Airplane ground deceleration system, method, airplane landing gear and airplane

Abstract

The application relates to an airplane ground deceleration system, method, airplane landing gear and airplane. The system comprises: an electromagnetic coil installed on an airplane landing gear support column, used for generating an electromagnetic field around the electromagnetic coil after being electrified; a power supply controller located in an airplane cabin, used for adjusting the current in the electromagnetic coil; and a metal pipe network layer laid under an airport runway, used for generating an induced current; wherein the electromagnetic coil is electrified and generates an electromagnetic field, the electromagnetic field also moves forward when the airplane moves forward after landing, the metal pipes in the metal pipe network layer cut the magnetic field lines of the electromagnetic field, due to the existence of an induced electromotive force, there is an induced current in the metal pipe network layer, the metal pipe network layer has a certain resistance, due to the thermal effect of the resistance, the kinetic energy of the airplane is converted into electric energy and then into heat energy and heat dissipation, so that the airplane is ground decelerated. The application can achieve the following beneficial technical effects: the airplane is ground decelerated by relying on a new type of braking mode.

Description

TECHNICAL FIELD

[0001] The present application relates to an airplane ground deceleration system, method, airplane landing gear and airplane, and belongs to the field of airplane brake systems. BACKGROUND

[0002] As the main means of transportation today, airplanes have brake systems for deceleration and braking. Airplane brake systems are mostly hydraulic brake systems or electric brake systems. The working principle is that the brake device is driven by hydraulic pressure or electricity to make the brake disc rub, converting the kinetic energy of the airplane into heat energy to achieve the purpose of braking. The control aspect adjusts the hydraulic actuation pressure or adjusts the motor actuator input current to adjust the motor speed to achieve the purpose of anti-skid and anti-lock.

[0003] The airplane brake system has inherent drawbacks. For example, for airplane hydraulic brake systems, inherent problems such as leakage, poor anti-pollution ability, relatively low dispatch rate, and complex maintenance have not been solved. Electric brake systems have many components, complex systems, and low reliability. Both hydraulic brakes and electric brakes require friction brake discs to convert kinetic energy into heat energy.

[0004] Among them, the airplane friction material brake disc has the following shortcomings:

[0005] The brake disc, as a consumable, has huge wear and tear, and needs to be replaced every 200-600 landing gear cycles, increasing the use cost;

[0006] The production process of the friction material is complex, and the production cycle is long. For example, the production cycle of a pair of carbon-carbon composite brake discs is at least 3 months;

[0007] The powder metallurgy / metal brake disc is heavy, easy to stick at high temperatures, and prone to cracks and chipping;

[0008] The carbon-carbon composite material has low strength, large volume, small static friction coefficient, and complex process and high cost. SUMMARY

[0009] An object of the present application is to provide an airplane ground deceleration system that can overcome at least some of the deficiencies of the prior art and can achieve ground deceleration of an airplane by relying on a new braking mode without major changes to the main structure of the airplane landing gear.

[0010] The above object of the present application is achieved by an airplane ground deceleration system, which comprises:

[0011] An electromagnetic coil is installed on the airplane landing gear strut for generating an electromagnetic field around it after being energized;

[0012] a power controller, located in the aircraft cabin, for regulating the current in the electromagnetic coil;

[0013] a metallic pipe network layer, laid under the airport runway, for generating an induced current, preventing the aircraft from taxiing forward;

[0014] wherein the electromagnetic coil is energized and generates an electromagnetic field, which also moves forward when the aircraft moves forward after landing, the metal pipes in the metallic pipe network layer cut the magnetic field lines of the electromagnetic field, generating an induced electromotive force due to electromagnetic induction, and due to the presence of the induced electromotive force, an induced current will be generated in the metallic pipe network layer, and the metallic pipe network layer has a certain resistance, due to the thermal effect of the resistance, the kinetic energy of the aircraft is converted into electrical energy and then into heat energy and heat dissipation, thereby slowing down the aircraft on the ground.

[0015] According to the above technical solution, the aircraft ground deceleration system of the present application can achieve the following beneficial technical effects: it can slow down the aircraft on the ground by relying on a new braking mode without making major changes to the main structure of the aircraft landing gear.

[0016] Preferably, the induced current in the metallic pipe network layer generates a reverse electromagnetic field, hindering the forward movement of the electromagnetic coil, thereby generating resistance to the aircraft landing gear strut and slowing down the aircraft on the ground.

[0017] According to the above technical solution, the aircraft ground deceleration system of the present application can achieve the following beneficial technical effects: it can further slow down the aircraft on the ground.

[0018] Preferably, the aircraft ground deceleration system further comprises a control unit located in the aircraft cabin for calculating the required current for deceleration and controlling the power controller to regulate the current in the electromagnetic coil.

