CN112644694B - Electromagnetic energy conversion hydraulic brake integrated device - Google Patents
Electromagnetic energy conversion hydraulic brake integrated device Download PDFInfo
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- CN112644694B CN112644694B CN202110043404.9A CN202110043404A CN112644694B CN 112644694 B CN112644694 B CN 112644694B CN 202110043404 A CN202110043404 A CN 202110043404A CN 112644694 B CN112644694 B CN 112644694B
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- brake
- hydraulic
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- assembly
- disc
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T13/00—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems
- B60T13/10—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with fluid assistance, drive, or release
- B60T13/12—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with fluid assistance, drive, or release the fluid being liquid
- B60T13/16—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with fluid assistance, drive, or release the fluid being liquid using pumps directly, i.e. without interposition of accumulators or reservoirs
- B60T13/20—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with fluid assistance, drive, or release the fluid being liquid using pumps directly, i.e. without interposition of accumulators or reservoirs with control of pump driving means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T7/00—Brake-action initiating means
- B60T7/12—Brake-action initiating means for automatic initiation; for initiation not subject to will of driver or passenger
Abstract
The integrated device is arranged between a main shaft of an undercarriage and wheels and comprises a fixed disc, a magnetic power generation assembly and a hydraulic brake assembly, wherein the fixed disc is fixedly connected with the lower end of the main shaft of the undercarriage, the fixed disc is rotatably connected with the wheels through a rotating shaft, and the magnetic power generation assembly and the hydraulic brake assembly are arranged between the fixed disc and the wheels; this is disclosed through setting up magnetism electricity generation subassembly and hydraulic brake subassembly, when the aircraft landed, at the in-process of landing with aircraft self kinetic energy conversion electric energy to provide brake pressure through electric energy drive hydraulic brake subassembly, under the passive circumstances of inputing, realized the brake function.
Description
Technical Field
The utility model relates to an aircraft brake field especially relates to an electromagnetic energy conversion hydraulic pressure brake integrated device.
Background
The braking process is an energy dissipation process, and the energy can be quickly dissipated in a proper mode, so that the landing running distance can be shortened, and the aim of quick braking is fulfilled. The existing braking modes adopted by the airplane comprise pneumatic braking, traditional long pipeline hydraulic braking, mechanical braking and other structures. For pneumatic braking, the problems of light braking force (low braking pressure) and serious heating exist; for the traditional long-pipe hydraulic brake, the problems of poor cleaning degree, difficult maintenance and the like of 'running, overflowing and dripping' exist; for a mechanical brake, the key problem that the clamping is difficult to remove exists.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present disclosure provides an electromagnetic energy conversion hydraulic brake integrated device.
According to the electromagnetic energy conversion hydraulic brake integrated device, the integrated device is arranged between a landing gear main shaft and wheels, the integrated device comprises a fixed disc, a magnetic power generation assembly and a hydraulic brake assembly, the fixed disc is fixedly connected with the lower end of the landing gear main shaft, the fixed disc is rotatably connected with the wheels through a rotating shaft, and the magnetic power generation assembly and the hydraulic brake assembly are arranged between the fixed disc and the wheels;
the magnetic power generation assembly comprises an electromagnetic generator which is fixedly arranged between the fixed disc and the airplane wheel;
the hydraulic brake subassembly includes hydraulic pressure subassembly and brake subassembly, hydraulic pressure subassembly with fixed disk fixed connection, hydraulic pressure subassembly's power input end with electromagnetic generator's power output end electricity is connected, brake subassembly sets up the fixed disk with between the wheel, the hydraulic pressure subassembly drive the brake subassembly action.
Specifically, the electromagnetic generator includes an electromagnetic stator and an electromagnetic rotor, the electromagnetic rotor is fixedly disposed on the hub of the airplane wheel, the electromagnetic stator is fixedly disposed on the fixed disk, and the electromagnetic stator and the electromagnetic rotor are correspondingly disposed.
