Landing gear system for an aircraft and associated aircraft

Abstract

A landing gear system (5) for an aircraft (1) includes a nose landing gear (2) and at least one rear landing gear, the rear landing gear being of bogie beam type and including at least two wheels. The landing gear system is also equipped with a hybrid braking system, which includes at least one friction brake and at least one auxiliary brake that provides energy dissipation by means other than friction. At least one of the wheels of the rear landing gear is equipped with only one or more auxiliary brakes, and at least one of the wheels of the rear landing gear is equipped with only one or more friction brakes. All wheels of the rear landing gear are equipped with at least one auxiliary brake or a friction brake. An aircraft equipped with such a landing gear system.

Description

Technical Field

[0001] This invention relates to landing gear systems for aircraft.

[0002] The present invention also relates to aircraft equipped with such a landing gear system. Background Technology

[0003] In the aviation industry, it is well known to equip aircraft wheels with friction brakes, which are intended to selectively slow down and stop the aircraft when it is moving on the ground or during the landing phase. While effective, friction brakes require periodic replacement of worn components. Furthermore, the friction of these worn components during braking generates particularly polluting dust particles.

[0004] However, climate change is a major concern for many legislative and regulatory bodies around the world. Specifically, numerous countries have already implemented, are implementing, or will implement various restrictions on carbon emissions. In particular, a broad standard applies to both new and currently used aircraft, requiring the implementation of technological solutions to ensure compliance with existing regulations. The civil aviation industry has been mobilized for years to contribute to addressing climate change.

[0005] Technological research has yielded significant improvements in the environmental performance of aircraft. All stakeholders in the field are continuously striving to improve energy efficiency. The applicant will take into account influencing factors at all stages of design and development to obtain aircraft components and products that consume less energy, are more environmentally friendly, and have a milder environmental impact when integrated and used in civil aviation, with the aim of improving the energy efficiency of air transport.

[0006] Therefore, the applicant continuously strives to reduce its climate impact by using benign development and manufacturing methods and processes that minimize greenhouse gas emissions, thereby reducing the environmental footprint of its activities.

[0007] This ongoing research and development effort focuses on: next-generation aircraft engines; making aircraft lighter, particularly through the materials used and lighter onboard equipment; developing the use of propulsion electric technologies; and aviation biofuels as a necessary complement to technological progress. Summary of the Invention

[0008] The present invention aims to provide an aircraft landing gear system and an aircraft that can at least partially overcome the above-mentioned disadvantages.

[0009] To this end, the present invention provides a landing gear system for an aircraft, the landing gear system including a nose landing gear and at least one rear landing gear, the rear landing gear being of bogie beam type and including at least two wheels, the landing gear system also being equipped with a hybrid braking system, the hybrid braking system including at least one friction brake and at least one auxiliary brake providing energy dissipation by means other than friction, at least one of the wheels of the rear landing gear being equipped with only one or more auxiliary brakes, and at least one of the wheels of the rear landing gear being equipped with only one or more friction brakes, and all wheels of the rear landing gear being equipped with at least one auxiliary brake or friction brake.

[0010] Therefore, the aircraft landing gear is equipped not only with at least one friction brake, but also with at least one auxiliary brake to ensure that energy is dissipated by means other than friction.

[0011] With this hybrid braking system, less stress can be applied to at least one friction brake, especially during ground motion or landing phases.

[0012] This limits the pollution of the surrounding air by particles released during friction of the wear elements of one or more friction brakes.

[0013] This also makes it possible to limit any temperature rise in one or more friction brakes that tends to accelerate their aging.

[0014] In this invention, all rear landing gears have at least one wheel that is equipped with only friction brakes or only multiple friction brakes (i.e., at least one wheel without auxiliary brakes).

[0015] For the purposes of this application, the term "landing gear system" refers to the entire system deployed to enable an aircraft to land and subsequently glide on the ground.

[0016] The term "landing gear" refers to each unit of the landing gear system that is connected to the aircraft via landing gear unit legs. The landing gear system thus comprises multiple landing gear units. It should be noted that each landing gear unit can support one or more wheels.

[0017] In this application, the terms "front" and "rear" should be understood along the longitudinal axis passing through the aircraft, with the front of the aircraft being its nose and the rear of the aircraft being its tail.