[0019] According to the above technical solution, the aircraft ground deceleration system of the present application can achieve the following beneficial technical effects: by adjusting the current in the electromagnetic coil, it can appropriately adjust the deceleration rate of the aircraft.

[0020] Preferably, the aircraft ground deceleration system further comprises a cooling system for cooling the metallic pipe network layer.

[0021] According to the above technical solution, the aircraft ground deceleration system of the present application can achieve the following beneficial technical effects: it can prevent the metal pipes in the metallic pipe network layer from being burned out due to persistent heating.

[0022] Preferably, the distance from the electromagnetic coil to the metallic pipe network layer depends on the size of the aircraft wheels.

[0023] According to the technical scheme, the aircraft ground deceleration system can more favorably adjust the aircraft deceleration rate through the appropriate distance between the electromagnetic coil and the metal pipe network layer.

[0024] The above object of the present application is also achieved by an aircraft ground deceleration method, which comprises:

[0025] When the aircraft deceleration function is activated, the electromagnetic coil installed on the aircraft landing gear strut is electrified to generate an electromagnetic field;

[0026] When the aircraft moves forward after landing, the electromagnetic field also moves forward, the metal conduit in the metal pipe network layer laid under the airport runway cuts the magnetic field lines of the electromagnetic field, an induced electromotive force is generated due to electromagnetic induction, and due to the existence of the induced electromotive force, an induced current will exist in the metal pipe network layer, and the metal pipe network layer has a certain resistance, and due to the thermal effect of the resistance, the kinetic energy of the aircraft is converted into electrical energy and then into heat energy and heat dissipation, thereby decelerating the aircraft on the ground.

[0027] The current in the electromagnetic coil is adjusted through the power supply controller located in the aircraft cabin, so as to adjust the deceleration rate of the aircraft.

[0028] According to the technical scheme, the aircraft ground deceleration method can achieve the following beneficial technical effects: the aircraft can be decelerated on the ground by relying on a new braking mode without making major changes to the main structure of the aircraft landing gear.

[0029] Preferably, the induced current in the metal pipe network layer generates a reverse electromagnetic field, which hinders the forward movement of the electromagnetic coil, thereby generating resistance to the aircraft landing gear strut and decelerating the aircraft on the ground.

[0030] According to the technical scheme, the aircraft ground deceleration method can achieve the following beneficial technical effects: the aircraft can be further decelerated on the ground.

[0031] Preferably, the aircraft ground deceleration method further comprises:

[0032] Before the aircraft lands, the deceleration rate of the aircraft is selected in the air, and the power supply controller is turned on, at which time the aircraft deceleration function is in a standby state.

[0033] After the aircraft lands, the control unit located in the aircraft cabin judges the aircraft grounding state based on the landing gear grounding signal; if the aircraft is grounded, the aircraft deceleration function is activated, and the control unit outputs a deceleration instruction; if the aircraft is not grounded, the aircraft deceleration function is not activated, and the control unit does not output a deceleration instruction.

[0034] According to the technical scheme, the aircraft ground deceleration method can activate the aircraft deceleration function at appropriate time, and timely realize the ground deceleration of the aircraft.

[0035] Preferably, the aircraft ground deceleration method further comprises: cooling the metal pipe network layer by the cooling system when the aircraft deceleration function is activated.

[0036] According to the technical scheme, the aircraft ground deceleration method can prevent the metal pipe network layer from being burnt by long-term heating.

[0037] Preferably, the distance between the electromagnetic coil and the metal pipe network layer depends on the size of the aircraft wheel.

[0038] According to the technical scheme, the aircraft ground deceleration method can more advantageously adjust the aircraft deceleration rate by the appropriate distance between the electromagnetic coil and the metal pipe network layer.

[0039] Preferably, when the aircraft deceleration function is activated, the control unit controls the power controller to adjust the current in the electromagnetic coil according to the selected aircraft deceleration rate.

[0040] When the actual aircraft deceleration rate is lower than the selected deceleration rate, the control unit outputs an instruction to increase the current; when the actual aircraft deceleration rate is higher than the selected deceleration rate, the control unit outputs an instruction to decrease the current.

[0041] According to the technical scheme, the aircraft ground deceleration method can appropriately adjust the aircraft deceleration rate by adjusting the current in the electromagnetic coil.

[0042] Preferably, the aircraft ground deceleration method further comprises: when the aircraft is lower than a certain speed, the control unit outputs an instruction to close the deceleration function.

[0043] According to the technical scheme, the aircraft ground deceleration method can further reduce the aircraft operation cost by timely closing the deceleration function.

[0044] The above object of the present application is also achieved by an aircraft landing gear, which comprises an electromagnetic coil, the electromagnetic coil is installed on the aircraft landing gear strut, and is used to generate an electromagnetic field around the electromagnetic coil after being powered on.