Preferably, the magnetic power generation assembly further comprises a conditioning circuit and an energy storage capacitor, the conditioning circuit is arranged between the power output end of the electromagnetic generator and the power input end of the hydraulic assembly, and the energy storage capacitor is connected with the electromagnetic generator in parallel.
Specifically, the brake assembly comprises a brake disc and a brake device, the brake disc is fixedly connected with a hub of the wheel, the brake device is fixedly connected with an action end of the hydraulic assembly, and the brake disc and the brake device are correspondingly arranged.
Preferably, the fixed disk, the airplane wheel, the electromagnetic stator, the electromagnetic rotor and the brake disc are coaxially arranged, the electromagnetic stator and the braking device are arranged on the outer side surface of the fixed disk, and the electromagnetic rotor and the brake disc are arranged on the inner side surface of the hub of the airplane wheel.
Specifically, the hydraulic pressure subassembly includes motor, hydraulic pump, oil tank, brake control subassembly and actuator, the power input of motor with modulate circuit's power output end electricity and connect, the torque output of motor with the torque input of hydraulic pump is connected, the hydraulic oil input of hydraulic pump pass through the low pressure oil circuit with the oil tank intercommunication, the hydraulic oil output of hydraulic pump pass through high-pressure oil circuit with the brake control subassembly with the actuator intercommunication, the brake control subassembly with be provided with the oil return oil circuit between the oil tank, the action end of actuator with arresting gear connects.
Specifically, the brake control assembly comprises a brake control system and at least two brake control valves, the brake control valves are electrically connected with the brake control system, and the two brake control valves are respectively arranged on the high-pressure oil path and the oil return oil path.
Furthermore, the hydraulic assembly further comprises an energy accumulator and a safety valve, the energy accumulator is arranged on the high-pressure oil way, the safety valve is arranged between the high-pressure oil way and the low-pressure oil way, and a connection point of the safety valve and the high-pressure oil way is arranged behind the energy accumulator.
Specifically, the undercarriage main shaft is fixedly connected with the inner side face of the fixed disk, and the undercarriage main shaft is perpendicular to the central axis of the fixed disk.
According to at least one embodiment of the disclosure, by arranging the magnetic power generation assembly and the hydraulic brake assembly, when the aircraft lands, the kinetic energy of the aircraft is converted into electric energy in the landing process, the hydraulic brake assembly is driven by the electric energy to provide brake pressure, and the brake function is realized under the condition of passive input.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.
Fig. 1 is a structural block diagram of an electromagnetic energy conversion hydraulic brake integrated device according to the present disclosure.
Fig. 2 is a front view of an electromagnetic energy conversion hydraulic brake integrated device according to the present disclosure.
Fig. 3 is an exploded view of an integrated electromagnetic energy-to-hydraulic brake device according to the present disclosure.
Reference numerals are as follows: the method comprises the following steps of 1-undercarriage spindle, 2-hydraulic brake component, 3-electromagnetic rotor, 4-electromagnetic stator, 5-airplane wheel, 6-hub and 7-fixed disc.
Detailed Description
The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant matter and not restrictive of the disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1, an electromagnetic energy conversion hydraulic brake integrated device includes a fixed disk 7, a magnetic power generation assembly and a hydraulic brake assembly 2, wherein the magnetic power generation assembly includes a magnetic device rotor (an electromagnetic rotor 3), a magnetic device stator (an electromagnetic stator 4) and a capacitor (an energy storage capacitor); the hydraulic brake component 2 comprises a motor, a hydraulic pump, an oil tank, an energy accumulator, a safety valve, a brake controller and an actuator.
