Novel single-web type airplane brake main wheel

Abstract

The invention relates to the field of aviation brake airplane wheels, in particular to a novel single-web type airplane brake main airplane wheel which comprises a brake assembly and an airplane wheel assembly which are arranged on an undercarriage shaft, and the airplane wheel assembly and the brake assembly are installed on the undercarriage shaft together to form the single-web type airplane brake main airplane wheel. A first heat dissipation channel is formed between the outer ring of the heat reservoir assembly and the inner wall of an outer cylinder of the hub assembly, a second heat dissipation channel is formed between the inner ring of the brake shell assembly and the outer wall of an inner cylinder of the hub assembly, and the second heat dissipation channel communicates with a through hole formed in the end face of the brake shell assembly. Air flow output by the cooling fan assembly in the air collection cavity brings heat of the heat reservoir assembly out of the brake assembly through heat dissipation holes, a first heat dissipation channel and a second heat dissipation channel which are formed in the hub web. Radiation heat of the heat reservoir assembly can be dissipated into the atmosphere on the outer side of the aircraft wheel, and the cooling efficiency of the cooling fan on the heat reservoir assembly is greatly improved.

Description

Technical Field

[0001] The invention relates to the field of aircraft brake wheels, and in particular to a novel single-belly type aircraft brake main engine wheel. Background Art

[0002] In the field of aviation brakes, aircraft energy is increasing, while the weight requirements of wheels and their matching tires are decreasing. The unit mass energy load of the main brake wheel is increasing linearly. In order to quickly reduce the temperature of the main brake wheel and shorten the time it takes for the aircraft to be deployed again, more and more aircraft are equipped with fan cooling devices; in addition, in order to improve the field maintainability of the aircraft, a tire temperature and pressure monitoring device is designed to monitor the temperature and pressure of the wheel tire.

[0003] The key to rapid cooling of the main brake wheel lies in the matching design of the brake cooling fan and the motor. In the prior art, the lift-to-drag ratio is often improved by changing the number of fan blades and the airfoil, or the fan speed is increased by increasing the motor power to achieve the purpose of improving the cooling efficiency of the cooling fan. In recent years, the airfoil optimization of cooling fan blades has become increasingly mature and can no longer bring more efficiency improvements. At the same time, the increase in motor power will increase the weight and heat of the motor. Due to the restrictions on the use of the landing gear shaft, there are extremely strict requirements on the size, weight and heat generation of the motor installed inside the landing gear shaft. Therefore, from the perspective of the cooling device itself, there is not much potential for the cooling efficiency of the cooling fan.

[0004] Since the tire temperature and pressure sensors in the tire temperature and pressure monitoring device in the prior art are connected together through the threaded holes on the wheel hub that are connected to the inner cavity of the tire, the tire temperature and pressure signals are sent to the temperature and pressure detector through radio frequency signals, thereby detecting the temperature and pressure of the tire. In the entire take-off and landing mission profile of the aircraft, the tire temperature and pressure sensors need to withstand the impact load, brake vibration, and brake heat together with the main brake wheel, especially brake heat, which can cause the electronic components of the communication control module contained in the tire temperature and pressure sensor to malfunction. Therefore, how to improve the heat dissipation of the tire temperature and pressure monitoring device is an urgent problem to be solved.

[0005] Therefore, it is necessary to provide a novel single-belly type aircraft brake main wheel to solve the above problems. Summary of the invention

[0006] The invention provides a novel single-belly type aircraft brake main wheel to solve the problem in the prior art that electronic components of a communication control module included in a tire temperature and pressure sensor may fail due to the influence of brake heat.