[0045] The electromagnetic coil is electrified to generate an electromagnetic field, and the electromagnetic field moves forward when the airplane moves forward after landing, the metal pipe network layer in the metal pipe network layer under the airport runway cuts the magnetic field line of the electromagnetic field, and an induced electromotive force is generated due to electromagnetic induction, and due to the existence of the induced electromotive force, an induced current exists in the metal pipe network layer, and due to the heat effect of the resistance, the kinetic energy of the airplane is converted into electric energy and then into heat energy and is dissipated to heat, thereby slowing down the airplane on the ground.

[0046] The current in the electromagnetic coil can be adjusted.

[0047] According to the above technical solution, the aircraft landing gear can achieve the following beneficial technical effects: under the premise that the main structure of the aircraft landing gear is not changed significantly, the aircraft is slowed down on the ground by relying on a new braking mode.

[0048] Preferably, the induced current in the metal pipe network layer generates a reverse electromagnetic field, which hinders the forward movement of the electromagnetic coil, thereby generating resistance to the aircraft landing gear strut and slowing down the aircraft on the ground.

[0049] According to the above technical solution, the aircraft landing gear can achieve the following beneficial technical effects: further slowing down the aircraft on the ground.

[0050] The above object of the application is also achieved by an aircraft, which comprises:

[0051] The aircraft landing gear according to any one of the preceding aspects; and

[0052] A power supply controller, which is located in the aircraft cabin and is used to adjust the current in the electromagnetic coil.

[0053] According to the above technical solution, the aircraft can achieve the following beneficial technical effects: under the premise that the main structure of the aircraft landing gear is not changed significantly, the aircraft is slowed down on the ground by relying on a new braking mode.

[0054] Preferably, the aircraft further comprises: a control unit, which is located in the aircraft cabin and is used to calculate the required current for deceleration and control the power supply controller to adjust the current in the electromagnetic coil.

[0055] According to the above technical solution, the aircraft can achieve the following beneficial technical effects: by adjusting the current in the electromagnetic coil, the deceleration rate of the aircraft can be appropriately adjusted. BRIEF DESCRIPTION OF DRAWINGS

[0056] Figure 1 is a schematic diagram of an aircraft ground deceleration system according to an embodiment of the application;

[0057] Figure 2 is a schematic diagram of an aircraft ground deceleration system according to an embodiment of the invention;

[0058] Figure 3 is a parametric diagram of an aircraft ground deceleration system according to an embodiment of the invention.

[0059] List of reference signs

[0060] 1. electromagnetic coil

[0061] 2. power supply controller

[0062] 4. airport runway

[0063] 5. metallic mesh layer

[0064] 6. cooling system DETAILED DESCRIPTION

[0065] The specific embodiments of the present invention will now be described in detail with specific reference being made to the figures. It is noted that in the description of embodiments specific details are set forth in order to provide a thorough understanding of the embodiments. However, it will be apparent to one skilled in the art that the present invention can be practiced without specific details given. In other instances, well-known methods, procedures, components, and networks have not been described in detail so as not to unnecessarily obscure aspects of the present invention.

[0066] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and / or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0067] Figure 1 is a schematic diagram of an airplane ground deceleration system according to an embodiment of the present application; Figure 2 is a schematic diagram of an airplane ground deceleration system according to an embodiment of the present application; Figure 3 is a parameter diagram of an airplane ground deceleration system according to an embodiment of the present application.

[0068] As shown in Figures 1 to 3 , according to an embodiment of the present application, the airplane ground deceleration system comprises:

[0069] An electromagnetic coil 1, which is installed on the airplane landing gear strut, is used to generate an electromagnetic field around it after being electrified;

[0070] A power supply controller 2, which is located in the airplane cabin, is used to adjust the current in the electromagnetic coil 1;

[0071] A metal pipe network layer 5, which is laid under the airport runway 4 (the carrier of airplane landing deceleration), is used to generate induced current to prevent the airplane from taxiing forward;

[0072] Wherein, the electromagnetic coil 1 is electrified and generates an electromagnetic field, when the airplane moves forward after landing, the electromagnetic field also moves forward, the metal pipes in the metal pipe network layer 5 cut the magnetic field lines of the electromagnetic field, due to electromagnetic induction, an induced electromotive force is generated, due to the existence of the induced electromotive force, there will be induced current in the metal pipe network layer 5, and the metal pipe network layer 5 has a certain resistance, due to the heat effect of the resistance, the kinetic energy of the airplane is converted into electrical energy and then into heat energy and heat dissipation, thereby decelerating the airplane on the ground.