As shown in fig. 2, an electromagnetic energy conversion hydraulic brake integrated device, the integrated device is arranged between an undercarriage main shaft 1 and an undercarriage wheel 5, a fixed disk 7 is fixedly connected with the lower end of the undercarriage main shaft 1, the fixed disk 7 is rotatably connected with the undercarriage wheel 5 through a rotating shaft, a magnetic power generation assembly and a hydraulic brake assembly 2 are arranged between the fixed disk 7 and the undercarriage wheel 5, the undercarriage main shaft 1 is fixedly connected with the inner side surface of the fixed disk 7, and the undercarriage main shaft 1 is perpendicular to the central axis of the fixed disk 7.
The magnetic power generation assembly (partial element), the energy storage capacitor, the motor, the hydraulic pump, the energy accumulator, the oil tank, the brake control valve, the safety valve and the like are designed into an integrated hydraulic package and are attached to the undercarriage.
The kinetic energy of the airplane is large when the airplane lands, the kinetic energy of the airplane is converted into electric energy through the magnetic power generation assembly and is transmitted to the highly-integrated hydraulic bag, the brake pressure of the MPa level is finally provided, the purpose of rapid braking is achieved, the energy transmission of a long pipeline is replaced, and the self weight of the airplane is reduced.
The magnetic power generation assembly comprises an electromagnetic power generator, a conditioning circuit and an energy storage capacitor, the electromagnetic power generator is fixedly arranged between the fixed disc 7 and the wheel 5, the conditioning circuit is arranged between the power output end of the electromagnetic power generator and the power input end of the hydraulic assembly, and the energy storage capacitor is connected with the electromagnetic power generator in parallel.
The electromagnetic generator comprises an electromagnetic stator 4 and an electromagnetic rotor 3, wherein the electromagnetic rotor 3 is fixedly arranged on a hub 6 of the airplane wheel 5, the electromagnetic stator 4 is fixedly arranged on a fixed disc 7, and the electromagnetic stator 4 and the electromagnetic rotor 3 are correspondingly arranged.
The electromagnetic rotor 3 is attached to a hub 6 of the airplane wheel 5, the random wheel 5 rotates together, the electromagnetic rotor serves as a rotor of the electromagnetic generator, and the electromagnetic stator 4 (in a coil winding fixing mode) is fixed on the fixed disc 7 and faces the electromagnetic rotor 3.
When the wheel 5 rotates at a high speed, the electromagnetic generator is connected in parallel with the energy storage capacitor through the direct current voltage which is generated by the electromagnetic induction phenomenon and changes along with the rotating speed of the wheel 5.
When the power generation capacity is sufficient, two parts of supply are carried out, one part is stored in the energy storage capacitor, and the other part is directly conveyed to the hydraulic assembly for use.
When the power generation capacity is insufficient, the energy stored in the energy storage capacitor is discharged and is transmitted to the hydraulic assembly for use.
In the hydraulic brake component 2, the hydraulic component drives the brake component to act, so that the deceleration brake capacity of the airplane is realized.
The hydraulic brake component 2 comprises a hydraulic component and a brake component, the hydraulic component is fixedly connected with the fixed disk 7, a power input end of the hydraulic component is electrically connected with a power output end of the electromagnetic generator, the brake component is arranged between the fixed disk 7 and the wheel 5, and the hydraulic component drives the brake component to act.
The brake assembly comprises a brake disc and a brake device, the brake disc is fixedly connected with a hub 6 of the wheel 5, the brake device is fixedly connected with an action end of the hydraulic assembly, and the brake disc and the brake device are correspondingly arranged.
The hydraulic component comprises a motor, a hydraulic pump, an oil tank, a brake control component and an actuator, wherein a power input end of the motor is electrically connected with a power output end of the conditioning circuit, a torque output end of the motor is connected with a torque input end of the hydraulic pump, a hydraulic oil input end of the hydraulic pump is communicated with the oil tank through a low-pressure oil way, a hydraulic oil output end of the hydraulic pump is communicated with the actuator through a high-pressure oil way and the brake control component, an oil return way is arranged between the brake control component and the oil tank, and an action end of the actuator is connected with the braking device.