[0018] For the purposes of this application, the terms “right” and “left” shall be understood relative to the longitudinal axis passing through the aircraft when viewed from the rear of the aircraft when it is parked on the ground, from its tail toward its nose; right and left respectively refer to the two sides of the aircraft.

[0019] Preferably, the rear landing gear is the first landing gear, and the landing gear system includes a second rear landing gear, which is of the bogie beam type and includes at least two wheels, at least one of the wheels of the second landing gear being equipped with only one or more friction brakes.

[0020] Preferably, the number of wheels equipped with friction brakes in the rear landing gear assembly of the aircraft is greater than or equal to the number of wheels equipped with auxiliary brakes in the rear landing gear assembly of the aircraft.

[0021] Optionally, the rear landing gear is the first landing gear, and the landing gear system includes a second rear landing gear, which is of the bogie beam type and includes at least two wheels, at least one of the wheels of the second landing gear being equipped with only one or more friction brakes.

[0022] Optionally, the number of wheels equipped with friction brakes in the rear landing gear assembly of the aircraft is greater than or equal to the number of wheels equipped with auxiliary brakes in the rear landing gear assembly of the aircraft.

[0023] Optionally, at least one of the auxiliary brakes is a magnetic brake.

[0024] Alternatively, the magnetic brake is an eddy current brake.

[0025] Optionally, the landing gear system includes at least three rear landing gears, all of which are bogie beams, namely the center landing gear, the right landing gear, and the left landing gear, wherein the wheels of the right and left landing gear are equipped with only friction brakes, and the wheels of the center landing gear are equipped with only auxiliary brakes.

[0026] Optionally, at least one of the rear landing gear includes at least one bogie beam and at least one first axle extending laterally relative to the bogie beam, and at least one second axle extending laterally relative to the bogie beam, each axle being associated with at least one right wheel and at least one left wheel.

[0027] Optionally, the wheel associated with the first axle is equipped with only an auxiliary brake, and the wheel associated with the second axle is equipped with only a friction brake, or vice versa.

[0028] Optionally, the first axle with the wheel equipped only with an auxiliary brake is arranged in front of the second axle with the wheel equipped only with a friction brake, or the first axle with the wheel equipped only with an auxiliary brake is arranged behind the second axle with the wheel equipped only with a friction brake.

[0029] Alternatively, the wheels on the same side of the landing gear may be equipped with only auxiliary brakes, while the wheels on the other side of the landing gear may be equipped with only friction brakes.

[0030] Alternatively, the wheel equipped with the auxiliary brake may be the right wheel or the left wheel.

[0031] Optionally, the wheel equipped with the friction brake is either the wheel furthest from the longitudinal axis (X) of the aircraft or the wheel closest to the axis.

[0032] The present invention also relates to aircraft including the landing gear system described above. Attached Figure Description

[0033] The invention will be better understood from the following description, which is purely illustrative and not restrictive, and should be read with reference to the accompanying drawings, in which: [ Figure 1 ] Figure 1 This is a simplified top view of an aircraft including a landing gear system according to a first embodiment of the present invention, the landing gear system being shown in dashed lines to enable it to... Figure 1 Seen in; [ Figure 2 ] Figure 2 yes Figure 1 An enlarged front view of one of the landing gears of the aircraft shown; [ Figure 3 ] Figure 3 This is a simplified top view of an aircraft including a landing gear system according to a second embodiment of the present invention, the landing gear system being shown in dashed lines to enable it to... Figure 3 I saw it in the middle. Detailed Implementation

[0034] Now refer to Figure 1 and Figure 2 The aircraft 1 according to the first embodiment is described.

[0035] The aircraft 1 includes an aircraft landing gear system 5, which includes a nose landing gear 2 and two main landing gears, namely a left rear landing gear 3a and a right rear landing gear 3b. The nose landing gear 2 is located under the fuselage 6, in front of the left rear landing gear 3a and in front of the right rear landing gear 3b. The left rear landing gear 3a and the right rear landing gear 3b are located under the left wing 7a and the right wing 7b of the aircraft 1, respectively.

[0036] The nose landing gear 2 includes a single axle 8, which supports two wheels 9. The nose landing gear unit 2 is therefore not a bogie landing gear unit.

[0037] In contrast, both the left rear landing gear 3a and the right rear landing gear 3b are bogie beam types.

