wheel angle is greater than the threshold value of 60 degrees from the centre of the fuselage.
During use, the brake input receiver receives a signal due to the pilot applying the brakes. The control unit compares the signals from the receivers to the parameter reference thresholds. In this particular embodiment, the speed and nose wheel angle are outside their respective thresholds. The brake control unit therefore effects application of the brakes to only the wheels on the side of the bogie closer to the centre of turning. The torque in the landing gear leg is thereby maintained at an acceptable level such that relatively little fatigue damage occurs.
Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein. By way of example, certain variations to the above-described embodiments will now be described.
Each landing gear need not comprise four wheels. For example, the landing gear may comprise two wheels (in which case the term ‘bogie’ will be understood to mean the structure at one end of the landing gear leg that is common to both wheels, for example the axle). The landing gear may comprise 6 or more wheels. The steps performed to effect the braked pivot turn need not be made in the order described above. A Jacobs manoeuvre may be effected, rather than the braked pivot turn described in respect of the first embodiment.
Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims.
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|---|---|---|---|
| 0523069.3 | Nov 2005 | GB | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/GB2006/004206 | 11/10/2006 | WO | 00 | 4/25/2008 |
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