The brake control assembly comprises a brake control system and at least two brake control valves, the brake control valves are electrically connected with the brake control system, and the two brake control valves are respectively arranged on the high-pressure oil path and the oil return path.
When the brake control assembly judges that braking can be carried out, the motor drives the hydraulic pump to work, the hydraulic pump pumps hydraulic oil in the oil tank into the brake control assembly, high-pressure oil is input into the actuator through the brake control assembly, the actuator drives the brake device to act, and braking operation is achieved through friction between the brake device and the brake disc.
The braking device can be a brake device such as a brake caliper, a brake pad and the like.
After the brake is finished, hydraulic oil in the actuator flows back to the oil tank through the brake control assembly, and the brake is loosened.
The brake control valve is only one example, and the control of the actuator can be realized by other valve components, such as a four-way servo valve.
The hydraulic assembly further comprises an energy accumulator and a safety valve, the energy accumulator is arranged on the high-pressure oil way, the safety valve is arranged between the high-pressure oil way and the low-pressure oil way, and a connection point of the safety valve and the high-pressure oil way is the rear of the energy accumulator.
Through setting up energy storage ware and relief valve, can carry out the energy storage operation in advance, promote brake efficiency, can flow back to the oil tank through the relief valve with the hydraulic oil of high pressure simultaneously, avoid the actuator to be damaged.
The fixed disc 7, the airplane wheel 5, the electromagnetic stator 4, the electromagnetic rotor 3 and the brake disc are all coaxially arranged, the electromagnetic stator 4 and the braking device are arranged on the outer side face of the fixed disc 7, and the electromagnetic rotor 3 and the brake disc are arranged on the inner side face of the hub 6 of the airplane wheel 5.
Through with each part coaxial arrangement, can avoid appearing tangential force, influence the work efficiency of pivot and each part.
The working flow of the integrated device is described below with reference to fig. 1, 2 and 3:
high-speed working conditions: when the airplane lands on the ground, the braking operation cannot be carried out within a few seconds just after the airplane lands on the ground, the airplane wheel 5 can rotate sufficiently, and at the moment, the electromagnetic stator 4 and the electromagnetic mover 3 move relatively to generate power under the principle of electromagnetic induction.
Although the braking operation is not performed and the hydraulic brake component 2 is not actuated, the electric energy generated by the electromagnetic generator is already stored in the energy storage capacitor connected in parallel.
After the wheel speed is continuously stabilized, the brake control system judges that the brake can be carried out, the brake control system controls to transmit electric energy to the hydraulic assembly at the moment, the output voltage generated by the magnetic power generation assembly is set at the constant working point of the motor through the conditioning circuit, and the requirement that the motor drives the hydraulic pump to work is met.
The brake control valves are also opened simultaneously, the hydraulic part of the whole device is closed and starts to supply pressure, the pressure pushes the actuator to apply acting force to the brake device, so that the brake device extrudes the friction brake disc, redundant flow is overflowed through the fixed safety valve, and meanwhile, the energy accumulator is designed to stabilize fluctuation generated when the brake control valves are opened. Finally, the actuator extrudes the brake disc to generate braking torque, so that the airplane can be rapidly stopped.
And (3) low-speed working condition: when the speed of the airplane is reduced and the rotating speed of the airplane wheel 5 is lower than the generating rotating speed of the magnetic generating device, the conditioning circuit switches energy input to the energy storage capacitor for independent discharging, the requirement of the motor is met, and the capability of stopping the airplane is realized.
The aircraft uses the braking logic process when the aircraft lands on the ground and the relative motion of the wheel 5 and the fixed disk 7 in the braking process, and converts the magnetic power generation assembly designed by the electromagnetic characteristic in a non-contact mode into electric energy for use, thereby realizing passive input.