[0038] Thus, each of these landing gears 3a, 3b includes a leg that carries a shock absorber assembly, which is connected to the bogie beam, from which the leg extends.

[0039] Each bogie beam includes a main body 10 extending along axis A, which, when the landing gear is deployed, extends parallel to the longitudinal axis X of the aircraft 1 (the axis extending from the tail to the nose of the aircraft 1). The main body 10 has a first sleeve 11 at a first end and a second sleeve 12 extending parallel to the first sleeve 11 at a second end. Furthermore, the two sleeves 11 and 12 extend orthogonally to the main body 10. A first wheel axle 13 extends coaxially through the first sleeve 11, and a second wheel axle 14 extends coaxially through the second sleeve 12. Each wheel axle 13 and 14 carries at least one wheel at each of its ends.

[0040] In this case, both the left rear landing gear 3a and the right rear landing gear 3b have four-wheel bogie beams, such that each axle 13, 14 carries a single wheel at each end.

[0041] The left rear landing gear 3a thus includes a front axle 13 (first axle) that carries the left wheel 15a and the right wheel 15b, and a rear axle 14 (second axle) that carries the left wheel 16a and the right wheel 16b.

[0042] In the same manner, the right rear landing gear 3b thus includes a front axle 17 (first axle) that carries the left wheel 18a and the right wheel 18b, and a rear axle 19 (second axle) that carries the left wheel 20a and the right wheel 20b.

[0043] In addition, the landing gear system 5 is equipped with a hybrid braking system, which includes a friction brake and an auxiliary brake that dissipates energy by means other than friction.

[0044] In a manner known per se, a friction brake comprises both a rotor disc connected to the wheel in question and a stator disc connected to the axle or another part of the associated landing gear. When braking force is desired, at least one actuator (hydraulic and / or electric) presses against a pressure distribution plate, which in turn presses the individual discs against each other in the direction of the end plates. The friction between the rotor disc and the stator disc thereby stops the rotor disc.

[0045] At least one of the discs includes a body, at least one friction liner attached to the body, and / or includes a body that directly forms the friction liner.

[0046] At least one of the plates can therefore be carbon-based and / or metal-based (e.g., made of steel).

[0047] For example, at least one of the discs is metal-based and is equipped with at least one friction liner at at least one end thereto, and / or at least one of the discs is carbon-based and thus forms a friction disc directly (which therefore does not have a friction liner).

[0048] The auxiliary brake is preferably a magnetic brake.

[0049] The auxiliary brake is preferably an eddy current brake.

[0050] Each auxiliary brake thus comprises a stator connected to the axle or another part of the landing gear in question, and a rotor connected to the associated wheel, one carrying a magnetic element (a permanent magnet and / or an electromagnet and / or a combination of both), and the other carrying at least one conductive surface. The rotational motion between the stator and rotor causes said surface to rotate in a magnetic field generated by the magnetic element: this results in eddy currents within said surface, which in turn cause the kinetic energy between the stator and rotor to be converted into heat dissipation, thereby braking the rotor relative to the stator.

[0051] The front landing gear 2 is preferably without brakes.

[0052] Different configurations can be envisioned for the left rear landing gear 3a and the right rear landing gear 3b. In all cases, at least one of the rear landing gears 3a and 3b is equipped with at least one auxiliary brake, and at least one of the rear landing gears 3a and 3b is equipped with at least one friction brake.

[0053] Preferably, the number of wheels equipped with friction brakes on the rear landing gear 3a and 3b of the aircraft is greater than or equal to the number of wheels equipped with auxiliary brakes on the rear landing gear 3a and 3b.

[0054] According to the first configuration, the two wheels 15a and 15b of the front axle 13 of the left rear landing gear 3a and the two wheels 18a and 18b of the front axle 17 of the right rear landing gear 3b are only equipped with auxiliary brakes (i.e., they are not equipped with friction brakes). Furthermore, the two wheels 16a and 16b of the rear axle 14 of the left rear landing gear 3a and the two wheels 20a and 20b of the rear axle 19 of the right rear landing gear 3b are only equipped with friction brakes (i.e., they are not equipped with auxiliary brakes).