[0073] According to the above technical solution, the airplane ground deceleration system of the present application can achieve the following beneficial technical effects: it can realize the ground deceleration of the airplane by relying on a new type of braking mode (not relying on the friction brake disc) without making major changes to the main structure of the airplane landing gear.

[0074] Specifically, when the electromagnetic coil 1 on the landing gear strut is electrified, an electromagnetic field will be generated around the electromagnetic coil 1, the strength of the generated electromagnetic field can be calculated according to the Biot-Savart law, and the electromagnetic field strength is proportional to the number of turns N, the cross-sectional area S and the current I of the electromagnetic coil.

[0075] The electromagnetic field continuously spreads outward and penetrates the metal pipe network layer 5 underground, and the magnetic flux in the metal pipe network layer 5 is proportional to the electromagnetic field strength and inversely proportional to the distance D from the electromagnetic coil 1 to the metal pipe network layer 5.

[0076] When the plane moves forward after landing, the electromagnetic field also moves forward, the metal pipes in the metal pipe network layer 5 cut the magnetic field lines of the electromagnetic field, and an induced electromotive force is generated due to electromagnetic induction, the induced electromotive force is proportional to the rate of change of the magnetic flux in the metal pipe network layer 5, that is, proportional to the speed V of the plane and the magnetic flux in the metal pipe network layer 5.

[0077] Due to the existence of the induced electromotive force, there will be an induced current in the metal pipe network layer 5, and the metal pipe network layer 5 has a certain resistance. Due to the thermal effect of the resistance, the kinetic energy of the plane is converted into electrical energy and then into heat energy and heat dissipation, thereby slowing down the plane on the ground.

[0078] In some embodiments, as shown in Figures 1 to 3 The induced current in the metal pipe network layer 5 generates a reverse electromagnetic field, which hinders the forward movement of the electromagnetic coil 1, thereby generating resistance to the landing gear strut of the plane and slowing down the plane on the ground. According to the above technical solution, the aircraft ground deceleration system of the present application can achieve the following beneficial technical effects: further slowing down the plane on the ground.

[0079] Specifically, according to Lenz's law, the magnetic field generated by the induced current always hinders the change of the magnetic flux that causes the induced current. During the deceleration process after the plane lands, the metal pipe network layer below the runway is divided into two regions, A region and B region, with the landing gear strut as the boundary. The A region is the region in front of the landing gear strut, and the B region is the region behind the landing gear strut. As shown in Figure 2 When the plane moves forward after landing, the electromagnetic field generated by the electromagnetic coil on the landing gear in the A region will increase, according to Lenz's law, the closed metal pipe network in the A region generates an electromagnetic field that reduces the magnetic flux, that is, an electromagnetic field opposite to the original magnetic field direction, that is, the N pole of the magnetic field points to the ground, and the same polarity repels each other, at this time the A region magnetic field hinders the plane to move forward; similarly, according to Lenz's law, when the plane moves forward after landing, the closed metal pipe network in the B region will generate an electromagnetic field that increases the magnetic flux, that is, an electromagnetic field consistent with the original magnetic field direction, that is, the N pole of the magnetic field points to the ground, and the different polarity attracts each other, at this time the B region magnetic field also hinders the plane to move forward.

[0080] The magnetic field strength of the reverse electromagnetic field is proportional to the induced current, which hinders the forward movement of the electromagnetic coil 1 on the plane strut, generates resistance to the landing gear strut of the plane, and slows down the plane on the ground until the plane stops moving forward, achieving the purpose of converting the kinetic energy of the plane into electrical energy and then into heat energy and heat dissipation, thereby slowing down the plane on the ground.

[0081] In summary, the generated resistance of the aircraft ground deceleration system is proportional to the aircraft movement speed V, the electromagnetic coil turns N, the cross-sectional area S and the current I, and is inversely proportional to the distance D from the electromagnetic coil to the metal pipe network layer. Since the electromagnetic coil turns N, the cross-sectional area S and the distance D from the electromagnetic coil to the metal pipe network layer are determined, when the aircraft lands on the airport runway at a certain speed, only the current I needs to be adjusted to control the deceleration rate of the aircraft.

[0082] In some embodiments, as shown in Figures 1 to 3 The aircraft ground deceleration system further comprises a control unit (not shown) located in the aircraft cabin, connected to the power supply controller 2, for calculating the required current for deceleration and controlling the power supply controller 2 to adjust the current in the electromagnetic coil 1. According to the above technical solution, as shown in Figures 1 to 3 The aircraft ground deceleration system of the present application has the following beneficial technical effects: by adjusting the current in the electromagnetic coil 1, the aircraft deceleration rate can be appropriately adjusted.