[0007] A novel single-belly type aircraft brake main wheel of the present invention adopts the following technical scheme, including: a brake assembly and a wheel assembly arranged on a landing gear shaft, the wheel assembly including: a hub assembly, the hub assembly including an inner tube and an outer tube arranged concentrically, the inner tube sleeve being fixed on the landing gear shaft, an annular cavity being formed between the inner tube and the outer tube, and one of the end faces of the inner tube and the outer tube being connected through a hub belly plate, an air collecting hood assembly being arranged on a side of the hub belly plate away from the annular cavity, an air collecting cavity being formed between the air collecting hood assembly and the hub belly plate; a valve core seat and a temperature monitoring device are arranged on the outer surface of the hub belly plate in the air collecting cavity, and a cooling fan assembly is arranged on the end face of the landing gear shaft in the air collecting cavity; The brake assembly includes: a brake housing assembly, one of which extends into the annular cavity, and a cylinder seat assembly and a heat storage assembly are arranged on the outer ring of the brake housing assembly; Among them, a first heat dissipation channel is formed between the outer ring of the heat storage assembly and the inner wall of the outer tube of the wheel hub assembly, and a second heat dissipation channel is formed between the inner ring of the brake housing assembly and the outer wall of the inner tube of the wheel hub assembly. The second heat dissipation channel is connected to the through hole set on the end face of the brake housing assembly, and the airflow output by the cooling fan assembly in the air collecting cavity brings the heat of the heat storage assembly to the outside of the brake assembly through the heat dissipation holes set on the belly plate of the wheel hub, the first heat dissipation channel and the second heat dissipation channel.

[0008] Preferably, the outer cylinder of the hub assembly is trumpet-shaped, and a heat insulation shield assembly is provided on the inner wall of the outer cylinder.

[0009] Preferably, the heat insulation screen assembly comprises a heat insulation screen, a circular rubber pad is arranged on the surface of the heat insulation screen facing the inner wall of the outer cylinder, and the end of the heat insulation screen is connected to the inner wall of the outer cylinder through a connecting ear.

[0010] Preferably, the heat storage assembly includes a plurality of moving disk assemblies, and a plurality of arc-shaped heat dissipation grooves are arranged on the outer circle of each moving disk assembly.

[0011] Preferably, the through hole provided on the end surface of the brake housing assembly is an arc-shaped strip through hole, and the arc-shaped strip through hole is connected with the air collecting cavity through the second heat dissipation channel and the heat dissipation hole.

[0012] Preferably, an annular heat insulation plate is provided on the cylinder seat assembly, and a zirconium oxide thermal barrier coating is provided on the inner and outer surfaces of the annular heat insulation plate; a plurality of circular holes are opened on the annular heat insulation plate, and the circular holes are correspondingly sleeved on the bushing of the cylinder seat assembly, and the annular heat insulation plate and the bushing are fixed by a bushing nut.

[0013] Preferably, the heat dissipation hole arranged on the hub web is a transition hole with one end being larger and the other end being smaller, and the small end of the heat dissipation hole faces the air collecting cavity.

[0014] Preferably, the brake assembly further comprises: a heat insulation disc assembly, which is installed on the brake housing assembly between the cylinder seat assembly and the heat storage assembly.

[0015] Preferably, the insulation disk assembly comprises: an insulation disk, an inner insulation pad is arranged on the side of the insulation disk facing the output end of the cylinder seat assembly, and an outer insulation pad is arranged on the side of the insulation disk facing the heat storage assembly.

[0016] Preferably, the outer insulation pad and the inner insulation pad are made of titanium alloy material, and zirconium oxide thermal barrier coatings are provided on both side surfaces of the insulation disk.

[0017] The beneficial effects of the present invention are: 1. Through the brake assembly and the wheel assembly on the landing gear shaft, a first heat dissipation channel is formed between the outer ring of the heat storage assembly of the brake assembly and the inner wall of the outer tube of the wheel hub assembly, a second heat dissipation channel is formed between the inner ring of the brake housing assembly of the brake assembly and the outer wall of the inner tube of the wheel hub assembly, and an air collecting cavity is formed between the air collecting cover assembly and the hub belly plate. The first heat dissipation channel and the second heat dissipation channel are connected to the air collecting cavity through the heat dissipation holes on the hub belly plate, respectively. The cooling fan assembly of the air collecting cavity blows the cooling air to the heat storage assembly along the heat dissipation holes and the first heat dissipation channel, thereby dissipating the radiant heat of the heat storage assembly into the atmosphere outside the aircraft wheel, which greatly improves the cooling efficiency of the cooling fan on the heat storage assembly.

[0018] 2. The application of the heat insulation disc assembly and heat insulation plate of titanium alloy material and the zirconium oxide thermal barrier coating in the present invention realizes double-layer heat insulation. The design of the heat insulation pad of the heat insulation screen assembly plays a role in further isolating the heat of the heat storage assembly, ensuring that the temperature of the wheel hub, cylinder seat and landing gear shaft can meet the standard requirements under various working conditions.