[0055] According to the second configuration, the two wheels 16a and 16b of the rear axle 14 of the left rear landing gear 3a and the two wheels 20a and 20b of the rear axle 19 of the right rear landing gear 3b are only equipped with auxiliary brakes (i.e., they are not equipped with friction brakes). Furthermore, the two wheels 15a and 15b of the front axle 13 of the left rear landing gear 3a and the two wheels 18a and 18b of the front axle 17 of the right rear landing gear 3b are only equipped with friction brakes (i.e., they are not equipped with auxiliary brakes).

[0056] According to the third configuration, the two left wheels 15a and 16a of the left rear landing gear 3a and the two left wheels 18a and 20a of the right rear landing gear 3b are only equipped with auxiliary brakes (i.e., they are not equipped with friction brakes). Furthermore, the two right wheels 15b and 16b of the left rear landing gear 3a and the two right wheels 18b and 20b of the right rear landing gear 3b are only equipped with friction brakes (i.e., they are not equipped with auxiliary brakes).

[0057] According to the fourth configuration, the two right wheels 15b and 16b of the left rear landing gear 3a and the two right wheels 18b and 20b of the right rear landing gear 3b are only equipped with auxiliary brakes (i.e., they are not equipped with friction brakes). Furthermore, the two left wheels 15a and 16a of the left rear landing gear 3a and the two left wheels 18a and 20a of the right rear landing gear 3b are only equipped with friction brakes (i.e., they are not equipped with auxiliary brakes).

[0058] According to the fifth configuration, the two right wheels 15b and 16b of the left rear landing gear 3a and the two left wheels 18a and 20a of the right rear landing gear 3b are only equipped with auxiliary brakes (i.e., they are not equipped with friction brakes). Furthermore, the two left wheels 15a and 16a of the left rear landing gear 3a and the two right wheels 18b and 20b of the right rear landing gear 3b are only equipped with friction brakes (i.e., they are not equipped with auxiliary brakes).

[0059] Therefore, an auxiliary brake is provided on the innermost wheel relative to the axis X of aircraft 1.

[0060] According to the sixth configuration, the two left wheels 15a and 16a of the left rear landing gear 3a and the two right wheels 18b and 20b of the right rear landing gear 3b are only equipped with auxiliary brakes (i.e., they are not equipped with friction brakes). Furthermore, the two right wheels 15b and 16b of the left rear landing gear 3a and the two left wheels 18a and 20a of the right rear landing gear 3b are only equipped with friction brakes (i.e., they are not equipped with auxiliary brakes).

[0061] Therefore, an auxiliary brake is provided on the outermost wheel relative to the axis X of aircraft 1.

[0062] In all these configurations, each rear landing gear 3a, 3b has at least one wheel equipped only with a friction brake.

[0063] In all configurations here, the number of wheels equipped with auxiliary brakes on the rear landing gear 3a and 3b is equal to the number of wheels equipped with friction brakes on the rear landing gear 3a and 3b.

[0064] The braking system is preferably configured such that the first group formed by friction brakes and the second group formed by auxiliary brakes can be controlled independently of each other. Thus, it is possible to control all friction brakes together, or all auxiliary brakes together, or, if desired, all brakes together.

[0065] This allows for better control of braking, and in particular, makes it possible to activate only the auxiliary brake if the braking force generated by the auxiliary brake is sufficient during the phase in question.

[0066] Therefore, during taxiing maneuvers, where the speed of aircraft 1 is relatively low and runway traffic may require the activation and deactivation of the brakes when aircraft 1 is in position for takeoff, the auxiliary brakes can be used independently of the friction brakes (to avoid applying the friction brakes). This can have a significant impact on extending the service life of the friction brake components.

[0067] Furthermore, during landing maneuvers, where the speed of aircraft 1 is relatively high, the auxiliary brakes can be used in conjunction with friction brakes and other drags (drag, thrust, etc.) to absorb energy and reduce the force required by other braking systems, and / or achieve a shorter landing distance.

[0068] Now refer to Figure 3 Describes aircraft 1 according to the second embodiment.

[0069] The aircraft 1 includes an aircraft landing gear system 5, which includes a nose landing gear 2 and three rear landing gears: - Central rear landing gear 4, and - Two main rear landing gears, namely the left rear landing gear 3a and the right rear landing gear 3b.