[0083] In some embodiments, as shown in Figures 1 to 3 The aircraft ground deceleration system further comprises a cooling system 6 (for example, a water cooling system) for cooling the metal pipe network layer 5. According to the above technical solution, the aircraft ground deceleration system of the present application has the following beneficial technical effects: it can prevent the metal pipes in the metal pipe network layer 5 from being burned out due to persistent heating.

[0084] In some embodiments, as shown in Figures 1 to 3 The distance from the electromagnetic coil 1 to the metal pipe network layer 5 depends on the size of the aircraft wheel. According to the above technical solution, the aircraft ground deceleration system of the present application has the following beneficial technical effects: by appropriately adjusting the distance from the electromagnetic coil 1 to the metal pipe network layer 5, the aircraft deceleration rate can be more advantageously adjusted.

[0085] Specifically, the size of the aircraft wheel is usually divided into three types: the diameter of the wheel of a branch line aircraft is about 19 inches, the diameter of the wheel of a trunk line aircraft is about 20 inches, and the diameter of the wheel of a long-range passenger aircraft is about 23 inches. In some embodiments, taking the trunk line aircraft as an example, since the diameter of the wheel of the trunk line aircraft is about 20 inches, plus the thickness of the wheel tire is about 1-2 inches, the total size of the wheel of the trunk line aircraft is about 21-22 inches, which is about 0.53-0.56 meters in metric units.

[0086] Generally, the distance between the lower end of the electromagnetic coil 1 and the upper surface of the airport runway 4 is approximately 20% to 50% of the overall wheel size. This is because if the lower end of the electromagnetic coil 1 is installed too low, it is easily affected by dust and debris kicked up from the runway; if it is installed too high, the installation space becomes too limited, making it impossible to install a sufficient number of coil turns. Therefore, for mainline aircraft, the distance between the lower end of the electromagnetic coil 1 and the upper surface of the airport runway 4 is approximately 0.1 to 0.3 meters.

[0087] The distance D from the electromagnetic coil 1 to the metal conduit layer 5 is approximately equal to the distance from the lower end of the electromagnetic coil 1 to the upper surface of the airport runway 4, plus the laying depth of the metal conduit layer 5. The laying depth of the metal conduit layer 5 is related to the thickness of the airport runway. Specifically, the total thickness of the airport runway is approximately 1.2 meters, including approximately 0.4 meters of concrete, approximately 0.3 meters of lean concrete, and approximately 0.5 meters of rammed earth. The metal conduit layer 5 is typically laid beneath the 0.4-meter-thick concrete layer. Therefore, for mainline aircraft, the distance D from the electromagnetic coil 1 to the metal conduit layer 5 is approximately 0.5 to 0.8 meters.

[0088] In some embodiments, such as Figures 1 to 3 As shown, an iron core can be inserted into the electromagnetic coil 1 to increase the magnetic field strength generated by the electromagnetic coil 1. In some embodiments, such as Figures 1 to 3 As shown, the landing gear strut can be inserted into the electromagnetic coil 1 to increase the magnetic field strength. In some embodiments, such as Figures 1 to 3 As shown, the installation position of electromagnetic coil 1 should be as close to the ground as possible (i.e., airport runway 4). For single-wheel landing gear, electromagnetic coil 1 can be installed on the landing gear strut; for multi-wheel trolley-type landing gear with two or more wheels, electromagnetic coil 1 can be installed at the center of the trolley-type landing gear wheel axle.

[0089] In some embodiments, the number of electromagnetic coils 1 may be selected to be installed depending on the weight of the aircraft. In some embodiments, such as Figures 1 to 3 As shown, the installation direction of electromagnetic coil 1 should be such that the magnetic field generated by electromagnetic coil 1 passes through the metal pipe network layer 5 perpendicularly, so as to ensure that the magnetic flux passing through the metal pipe network layer 5 is as large as possible.

[0090] In some embodiments, the aircraft landing gear strut may have multiple fastening holes. Multiple fasteners are engaged in the corresponding fastening holes after securing the electromagnetic coil 1, thereby securely mounting the electromagnetic coil 1 on the aircraft landing gear strut. For example, the multiple fastening holes may be arranged in 2N rows, where N is the number of turns of the electromagnetic coil. That is, every two rows (located on the upper and lower sides of each turn of the electromagnetic coil) of fastening holes and corresponding fasteners are used to secure one turn of the electromagnetic coil.

[0091] In some embodiments, the laying of the metal pipe network layer 5 can be selected to be modular installation, i.e. to produce and manufacture modular runway blocks with the metal pipe network layer; the runway block is composed of a runway section and a metal pipe network layer section laid under the runway section. A plurality of runway blocks are formed into an airport runway 4 in accordance with the standard requirements of the airport runway. In some embodiments, the metal pipes in the metal pipe network layer 5 are closed pipelines with electrically conductive properties. In order to ensure the consistency of the induced electromotive force generated by electromagnetic induction, the metal pipe network layer sections of each runway block should be consistent.