[0019] 3. Secondly, the present invention sets the opening of the heat dissipation hole to be large at one end and small at the other end, and the small opening end of the heat dissipation hole faces the air collecting cavity, that is, the heat dissipation hole can prevent the cooling air of the cooling fan from rebounding to produce a vortex phenomenon, thereby ensuring that the cooling air is blown to the heat storage component; the water drop-shaped heat dissipation hole increases the area of ​​the heat dissipation hole and further improves the effective flow rate of the cooling air.

[0020] 4. The structural design of the valve core seat and valve core on the wheel hub assembly can ensure that the temperature and pressure monitoring device can be installed and removed at any time without the need to perform jacking and tire pressure release operations, greatly improving the operability of field maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1It is a schematic diagram of the overall structure of an embodiment of a novel single-belt type aircraft brake main wheel of the present invention; Figure 2 for Figure 1 A cross-sectional view of the structure of the brake assembly; Figure 3 for Figure 1 A half-section view of the structure of the middle wheel assembly; Figure 4 for Figure 3 A schematic diagram of the structure of the middle hub assembly; Figure 5 A schematic diagram of a heat dissipation channel for cooling air in a cross-sectional view of a wheel assembly and a brake assembly; Figure 6 for Figure 3 Schematic diagram of the structure of the middle insulation heat shield assembly; Figure 7 for Figure 2 Schematic diagram of the structure of the medium heat storage component; Figure 8 for Figure 2 A schematic diagram of the structure of the middle brake housing assembly; Fig. 9 for Figure 2 A schematic diagram of the structure of the middle cylinder seat assembly; Fig.10 It is a structural schematic diagram of the heat insulation board; Fig.11 is a schematic diagram of the structure of the heat insulation plate assembly; Fig.12 A schematic diagram of the installation holes for the temperature and pressure monitoring device; Fig.13 A schematic diagram of a valve core seat.

[0023] In the figure: 1. landing gear shaft; 2. brake device; 3. wheel assembly; 4. cooling fan assembly; 5. temperature and pressure monitoring device; 2-1. cylinder seat assembly; 2-2. brake housing assembly; 2-3. insulation plate assembly; 2-4. heat storage assembly; 3-1. wheel hub; 3-2. wheel rim; 3-3. snap ring; 3-4. air collecting cover assembly; 3-5. insulation screen assembly; 4-1. heat dissipation hole; 5-1. first heat dissipation channel; 5-2. second heat dissipation channel; 6-1. circular rubber pad; 6-2. connecting ear piece; 7-1. arc-shaped heat dissipation groove; 8-1. through hole; 10-1. round hole; 11-1. insulation plate; 11-2. inner insulation pad; 11-3. outer insulation pad. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] An embodiment of a novel single-belt aircraft brake main engine wheel of the present invention is as follows: Figure 1 As shown, it includes: a brake assembly 2 and a wheel assembly 3 arranged on the landing gear shaft 1, and the wheel assembly 3 and the brake assembly 2 are installed on the landing gear shaft 1 to form a Figure 1 The new single-belly aircraft brake main wheel shown.