[0070] The central rear landing gear 4 is located below the fuselage 6 of the aircraft 1, behind the nose landing gear unit 2 and in front of the left rear landing gear 3a and the right rear landing gear 3b. The nose landing gear 2 is located below the fuselage 6, in front of the left rear landing gear 3a and the right rear landing gear 3b. The left rear landing gear 3a and the right rear landing gear 3b are located below the left wing 7a and the right wing 7b of the aircraft 1, respectively.

[0071] The nose landing gear 2 includes a single axle 8, which supports two wheels 9. The nose landing gear unit 2 is therefore not a bogie landing gear unit.

[0072] In contrast, the central rear landing gear 4, the left rear landing gear 3a, and the right rear landing gear 3b are all bogie beam type.

[0073] Thus, each of these landing gears 4, 3a, 3b includes a leg that carries a shock absorber assembly, which is connected to the bogie beam, from which the leg extends.

[0074] Each bogie beam includes a main body 10 extending along axis A, which, when the landing gear is deployed, extends parallel to the longitudinal axis X of the aircraft 1 (the axis extending from the tail to the nose of the aircraft 1). The main body 10 has a first sleeve at a first end and a second sleeve extending parallel to the first sleeve at a second end. Furthermore, the two sleeves extend orthogonally to the main body 10. A first wheel axle 13 extends coaxially through the first sleeve, and a second wheel axle 14 extends coaxially through the second sleeve. Each wheel axle 13, 14 carries at least one wheel at each of its ends.

[0075] In this configuration, the central rear landing gear 4, the left rear landing gear 3a, and the right rear landing gear 3b all have four-wheel bogie beams, such that each axle carries a single wheel at each end.

[0076] The left rear landing gear 3a thus includes a front axle 13 (first axle) that carries the right and left wheels and a rear axle 14 (second axle) that carries the right and left wheels.

[0077] In the same manner, the right rear landing gear 3b thus includes a front axle 30 (first axle) that carries the right and left wheels and a rear axle 31 (second axle) that carries the right and left wheels.

[0078] In the same manner, the central rear landing gear 4 thus includes a front axle 32 (first axle) that carries the right and left wheels and a rear axle 33 (second axle) that carries the right and left wheels.

[0079] In addition, the landing gear system 5 is equipped with a hybrid braking system, which includes a friction brake and an auxiliary brake that dissipates energy by means other than friction.

[0080] In a manner known per se, a friction brake comprises both a rotor disc connected to the wheel in question and a stator disc connected to the axle or another part of the associated landing gear unit. When braking force is desired, at least one actuator (hydraulic and / or electric) presses against a pressure distribution plate, which in turn presses the individual discs against each other in the direction of the end plates. The friction between the rotor disc and the stator disc thereby stops the rotor disc.

[0081] At least one of the discs includes a body, at least one friction liner attached to the body, and / or includes a body that directly forms the friction liner.

[0082] At least one of the plates can therefore be carbon-based and / or metal-based (e.g., made of steel).

[0083] For example, at least one of the discs is metal-based and is equipped with at least one friction liner at at least one end thereto, and / or at least one of the discs is carbon-based and thus forms a friction disc directly (which therefore does not have a friction liner).

[0084] The auxiliary brake is preferably a magnetic brake.

[0085] The auxiliary brake is preferably an eddy current brake.

[0086] Each auxiliary brake thus comprises a stator connected to the axle or another part of the landing gear in question, and a rotor connected to the associated wheel, one carrying a magnetic element (a permanent magnet and / or an electromagnet and / or a combination of both), and the other carrying at least one conductive surface. The rotational motion between the stator and rotor causes said surface to rotate in a magnetic field generated by the magnetic element: this results in eddy currents within said surface, which in turn cause the kinetic energy between the stator and rotor to be converted into heat dissipation, thereby braking the rotor relative to the stator.

[0087] The front landing gear 2 is preferably without brakes.

[0088] Different configurations are possible for the right rear landing gear 3b, the left rear landing gear 3a, and the center rear landing gear 4. In all cases, at least one of the rear landing gears 3a, 3b, and 4 is equipped with at least one auxiliary brake, and at least one of the rear landing gears 3a, 3b, and 4 is equipped with at least one friction brake.