[0092] In some embodiments, as shown in Figures 1 to 3 , the cooling system 6 is laid under the metal pipe network layer 5 for cooling the metal pipe network layer 5, and the cooling system 6 includes but is not limited to a water cooling system.

[0093] It is worth noting that the size of the single closed pipeline in the metal pipe network layer 5 will affect the deceleration performance of the entire system, and the size of the single closed pipeline can be determined by experiments to achieve the best deceleration performance.

[0094] As shown in Figures 1 to 3 , according to an embodiment of the present application, the aircraft ground deceleration method comprises:

[0095] When the aircraft deceleration function is activated, the electromagnetic coil 1 installed on the aircraft landing gear strut is energized and generates an electromagnetic field;

[0096] When the aircraft moves forward after landing, the electromagnetic field also moves forward, and the metal pipes in the metal pipe network layer 5 laid under the airport runway 4 cut the magnetic field lines of the electromagnetic field, and an induced electromotive force is generated due to electromagnetic induction. Due to the existence of the induced electromotive force, there will be an induced current in the metal pipe network layer 5, and the metal pipe network layer 5 has a certain resistance. Due to the thermal effect of the resistance, the kinetic energy of the aircraft is converted into electrical energy and then into heat energy and heat dissipation, thereby decelerating the aircraft on the ground;

[0097] By adjusting the current in the electromagnetic coil 1 through the power supply controller 2 located in the aircraft cabin, the deceleration rate of the aircraft can be adjusted.

[0098] According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: under the premise that the main structure of the aircraft landing gear is not changed significantly, the aircraft can be decelerated on the ground by relying on a new type of braking mode.

[0099] In some embodiments, as shown in Figures 1 to 3 , the induced current in the metal pipe network layer 5 will generate a reverse electromagnetic field, which will hinder the forward movement of the electromagnetic coil 1, thereby generating resistance to the aircraft landing gear strut and decelerating the aircraft on the ground. According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: further decelerating the aircraft on the ground.

[0100] In some embodiments, as shown in Figures 1 to 3 the aircraft ground deceleration method further comprises: before the aircraft lands, selecting a deceleration rate of the aircraft in the air, turning on the power controller 2, at this time the aircraft deceleration function is in a standby state; after the aircraft lands, the control unit located in the cabin of the aircraft judges the grounding state of the aircraft based on the landing gear grounding signal; if the aircraft is grounded, the aircraft deceleration function is activated, and the control unit outputs a deceleration instruction; if the aircraft is not grounded, the aircraft deceleration function is not activated, and the control unit does not output a deceleration instruction. According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: the aircraft deceleration function can be activated at the appropriate time, and the aircraft can be timely decelerated on the ground.

[0101] In some embodiments, as shown in Figures 1 to 3 the aircraft ground deceleration method further comprises: when the aircraft deceleration function is activated, cooling the metal pipe network layer 5 through the cooling system 6. According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: it can prevent the metal pipes in the metal pipe network layer 5 from being burned out due to persistent heating.

[0102] In some embodiments, as shown in Figures 1 to 3 the distance from the electromagnetic coil 1 to the metal pipe network layer 5 depends on the size of the aircraft wheels. According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: by adjusting the distance from the electromagnetic coil 1 to the metal pipe network layer 5, the aircraft deceleration rate can be more advantageously adjusted.

[0103] In some embodiments, as shown in Figures 1 to 3 when the aircraft deceleration function is activated, the control unit controls the power controller 2 to adjust the current in the electromagnetic coil 1 according to the selected aircraft deceleration rate; when the actual aircraft deceleration rate is lower than the selected deceleration rate, the control unit outputs an instruction to increase the current; when the actual aircraft deceleration rate is higher than the selected deceleration rate, the control unit outputs an instruction to decrease the current. According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: by adjusting the current in the electromagnetic coil 1, the aircraft deceleration rate can be appropriately adjusted.

[0104] In some embodiments, a typical control unit should be equipped with a PID algorithm or other control algorithm similar to but not limited to PID algorithm or other control algorithm for self-adaptive adjustment of the current.

[0105] In some embodiments, as shown in Figures 1 to 3 the aircraft ground deceleration method further comprises: when the aircraft is below a certain speed, the control unit outputs a deceleration function shutdown instruction. According to the above technical solution, the aircraft ground deceleration method of the present application can achieve the following beneficial technical effects: by timely shutting down the deceleration function, the operating cost of the aircraft can be further reduced.