[0026] Among them, Figure 3 As shown, the wheel assembly 3 of this embodiment includes a hub assembly 3-1, a rim 3-2, a snap ring assembly 3-3, an air collecting cover assembly 3-4 and a heat shield assembly 3-5, wherein the inner ring of the rim 3-2 is sleeved on the outer tube wall of the hub assembly 3-1, and together with the fixed rim of the hub assembly 3-1, it limits the tire, the snap ring assembly 3-3 is installed in the snap ring groove on the hub assembly 3-1, and limits the rim 3-2, the hub assembly 3-1 includes an inner tube and an outer tube arranged concentrically, the inner tube sleeve is fixed on the landing gear shaft 1, an annular cavity is formed between the inner tube and the outer tube, and one of the end faces of the inner tube and the outer tube is connected by a hub web, and the side of the hub web facing away from the annular cavity is provided with An air collecting hood assembly 3-4 is provided, and an air collecting cavity is formed between the air collecting hood assembly 3-4 and the hub web. In this embodiment, the hub assembly 3-1 is a single web structure, and the material of the hub assembly 3-1 is 2014 aluminum alloy; the air collecting hood assembly 3-4 is installed on the hub web, and the air collecting hood of the air collecting hood assembly 3-4 is a truncated cone-shaped thin cylinder structure with a maximum outer diameter of φ391mm and a thickness of 13mm; a valve core seat and a temperature monitoring device 5 are provided on the outer surface of the hub web in the air collecting cavity. In this embodiment, two threaded holes are provided on the inclined platforms on both side surfaces of the hub web, and the threaded holes on the inner side of the hub web are used to install the valve core seat, and the threaded holes on the outer side are used to install the temperature and pressure monitoring device 5. Fig.13As shown, the inner hole of the valve core seat is designed with a 5V1 threaded interface for installing a standard aviation valve core. The inner hole is designed with a standard hexagonal interface for installing and removing the valve core seat. After the temperature and pressure monitoring device 5 is installed on the hub assembly 3-1, the small cone on the end face of the temperature and pressure monitoring device 5 presses against the valve core stem head, so that the valve core is in a normally open state; after the temperature and pressure monitoring device 5 is removed, the valve core stem rebounds, so that the valve core is in a normally closed state. The structural design of the valve core seat and valve core on the hub assembly 3-1 can ensure that the temperature and pressure monitoring device can be installed and removed at any time without the need to perform the operations of lifting the aircraft and releasing the tire pressure, greatly improving the operability of field maintenance; a cooling fan assembly 4 is provided on the end face of the landing gear shaft 1 in the air collecting cavity. The inner wall of the outer cylinder of the hub assembly 3-1 is provided with a heat shield assembly 3-5. In this embodiment, the bottom diameter of the outer cylinder is φ459 mm, the outer cylinder mouth diameter is φ483 mm, and the whole is in a trumpet shape; the heat shield assembly 3-5 is installed parallel to the inner wall of the outer cylinder of the hub, forming a trumpet-shaped structure with a large mouth; Figure 6 As shown, the heat insulation screen assembly 3-5 includes a heat insulation screen, and a circular rubber pad 6-1 with a radius R of 6 mm is arranged on the surface of the heat insulation screen facing the inner wall of the outer cylinder. The end of the heat insulation screen is connected to the inner wall of the outer cylinder through the arranged connecting ear piece 6-2, and the circular rubber pad 6-1 is in contact with the inner wall of the outer cylinder of the wheel hub, thereby reducing the heat conduction of the heat insulation screen assembly 3-5 to the inner wall of the outer cylinder of the wheel hub.

[0027] Among them, Figure 2 As shown, the cylinder seat assembly 2-1, the brake housing 2-2, the heat insulation disc assembly 2-3 and the heat storage assembly 2-4, as Figure 1 As shown, one of the brake housing components 2-2 extends into the annular cavity, and the cylinder seat component 2-3 and the heat storage component 2-4 are arranged on the outer ring of the brake housing component 2-2; Figure 5 As shown, a first heat dissipation channel 5-1 is formed between the outer ring of the heat storage component 2-4 and the inner wall of the outer tube of the hub component 3-1, and a second heat dissipation channel 5-2 is formed between the inner ring of the brake housing component 2-2 and the outer wall of the inner tube of the hub component 3-1. The second heat dissipation channel 5-2 is connected to the through hole 8-1 set on the end face of the brake housing component 2-2. The airflow output by the cooling fan component 4 in the air collecting cavity brings the heat of the heat storage component 2-4 to the outside of the brake component 2 through the heat dissipation holes 4-1, the first heat dissipation channel 5-1 and the second heat dissipation channel 5-2 set on the belly plate of the hub. That is, the present device can dissipate most of the heat radiated by the heat storage component 2-4 into the atmosphere outside the aircraft wheel, which greatly improves the cooling efficiency of the cooling fan component 4 on the heat storage component 2-4.

[0028] Specifically, Figure 1 and Figure 7As shown, the heat storage component 2-4 includes a plurality of moving disk components, and a plurality of arc-shaped heat dissipation grooves 7-1 are arranged on the outer circle of each moving disk component. In this embodiment, the heat storage component 2-4 includes four moving disk components, and the outer circle of each moving disk component is designed with nine arc-shaped heat dissipation grooves 7-1 with a radius R of 150 mm.