[0089] Preferably, the number of wheels equipped with friction brakes on the rear landing gear 3a, 3b, 4 of the aircraft is greater than or equal to the number of wheels equipped with auxiliary brakes on the rear landing gear 3a, 3b, 4.

[0090] For example, all wheels on the center rear landing gear 4 are equipped with only auxiliary brakes (i.e., they are not equipped with friction brakes). In addition, all wheels on the right rear landing gear 3b and all wheels on the left rear landing gear 3a are equipped with only friction brakes (i.e., they are not equipped with auxiliary brakes).

[0091] The number of wheels equipped with auxiliary brakes in the rear landing gear 3a, 3b, and 4 is thus less than the number of wheels equipped with friction brakes in the rear landing gear 3a, 3b, and 4.

[0092] The braking system is preferably configured such that the first group formed by friction brakes and the second group formed by auxiliary brakes can be controlled independently of each other. Thus, it is possible to control all friction brakes together, or all auxiliary brakes together, or, if desired, all brakes together.

[0093] This allows for better control of braking, and in particular, makes it possible to activate only the auxiliary brake if the braking force generated by the auxiliary brake is sufficient during the phase in question.

[0094] Therefore, during taxiing maneuvers, where the speed of aircraft 1 is relatively low and runway traffic may require the activation and deactivation of the brakes when aircraft 1 is in position for takeoff, the auxiliary brakes can be used independently of the friction brakes (to avoid applying the friction brakes). This can have a significant impact on extending the service life of the friction brake components.

[0095] Furthermore, during landing maneuvers, where the speed of aircraft 1 is relatively high, the auxiliary brakes can be used in conjunction with friction brakes and other drags (drag, thrust, etc.) to absorb energy and reduce the force required by other braking systems, and / or achieve a shorter landing distance.

[0096] Of course, the present invention is not limited to the embodiments described, but includes any variations that fall within the scope of the present invention, such as the variations defined in the claims.

[0097] Specifically, the number of landing gear units included in the landing gear system may differ from the number described. The landing gear units may be arranged in a manner different from what is specified.

[0098] The nose landing gear may be equipped with at least one brake. For example, one or more wheels of the nose landing gear may be equipped with friction brakes and / or auxiliary brakes.

[0099] The landing gear system may consist of only the bogie beam landing gear.

[0100] For bogie girder landing gear, it may include more than two axles and / or more than two wheels carried by at least one of the axles. For example, at least one axle may carry four wheels or even six wheels.

[0101] Of course, other configurations besides those described are also possible.

[0102] For example, in the case of two rear landing gears, each comprising four wheels, as in the first embodiment: - The number of wheels equipped with auxiliary brakes on the rear landing gear can be less than the number of wheels equipped with friction brakes on the rear landing gear. For example, each rear landing gear may have only one wheel equipped with an auxiliary brake, while the remaining wheels are equipped with friction brakes; - The number of wheels equipped with auxiliary brakes on the rear landing gear can be greater than the number of wheels equipped with friction brakes on the rear landing gear. For example, each rear landing gear may have only one wheel equipped with a friction brake, while the remaining wheels are equipped with auxiliary brakes. - etc.

[0103] For example, as in the second embodiment, in the case of three rear landing gears: - All front wheels of all rear landing gear may be equipped with one or more auxiliary brakes, and all rear wheels of all rear landing gear may be equipped with one or more friction brakes. - All front wheels of all rear landing gear may be equipped with one or more friction brakes, and all rear wheels of all rear landing gear may be equipped with one or more auxiliary brakes. - All right wheels of all rear landing gear may be equipped with one or more friction brakes, and all left wheels of all rear landing gear may be equipped with one or more auxiliary brakes. - All right wheels of all rear landing gear may be equipped with one or more auxiliary brakes, and all left wheels of all rear landing gear may be equipped with one or more friction brakes. - The number of wheels equipped with auxiliary brakes on the rear landing gear can be less than the number of wheels equipped with friction brakes on the rear landing gear. For example, each rear landing gear may have only one wheel equipped with an auxiliary brake, while the remaining wheels are equipped with friction brakes; - The number of wheels equipped with auxiliary brakes on the rear landing gear can be greater than the number of wheels equipped with friction brakes on the rear landing gear. For example, each rear landing gear may have only one wheel equipped with a friction brake, while the remaining wheels are equipped with auxiliary brakes; - At least one of the right or left landing gear may be equipped with only friction brakes. - etc.