[0106] As Figures 1 to 3 shown, according to an embodiment of the present application, the aircraft landing gear comprises an electromagnetic coil 1, which is installed on the aircraft landing gear strut and used to generate an electromagnetic field around it after being electrified;

[0107] Wherein, the electromagnetic coil 1 is electrified and generates an electromagnetic field, when the aircraft moves forward after landing, the electromagnetic field also moves forward, the metal conduit in the metal pipe network layer 5 laid under the airport runway 4 cuts the magnetic field lines of the electromagnetic field, and the induced electromotive force is generated due to electromagnetic induction, and due to the existence of the induced electromotive force, there will be an induced current in the metal pipe network layer 5, and the metal pipe network layer 5 has a certain resistance, due to the thermal effect of the resistance, the kinetic energy of the aircraft is converted into electrical energy and then into heat energy and heat dissipation, thereby slowing down the aircraft on the ground;

[0108] Wherein, the current in the electromagnetic coil 1 when electrified can be adjusted.

[0109] According to the above technical solution, the aircraft landing gear of the present application can achieve the following beneficial technical effects: under the premise that the main structure of the aircraft landing gear is not changed significantly, relying on a new braking mode, the aircraft can be slowed down on the ground.

[0110] In some embodiments, as Figures 1 to 3 shown, the induced current in the metal pipe network layer 5 will generate a reverse electromagnetic field, which will hinder the forward movement of the electromagnetic coil 1, thereby generating resistance to the aircraft landing gear strut and slowing down the aircraft on the ground. According to the above technical solution, the aircraft landing gear of the present application can achieve the following beneficial technical effects: further slowing down the aircraft on the ground.

[0111] As Figures 1 to 3 shown, according to an embodiment of the present application, the aircraft comprises:

[0112] The aircraft landing gear of any of the preceding aspects; and

[0113] A power supply controller 2, which is located in the aircraft cabin and used to adjust the current in the electromagnetic coil 1.

[0114] According to the above technical solution, the aircraft of the present application can achieve the following beneficial technical effects: under the premise that the main structure of the aircraft landing gear is not changed significantly, relying on a new braking mode, the aircraft can be slowed down on the ground.

[0115] In some embodiments, as Figures 1 to 3As shown, the aircraft further comprises a control unit located in the aircraft cabin for calculating the current required for deceleration and controlling the power controller 2 to adjust the current in the electromagnetic coil 1. According to the above technical scheme, the aircraft of the present application can have the following beneficial technical effects: by adjusting the current in the electromagnetic coil 1, the aircraft deceleration rate can be appropriately adjusted.

[0116] Compared with the prior art, the technical scheme of the present application has one or more of the following advantages:

[0117] (1) The electromagnetic brake device is used to replace the traditional hydraulic brake and the electric brake which need to use brake discs, so that the aircraft dispatch rate can be increased and the operation cost of the aircraft can be reduced;

[0118] (2) The problem of hydraulic leakage is solved, and the risk of fire is avoided;

[0119] (3) The traditional brake system brake disc will generate dust in the friction process, pollute the hydraulic energy system, affect the brake efficiency, and pollute the environment. The electromagnetic brake device can overcome such problems.

[0120] The specific embodiments of the present application are described above, but those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present application, and those skilled in the art can make various modifications on the basis of the above disclosure without departing from the scope of the present application.

Claims

1. An aircraft ground deceleration system, comprising: an electromagnetic coil mounted on an aircraft landing gear strut for generating an electromagnetic field around it when energized; a power supply controller located in the aircraft cabin for regulating the current in the electromagnetic coil; a metal pipe network layer laid under the airport runway for generating induced current to prevent the aircraft from taxiing forward; wherein the electromagnetic coil is energized and generates an electromagnetic field, when the aircraft moves forward after landing, the electromagnetic field also moves forward, the metal pipes in the metal pipe network layer cut the magnetic field lines of the electromagnetic field, and due to electromagnetic induction, an induced electromotive force is generated, and due to the existence of the induced electromotive force, there will be induced current in the metal pipe network layer, and the metal pipe network layer has a certain resistance, due to the thermal effect of the resistance, the kinetic energy of the aircraft is converted into electrical energy, and then into thermal energy and heat dissipation, thereby decelerating the aircraft on the ground; wherein the induced current in the metal pipe network layer generates an electromagnetic field, wherein the metal pipe network layer under the runway is divided into a front landing gear strut area and a rear landing gear strut area, the front landing gear strut area generates an electromagnetic field opposite to the original magnetic field direction of the electromagnetic coil, hindering the aircraft from advancing, and the rear landing gear strut area generates an electromagnetic field consistent with the original magnetic field direction of the electromagnetic coil, also hindering the aircraft from advancing.

2. The aircraft ground deceleration system of claim 1, wherein, The aircraft ground deceleration system further comprises a control unit located in the aircraft cabin for calculating the required current for deceleration and controlling the power supply controller to regulate the current in the electromagnetic coil.