For the earlier stage of the high-speed landing process, the magnetic power generation device has strong power generation capacity, the excess energy is stored through the energy storage capacitor connected in parallel with the magnetic power generation device, and meanwhile, the electric energy required by the motor can be met. When the wheel speed gradually reduces, the supply of the magnetic power generation assembly is cut off, the energy storage capacitor is completely used for discharging, the voltage required by the motor is met, and the utilization rate of energy is higher.
Whole device and original part do not have the cooperation of motion level, and the security is high, and the structure of hydraulic pressure part is the form of totally enclosed, integrating, has solved traditional hydraulic pressure pipeline and has transported the energy, reveals problem and pipeline weight problem.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure and are not intended to limit the scope of the disclosure. Other variations or modifications may be made to those skilled in the art, based on the above disclosure, and still be within the scope of the present disclosure.
Claims (6)
1. The electromagnetic energy conversion hydraulic brake integrated device is characterized in that the integrated device is arranged between a landing gear main shaft and wheels, the integrated device comprises a fixed disc, a magnetic power generation assembly and a hydraulic brake assembly, the fixed disc is fixedly connected with the lower end of the landing gear main shaft, the fixed disc is rotatably connected with the wheels through a rotating shaft, and the magnetic power generation assembly and the hydraulic brake assembly are arranged between the fixed disc and the wheels;
the magnetic power generation assembly comprises an electromagnetic generator which is fixedly arranged between the fixed disc and the airplane wheel;
the hydraulic brake component comprises a hydraulic component and a brake component, the hydraulic component is fixedly connected with the fixed disc, a power supply input end of the hydraulic component is electrically connected with a power supply output end of the electromagnetic generator, the brake component is arranged between the fixed disc and the airplane wheel, and the hydraulic component drives the brake component to act;
the magnetic power generation assembly further comprises a conditioning circuit and an energy storage capacitor, the conditioning circuit is arranged between the power output end of the electromagnetic generator and the power input end of the hydraulic assembly, and the energy storage capacitor is connected with the electromagnetic generator in parallel;
the brake assembly comprises a brake disc and a brake device, the brake disc is fixedly connected with a hub of the airplane wheel, the brake device is fixedly connected with an action end of the hydraulic assembly, and the brake disc and the brake device are arranged correspondingly;
the hydraulic assembly includes motor, hydraulic pump, oil tank, brake control subassembly and actuator, the power input of motor with the power output end electricity of modulate circuit is connected, the torque output of motor with the torque input of hydraulic pump is connected, the hydraulic oil input of hydraulic pump pass through the low pressure oil circuit with the oil tank intercommunication, the hydraulic oil output of hydraulic pump pass through the high pressure oil circuit with the brake control subassembly with the actuator intercommunication, the brake control subassembly with be provided with the oil return oil circuit between the oil tank, the action end of actuator with arresting gear connects.
2. The electromagnetic energy conversion hydraulic brake integrated device as claimed in claim 1, wherein the electromagnetic generator includes an electromagnetic stator and an electromagnetic mover, the electromagnetic mover is fixedly disposed on the hub of the wheel, the electromagnetic stator is fixedly disposed on the fixed disk, and the electromagnetic stator and the electromagnetic mover are disposed correspondingly.
3. The electromagnetic energy conversion hydraulic brake integrated device as claimed in claim 2, wherein the fixed disk, the wheels, the electromagnetic stator, the electromagnetic rotor and the brake disc are coaxially arranged, the electromagnetic stator and the brake device are arranged on an outer side surface of the fixed disk, and the electromagnetic rotor and the brake disc are arranged on an inner side surface of a hub of the wheels.
4. The electromagnetic energy conversion hydraulic brake integrated device as claimed in claim 1, wherein the brake control assembly includes a brake control system and at least two brake control valves, the brake control valves are electrically connected to the brake control system, and the two brake control valves are respectively disposed on the high-pressure oil path and the oil return oil path.