[0029] Specifically, Figure 8 As shown, the brake housing assembly 2-2 is trumpet-shaped, and the small end of the brake housing assembly 2-2 is provided with 6 through holes 8-1, and the through holes 8-1 are arc-shaped strip through holes, and the arc-shaped strip through holes are connected with the air collecting cavity through the second heat dissipation channel 5-2 and the heat dissipation hole 4-1. In this embodiment, the radius R of the arc part of the arc-shaped strip through hole is 6mm, the width of the strip part is 24mm, and the hole depth is 64mm. The 6 arc-shaped strip through holes are used to dissipate the hot air of the second heat dissipation channel 5-2 to the outside of the brake device.

[0030] Specifically, Fig. 9 As shown, a circular heat insulation plate is provided on the cylinder base assembly 2-3. Fig.10 As shown, zirconium oxide thermal barrier coatings are provided on the inner and outer surfaces of the annular heat insulation plate; a plurality of circular holes 10-1 are opened on the annular heat insulation plate, and the circular holes 10-1 are correspondingly sleeved on the bushing of the cylinder seat assembly 2-3, and the annular heat insulation plate and the bushing are fixed by the bushing nut. In this embodiment, the maximum outer diameter of the cylinder seat assembly 2-3 is φ420mm, the inner diameter of the cylinder seat assembly 2-3 is φ230mm, and the annular heat insulation plate with a thickness of 2mm is sleeved on the outer ring of the bushing on the cylinder seat assembly. Five arc-shaped grooves with a radius R of 250mm are provided on the outer arc surface of the annular heat insulation plate, and the material of the annular heat insulation plate is TC4. The planes on both sides of the annular heat insulation plate are coated with zirconium oxide thermal barrier coating; the annular heat insulation plate is provided with five circular holes 10-1 with a diameter of φ53 mm, the circular holes 10-1 are respectively sleeved on the bushings of the cylinder seat assembly 2-3, and the annular heat insulation plate and the bushing are fixed together by bushing nuts.

[0031] Specifically, Figure 1 As shown, the heat dissipation hole 4-1 on the hub belly is a transition hole with one end larger than the other end, and the small end of the heat dissipation hole 4-1 faces the air collecting cavity. In this embodiment, the heat dissipation hole 4-1 is a teardrop-shaped through hole composed of 4 arc segments; the size of the heat dissipation hole 4-1 facing the inner side of the belly is larger than the outer side, forming a cooling air drainage channel, which can prevent the cooling air of the cooling fan assembly 4 from rebounding to produce a vortex phenomenon, and ensure that the cooling air output by the cooling fan assembly 4 is blown to the heat storage assembly 2-4.

[0032] Specifically, Figure 1As shown, the brake assembly 2 also includes: a heat insulation disc assembly, which is installed on the brake housing assembly 2-2 between the cylinder seat assembly 2-3 and the heat storage assembly 2-4, and the inner ring of the heat insulation disc assembly is sleeved on the convex key set on the outer ring of the brake housing assembly 2-2 through a keyway, as shown in FIG. Fig.11 As shown, the heat insulation disk assembly includes: a heat insulation disk 11-1, an inner heat insulation pad 11-2 is arranged on the side of the heat insulation disk 11-1 facing the output end of the cylinder seat assembly 2-3, and an outer heat insulation pad 11-3 is arranged on the side of the heat insulation disk 11-1 facing the heat storage assembly 2-4; the outer heat insulation pad 11-3 and the inner heat insulation pad 11-2 are made of titanium alloy material, and zirconium oxide thermal barrier coatings are arranged on both sides of the heat insulation disk 11-1. In this embodiment, the heat insulation disk 11-1, the inner heat insulation pad 11-2 and the outer heat insulation pad 11-3 are all made of TC4; the maximum outer diameter of the heat insulation disk 11-1 is φ393mm, the inner diameter of the heat insulation disk 11-1 is φ232mm, and the thickness of the heat insulation disk 11-1 is a circular ring structure of 6mm.