3. The aircraft ground deceleration system of claim 1, wherein, The aircraft ground deceleration system further comprises a cooling system for cooling the metal pipe network layer.

4. The aircraft ground deceleration system of claim 1, wherein, The distance from the electromagnetic coil to the metal pipe network layer depends on the size of the aircraft wheels.

5. An aircraft ground deceleration method, comprising: when the aircraft deceleration function is activated, energizing the electromagnetic coil mounted on the aircraft landing gear strut to generate an electromagnetic field; when the aircraft moves forward after landing, the electromagnetic field also moves forward, the metal pipes in the metal pipe network layer laid under the airport runway cut the magnetic field lines of the electromagnetic field, and due to electromagnetic induction, an induced electromotive force is generated, and due to the existence of the induced electromotive force, there will be induced current in the metal pipe network layer, and the metal pipe network layer has a certain resistance, due to the thermal effect of the resistance, the kinetic energy of the aircraft is converted into electrical energy, and then into thermal energy and heat dissipation, thereby decelerating the aircraft on the ground; adjusting the current in the electromagnetic coil through the power supply controller located in the aircraft cabin to adjust the deceleration rate of the aircraft; wherein the induced current in the metal pipe network layer generates an electromagnetic field, wherein the metal pipe network layer under the runway is divided into a front landing gear strut area and a rear landing gear strut area, the front landing gear strut area generates an electromagnetic field opposite to the original magnetic field direction of the electromagnetic coil, hindering the aircraft from advancing, and the rear landing gear strut area generates an electromagnetic field consistent with the original magnetic field direction of the electromagnetic coil, also hindering the aircraft from advancing.

6. The method of claim 5, wherein, The aircraft ground deceleration method further comprises: before the aircraft lands, selecting the deceleration rate of the aircraft in the air, turning on the power supply controller, at this time the aircraft deceleration function is in a standby state; After the airplane lands, a control unit located in the airplane cabin determines the airplane grounding state based on the landing gear grounding signal; if the airplane is grounded, the airplane deceleration function is activated, and the control unit outputs a deceleration instruction; if the airplane is not grounded, the airplane deceleration function is not activated, and the control unit does not output a deceleration instruction.

7. The method of claim 5, wherein, The airplane ground deceleration method further comprises: when the airplane deceleration function is activated, cooling the metal pipe network layer by a cooling system.

8. The method of claim 5, wherein, The distance from the electromagnetic coil to the metal pipe network layer depends on the size of the airplane wheel.

9. The method of claim 6, wherein, When the airplane deceleration function is activated, the control unit controls the power controller to adjust the current in the electromagnetic coil according to the selected airplane deceleration rate; When the actual airplane deceleration rate is lower than the selected deceleration rate, the control unit outputs an instruction to increase the current; when the actual airplane deceleration rate is higher than the selected deceleration rate, the control unit outputs an instruction to decrease the current.

10. The method of claim 6, wherein, The airplane ground deceleration method further comprises: when the airplane is below a certain speed, the control unit outputs an instruction to turn off the deceleration function.

11. An airplane landing gear comprising an electromagnetic coil, the electromagnetic coil being mounted on the airplane landing gear strut for generating an electromagnetic field around it after being powered on; wherein When the electromagnetic coil is powered on and generates an electromagnetic field, and the airplane moves forward after landing, the electromagnetic field also moves forward, the metal pipes in the metal pipe network layer laid under the airport runway cut the magnetic field lines of the electromagnetic field, and an induced electromotive force is generated due to electromagnetic induction. Due to the existence of the induced electromotive force, an induced current will exist in the metal pipe network layer, and the metal pipe network layer has a certain resistance. Due to the thermal effect of the resistance, the kinetic energy of the airplane is converted into electrical energy and then into thermal energy and heat dissipation, thereby decelerating the airplane on the ground; The current in the electromagnetic coil when powered on can be adjusted. The induced current in the metal pipe network layer generates an electromagnetic field, wherein the metal pipe network layer under the runway is divided into a front area of the landing gear strut and a rear area of the landing gear strut. The front area of the landing gear strut generates an electromagnetic field opposite to the original magnetic field direction of the electromagnetic coil, which hinders the forward movement of the airplane, and the rear area of the landing gear strut generates an electromagnetic field consistent with the original magnetic field direction of the electromagnetic coil, which also hinders the forward movement of the airplane.

12. An airplane comprising: The airplane landing gear of claim 11; And A power controller, the power controller being located in the airplane cabin for adjusting the current in the electromagnetic coil.

13. The aircraft of claim 12, wherein, The airplane further comprises a control unit, the control unit being located in the airplane cabin for calculating the required current for deceleration and controlling the power controller to adjust the current in the electromagnetic coil.

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