CN210101975U - Hydraulic control braking device of light sport aircraft - Google Patents
Hydraulic control braking device of light sport aircraft Download PDFInfo
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- CN210101975U CN210101975U CN201920474495.XU CN201920474495U CN210101975U CN 210101975 U CN210101975 U CN 210101975U CN 201920474495 U CN201920474495 U CN 201920474495U CN 210101975 U CN210101975 U CN 210101975U
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Abstract
The utility model discloses and provides a hydraulic control brake device of a light sport airplane with good brake effect, flexible operation and improved airplane stability during braking, which comprises a hydraulic brake mechanism and a landing wheel mechanism, wherein the hydraulic brake mechanism and the landing wheel mechanism are connected through a hydraulic rubber tube; hydraulic braking mechanism includes braking frame, pedal brake group and brake valve, landing wheel mechanism includes unit wheel, unit link and brake disc, the utility model discloses be applied to aircraft braking technical field.
Description
Technical Field
The utility model belongs to the technical field of aircraft braking technique and specifically relates to a liquid accuse arresting gear of light-duty motion aircraft.
Background
When the airplane lands on the ground, the airplane has larger horizontal speed division, but the deceleration effect of the aerodynamic resistance and the rolling resistance of the airplane wheel on the airplane is smaller in the sliding process. If the aircraft is not tried to increase the drag and decelerate quickly, the landing and running distance and time will be long, and the runway for taking off and landing will be long. The aircraft is equipped with a reduction unit. Currently, the wheel brake device is the most important one of the wheel brake devices and the wheel brake device is the most widely applied one. The light sport aircraft in the prior art mainly adopts a steel wire directly connected with a brake pad, and directly uses a disc to brake a hub to realize speed reduction. Because there is the problem of elasticity in wire rope, will produce the risk of braking time delay or wire rope fracture when the aircraft brakes, obviously have very big potential safety hazard like this.
Disclosure of Invention
The utility model aims to solve the technical problem that overcome prior art not enough, provide a liquid accuse arresting gear of light-duty motion aircraft of aircraft stationarity when braking effectual, flexible operation and improvement braking.
The utility model adopts the technical proposal that: the hydraulic control brake device of the light sport aircraft comprises a hydraulic brake mechanism and a landing wheel mechanism, wherein the hydraulic brake mechanism is connected with the landing wheel mechanism through a hydraulic rubber tube.
The hydraulic braking mechanism comprises a braking rack, a pedal braking group and a braking valve; the foot brake group is including setting gradually from left to right first foot mechanism, second foot mechanism, third foot mechanism and fourth foot mechanism in the braking frame, first foot mechanism includes that first pedal and first brake pump, second foot mechanism includes that the second is pedal and second brake pump, third foot mechanism includes that the third is pedal and third brake pump, fourth foot mechanism includes that the fourth is pedal and fourth brake pump, first brake pump pass through the hydraulic hose with the third brake pump is connected, the second brake pump pass through the hydraulic hose with the fourth brake pump is connected, the third brake pump with the fourth brake pump pass through the hydraulic hose with brake valve connects.
The landing wheel mechanism comprises a unit wheel, a unit connecting frame and a brake disc; the unit connecting frame is fixedly connected with the unit wheel, the brake disc is arranged on the inner side of the unit wheel and used for braking the unit wheel, and the brake disc is connected with the brake valve through a hydraulic rubber tube.
And the brake valve is also connected with a hand brake device of the light sport airplane through a hand brake hydraulic pipe.
The utility model discloses beneficial effect with the prior art contrast is: because the hydraulic control brake device of the light sport aircraft comprises the hydraulic brake mechanism and the landing wheel mechanism, the hydraulic brake mechanism and the landing wheel mechanism are connected through the hydraulic rubber tube; the hydraulic braking mechanism comprises a braking rack, a pedal braking group and a braking valve; the landing wheel mechanism comprises a unit wheel, a unit connecting frame and a brake disc; through two sets of brake pumps provide pressure respectively, through hydraulic pressure rubber tube and brake valve, accomplish braking operation in arriving the brake disc of two sets of unit wheels respectively at last, so the utility model discloses effectively provide a liquid accuse arresting gear of the light-duty motion aircraft of aircraft stationarity when braking effectual, flexible operation and improvement braking.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings.