[0104] In all configurations, each rear landing gear will be provided with at least one wheel equipped with one or more friction brakes, and preferably at least one wheel equipped with only one or more friction brakes.

[0105] Preferably, in all configurations, all wheels of all rear landing gear will be equipped with at least one brake.

[0106] Preferably, the braking system will be configured such that the distribution of brakes in the rear landing gear unit is symmetrical about at least one axis (e.g., the longitudinal axis X corresponding to the roll axis, pitch axis, or yaw axis of the aircraft). As an example, it may have a left wheel distribution of the rear landing gear with a first type of brake and a right wheel distribution of the rear landing gear with a second type of brake, or a front wheel distribution of the rear landing gear with a first type of brake and a rear wheel distribution of the rear landing gear with a second type of brake.

[0107] Of course, in all configurations, the braking system must ensure sufficient braking in all envisioned phases, especially during landing.

[0108] At least one of the auxiliary brakes may be a type different from that of a magnetic brake, and may be, for example, a hydraulic brake (e.g., a "retarder" brake) or a compressed air brake (e.g., a "turbine brake" brake). A hybrid braking system may include several types of auxiliary brakes within the same aircraft.

[0109] The auxiliary brake will preferably be a non-contact type. Under no circumstances will the auxiliary brake be a friction brake.

Claims

1. A landing gear system (5) for an aircraft (1), the landing gear system comprising a nose landing gear (2) and at least one rear landing gear, the rear landing gear being of bogie beam type and comprising at least two wheels, the landing gear system further comprising a hybrid braking system comprising at least one friction brake and at least one auxiliary brake providing energy dissipation by means other than friction, at least one of the wheels of the rear landing gear being equipped with only one or more auxiliary brakes, and at least one of the wheels of the rear landing gear being equipped with only one or more friction brakes, and all wheels of the rear landing gear being equipped with at least one auxiliary brake or friction brake.

2. The landing gear system (5) according to claim 1, characterized in that, The rear landing gear is the first landing gear, and the landing gear system includes a second rear landing gear, which is a bogie beam type and includes at least two wheels, at least one of the wheels of the second landing gear being equipped with only one or more friction brakes.

3. The landing gear system (5) according to any one of claims 1 or 2, characterized in that, The number of wheels equipped with friction brakes in the rear landing gear assembly of the aircraft (1) is greater than or equal to the number of wheels equipped with auxiliary brakes in the rear landing gear assembly of the aircraft.

4. The landing gear system (5) according to any one of the preceding claims, characterized in that, At least one of the auxiliary brakes is a magnetic brake.

5. The landing gear system (5) according to the preceding claim, characterized in that, The magnetic brake is an eddy current brake.

6. The landing gear system (5) according to any one of the preceding claims, characterized in that, It includes at least three rear landing gears, all of which are bogie beam type, namely the center landing gear (4), the right landing gear (3b) and the left landing gear (3a), wherein the wheels of the right landing gear and the left landing gear are equipped with only friction brakes, and the wheels of the center landing gear are equipped with only auxiliary brakes.

7. The landing gear system (5) according to any one of claims 1 to 6, characterized in that, At least one of the rear landing gear (3a, 3b, 4) includes at least one bogie beam and at least one first axle extending laterally relative to the bogie beam and at least one second axle extending laterally relative to the bogie beam, each axle being associated with at least one right wheel and at least one left wheel.

8. The landing gear system (5) according to claim 7, characterized in that, The wheel associated with the first axle is equipped with only an auxiliary brake, and the wheel associated with the second axle is equipped with only a friction brake, or vice versa.

9. The landing gear system (5) according to claim 8, characterized in that, The first axle with a wheel equipped only with an auxiliary brake is arranged in front of the second axle with a wheel equipped only with a friction brake, or the first axle with a wheel equipped only with an auxiliary brake is arranged behind the second axle with a wheel equipped only with a friction brake.

10. The landing gear system (5) according to claim 7, characterized in that, The wheels on the same side of the landing gear are equipped with only auxiliary brakes, while the wheels on the other side of the landing gear are equipped with only friction brakes.

11. An aircraft, characterized in that, Includes the landing gear system (5) according to any one of the preceding claims.

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