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A novel single-belt aircraft brake main wheel, comprising a brake assembly and a wheel assembly arranged on a landing gear shaft, characterized in that: The wheel assembly comprises: a hub assembly, the hub assembly comprises an inner cylinder and an outer cylinder arranged concentrically, the inner cylinder is fixed on the landing gear shaft, an annular cavity is formed between the inner cylinder and the outer cylinder, and one of the end faces of the inner cylinder and the outer cylinder is connected through a hub web, a wind collecting cover assembly is arranged on a side of the hub web away from the annular cavity, and an air collecting cavity is formed between the wind collecting cover assembly and the hub web; a valve core seat and a temperature monitoring device are arranged on the outer surface of the hub web in the air collecting cavity, and a cooling fan assembly is arranged on the end face of the landing gear shaft in the air collecting cavity; The brake assembly includes: a brake housing assembly, one of which extends into the annular cavity, and a cylinder seat assembly and a heat storage assembly are arranged on the outer ring of the brake housing assembly; Among them, a first heat dissipation channel is formed between the outer ring of the heat storage assembly and the inner wall of the outer tube of the wheel hub assembly, and a second heat dissipation channel is formed between the inner ring of the brake housing assembly and the outer wall of the inner tube of the wheel hub assembly. The second heat dissipation channel is connected to the through hole set on the end face of the brake housing assembly, and the airflow output by the cooling fan assembly in the air collecting cavity brings the heat of the heat storage assembly to the outside of the brake assembly through the heat dissipation holes set on the belly plate of the wheel hub, the first heat dissipation channel and the second heat dissipation channel.

2. A novel single-belt aircraft brake main wheel according to claim 1, characterized in that: The outer cylinder of the hub assembly is trumpet-shaped, and a heat insulation screen assembly is arranged on the inner wall of the outer cylinder.

3. A novel single-belt aircraft brake main wheel according to claim 2, characterized in that: The heat insulation screen assembly comprises a heat insulation screen, a circular rubber pad is arranged on the surface of the heat insulation screen facing the inner wall of the outer cylinder, and the end of the heat insulation screen is connected to the inner wall of the outer cylinder through a connecting ear piece.

4. The novel single-belt aircraft brake main wheel according to claim 1, characterized in that: The heat storage component comprises a plurality of moving disk components, and a plurality of arc-shaped heat dissipation grooves are arranged on the outer circle of each moving disk component.

5. The novel single-belt aircraft brake main wheel according to claim 1, characterized in that: The through hole arranged on the end surface of the brake housing assembly is an arc-shaped strip-shaped through hole, and the arc-shaped strip-shaped through hole is connected with the air collecting cavity through the second heat dissipation channel and the heat dissipation hole.

6. The novel single-belt aircraft brake main wheel according to claim 1, characterized in that: An annular heat insulation plate is arranged on the cylinder seat assembly, and a zirconium oxide thermal barrier coating is arranged on the inner and outer surfaces of the annular heat insulation plate; a plurality of circular holes are opened on the annular heat insulation plate, and the circular holes are correspondingly sleeved on the bushing of the cylinder seat assembly, and the annular heat insulation plate and the bushing are fixed by a bushing nut.

7. The novel single-belt aircraft brake main wheel according to claim 1, characterized in that: The heat dissipation hole arranged on the hub web is a transition hole with a large opening at one end and a small opening at the other end, and the small opening end of the heat dissipation hole faces the air collecting cavity.

8. The novel single-belt type aircraft brake main wheel according to claim 1, characterized in that: The brake assembly also includes: a heat insulation disc assembly, which is installed on the brake housing assembly between the cylinder seat assembly and the heat storage assembly.

9. The novel single-belt aircraft brake main wheel according to claim 8, characterized in that: The heat insulation disk assembly comprises: a heat insulation disk, an inner heat insulation pad is arranged on one side of the heat insulation disk facing the output end of the cylinder seat assembly, and an outer heat insulation pad is arranged on one side of the heat insulation disk facing the heat storage assembly.

10. The novel single-belt type aircraft brake main wheel according to claim 9, characterized in that: The outer insulation pad and the inner insulation pad are made of titanium alloy material, and zirconium oxide thermal barrier coatings are provided on both sides of the insulation disk.

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