5. The integrated electromagnetic energy-to-hydraulic brake device of claim 1, wherein the hydraulic assembly further comprises an accumulator and a safety valve, the accumulator is disposed on the high-pressure oil path, the safety valve is disposed between the high-pressure oil path and the low-pressure oil path, and a connection point of the safety valve and the high-pressure oil path is behind the accumulator.
6. The integrated electromagnetic energy conversion hydraulic brake device of claim 3, wherein the landing gear main shaft is fixedly connected with the inner side surface of the fixed disk, and the landing gear main shaft is perpendicular to the central axis of the fixed disk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110043404.9A CN112644694B (en) | 2021-01-13 | 2021-01-13 | Electromagnetic energy conversion hydraulic brake integrated device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110043404.9A CN112644694B (en) | 2021-01-13 | 2021-01-13 | Electromagnetic energy conversion hydraulic brake integrated device |
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| Publication Number | Publication Date |
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| CN112644694A CN112644694A (en) | 2021-04-13 |
| CN112644694B true CN112644694B (en) | 2023-01-20 |
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| CN202110043404.9A Active CN112644694B (en) | 2021-01-13 | 2021-01-13 | Electromagnetic energy conversion hydraulic brake integrated device |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1378995A (en) * | 1972-03-17 | 1975-01-02 | Knorr Bremse Gmbh | Brake apparatus |
| EP2213538A1 (en) * | 2009-01-28 | 2010-08-04 | Alenia Aeronautica S.p.A. | Braking system for the undercarriage of an aircraft |
| CN103640487A (en) * | 2013-12-09 | 2014-03-19 | 江苏大学 | Electromagnetism and hydraulic pressure compound brake with self power generation function and working method |
| CN204701473U (en) * | 2015-05-15 | 2015-10-14 | 山东交通学院 | A kind of Electro-hydraulic brake system with retarder brake function |
| CN105365801A (en) * | 2014-08-15 | 2016-03-02 | 湾流航空航天公司 | Apparatus and method for controlling a hydraulic brake of an aircraft |
| WO2017007509A2 (en) * | 2015-07-07 | 2017-01-12 | Acs International, Llc | Kinetic energy recovery system under braking |
| CN107097764A (en) * | 2017-04-25 | 2017-08-29 | 浙江工业大学 | A kind of vehicle hydraulic, wheel hub motor combined brake energy recovery system |
| CN107444380A (en) * | 2017-09-13 | 2017-12-08 | 吉林大学 | A kind of integrated form line traffic control hydraulic brake system |
-
2021
- 2021-01-13 CN CN202110043404.9A patent/CN112644694B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1378995A (en) * | 1972-03-17 | 1975-01-02 | Knorr Bremse Gmbh | Brake apparatus |
| EP2213538A1 (en) * | 2009-01-28 | 2010-08-04 | Alenia Aeronautica S.p.A. | Braking system for the undercarriage of an aircraft |
| CN103640487A (en) * | 2013-12-09 | 2014-03-19 | 江苏大学 | Electromagnetism and hydraulic pressure compound brake with self power generation function and working method |
| CN105365801A (en) * | 2014-08-15 | 2016-03-02 | 湾流航空航天公司 | Apparatus and method for controlling a hydraulic brake of an aircraft |
| CN204701473U (en) * | 2015-05-15 | 2015-10-14 | 山东交通学院 | A kind of Electro-hydraulic brake system with retarder brake function |
| WO2017007509A2 (en) * | 2015-07-07 | 2017-01-12 | Acs International, Llc | Kinetic energy recovery system under braking |
| CN107097764A (en) * | 2017-04-25 | 2017-08-29 | 浙江工业大学 | A kind of vehicle hydraulic, wheel hub motor combined brake energy recovery system |
| CN107444380A (en) * | 2017-09-13 | 2017-12-08 | 吉林大学 | A kind of integrated form line traffic control hydraulic brake system |
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