As shown in figure 1, the hydraulic control brake device of the light sport aircraft comprises a hydraulic brake mechanism and a landing wheel mechanism, wherein the hydraulic brake mechanism is connected with the landing wheel mechanism through a hydraulic rubber tube.
The hydraulic braking mechanism comprises a braking rack 200, a pedal braking group and a brake valve 100; the pedal brake set comprises a first pedal mechanism, a second pedal mechanism, a third pedal mechanism and a fourth pedal mechanism which are sequentially arranged on the brake rack 200 from left to right, the first pedal mechanism comprises a first pedal 1 and a first brake pump 5, the second pedal mechanism comprises a second pedal 2 and a second brake pump 6, the third pedal mechanism comprises a third pedal 3 and a third brake pump 7, the fourth pedal mechanism comprises a fourth pedal 4 and a fourth brake pump 8, the first brake pump 5 is connected with the third brake pump 7 through a hydraulic hose, the second brake pump 6 is connected with the fourth brake pump 8 through a hydraulic hose, the third brake pump 7 and the fourth brake pump 8 are connected with the brake valve 100 through a hydraulic hose, and the brake system can be operated by a main driver and an auxiliary driver through the arrangement of two-stage brake pedals, the safety and flexibility of the takeoff and landing of the airplane are improved.
The landing wheel mechanism comprises a unit wheel 9, a unit connecting frame 10 and a brake disc 11; the unit connecting frame 10 is fixedly connected with the unit wheel 9, the brake disc 11 is arranged on the inner side of the unit wheel 9 and used for braking the unit wheel 9, and the brake disc 11 is connected with the brake valve 100 through a hydraulic rubber tube.
The brake valve 100 is also connected with a hand brake device of the light sport aircraft through a hand brake hydraulic pipe 12, and when the aircraft needs to be parked, the brake valve can be locked by pulling the hand brake device, so that the aircraft is braked.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are covered by the protection scope of the present invention, therefore, the protection scope of the present invention should be subject to the protection scope of the claims.
Claims (3)
1. A hydraulic control brake device of a light sport aircraft is characterized in that: the hydraulic control braking device of the light sport aircraft comprises a hydraulic braking mechanism and a landing wheel mechanism, wherein the hydraulic braking mechanism is connected with the landing wheel mechanism through a hydraulic rubber tube; the hydraulic brake mechanism comprises a brake rack (200), a pedal brake group and a brake valve (100); the pedal brake group comprises a first pedal mechanism, a second pedal mechanism, a third pedal mechanism and a fourth pedal mechanism which are sequentially arranged on the brake rack (200) from left to right, the first pedal mechanism comprises a first pedal (1) and a first brake pump (5), the second pedal mechanism comprises a second pedal (2) and a second brake pump (6), the third pedal mechanism comprises a third pedal (3) and a third brake pump (7), the fourth pedal mechanism comprises a fourth pedal (4) and a fourth brake pump (8), the first brake pump (5) is connected with the third brake pump (7) through a hydraulic rubber pipe, the second brake pump (6) is connected with the fourth brake pump (8) through a hydraulic rubber pipe, the third brake pump (7) and the fourth brake pump (8) are connected with the brake valve (100) through a hydraulic rubber pipe.
2. The pilot-operated brake device for a light sport aircraft as recited in claim 1, wherein: the landing wheel mechanism comprises a unit wheel (9), a unit connecting frame (10) and a brake disc (11); the unit connecting frame (10) is fixedly connected with the unit wheel (9), the brake disc (11) is arranged on the inner side of the unit wheel (9) and used for braking the unit wheel (9), and the brake disc (11) is connected with the brake valve (100) through a hydraulic rubber tube.
3. The pilot-operated brake device for a light sport aircraft as recited in claim 1, wherein: the brake valve (100) is also connected with a hand brake device of the light sport airplane through a hand brake hydraulic pipe (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920474495.XU CN210101975U (en) | 2019-04-10 | 2019-04-10 | Hydraulic control braking device of light sport aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920474495.XU CN210101975U (en) | 2019-04-10 | 2019-04-10 | Hydraulic control braking device of light sport aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210101975U true CN210101975U (en) | 2020-02-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920474495.XU Active CN210101975U (en) | 2019-04-10 | 2019-04-10 | Hydraulic control braking device of light sport aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210101975U (en) |
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2019
- 2019-04-10 CN CN201920474495.XU patent/CN210101975U/en active Active
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