CN113830295A - Amphibious aircraft brake oil circuit structure - Google Patents
Amphibious aircraft brake oil circuit structure Download PDFInfo
- Publication number
- CN113830295A CN113830295A CN202111169064.0A CN202111169064A CN113830295A CN 113830295 A CN113830295 A CN 113830295A CN 202111169064 A CN202111169064 A CN 202111169064A CN 113830295 A CN113830295 A CN 113830295A
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- CN
- China
- Prior art keywords
- brake
- normal
- emergency brake
- main
- hard conduit
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
- B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
- B60T17/04—Arrangements of piping, valves in the piping, e.g. cut-off valves, couplings or air hoses
- B60T17/043—Brake line couplings, air hoses and stopcocks
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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
- B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
- B60T17/04—Arrangements of piping, valves in the piping, e.g. cut-off valves, couplings or air hoses
- B60T17/046—Devices for pipe guiding and fixing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/008—Amphibious sea planes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Braking Arrangements (AREA)
- Valves And Accessory Devices For Braking Systems (AREA)
Abstract
The invention relates to a brake oil circuit structure of an amphibious aircraft, and belongs to the field of overall arrangement of aircrafts. The emergency brake system comprises an emergency brake upper hard conduit, a normal brake upper hard conduit, two groups of emergency brake rotary joints, a normal brake middle hard conduit, a normal brake hose, a normal lower hard conduit, an emergency brake lower hard conduit, a main undercarriage strut, an emergency brake hose, a main undercarriage front and rear rotary shaft, a main undercarriage lateral rotary shaft, four brackets, an emergency brake middle hard conduit, two groups of normal brake rotary joints and a main lifting fairing; the invention can avoid torsion in the movement process of only using the hydraulic hose, changes the complex movement track in the movement process of the undercarriage into circumferential and lateral movement, and can effectively prevent the hydraulic pipeline from being damaged by bird collision because the normal brake pipeline is completely arranged in the structural protection area in the main lifting fairing and the rear area of the main undercarriage along the heading direction, and can also effectively prevent the influence caused by tire explosion because the normal brake and the emergency brake are arranged in different channels.
Description
Technical Field
The invention relates to a brake oil circuit structure of an amphibious aircraft, and belongs to the field of overall arrangement of aircrafts.
Background
The safety requirement of the aircraft brake system is high, and under the condition that specific risks such as tire explosion, bird collision and the like are considered, higher isolation requirements are required to be provided for brake pipeline arrangement on a main landing gear fairing and a landing gear support. Therefore, an arrangement method is needed to be provided, and normal brake and emergency brake pipelines are reasonably arranged under the condition of meeting the complex movement track of the undercarriage, so that various functions, performances and safety requirements are met. The traditional hydraulic hose is used for transmitting a hydraulic oil path at a moving part, so that torsion can be generated, and the use requirement of the hose can not be met.
Disclosure of Invention
The invention aims to overcome the defects that hose transmission is easy to twist and the requirement of oil circuit transmission under a complex movement track cannot be met, and provides a brake oil circuit structure suitable for an amphibious aircraft.
A brake oil circuit structure of an amphibious aircraft comprises an emergency brake upper hard conduit 1, a normal brake upper hard conduit 2, two groups of emergency brake rotary joints 3, a normal brake middle hard conduit 4, a support I5, a normal brake hose 6, a support II 7, a normal lower hard conduit 8, a support III 9, an emergency brake lower hard conduit 10, a main undercarriage strut 11, an emergency brake hose 12, a main undercarriage front and rear rotating shaft 13, a main undercarriage lateral rotating shaft 14, a support IV 15, an emergency brake middle hard conduit 16, two groups of normal brake rotary joints 17 and a main lifting fairing 18; the upper ends of an emergency brake rotary joint 3 and a normal brake rotary joint 17 are connected with an emergency brake upper hard conduit 1 and a normal brake upper hard conduit 2 through a main lifting fairing 18, the lower ends of the emergency brake rotary joint 3 and the normal brake rotary joint 17 are arranged on a support frame four 15, the support frame four 15 is fixed on a main undercarriage rotating shaft 14, one path of the lower end of the normal brake rotary joint 17 is transited to a support frame one 5 through a normal brake middle hard conduit 4, the oil path of the normal brake rotary joint 17 is led to a support frame two 7 through a normal brake hose 6, and the oil path is transmitted to a normal lower hard conduit 8 through a pipe joint on the support frame two 7; the lower end of the emergency brake rotary joint 3 is transmitted to a fixed pipe joint on a fourth support 15 through a hard pipe 16 in 2 paths of emergency brakes, the oil path of the emergency brake rotary joint 3 is led to a third support 9 through an emergency brake hose 12, the oil path is transmitted to an emergency lower reaction pipe 10 through a pipe joint on the third support 9, a front rotating shaft 13 and a rear rotating shaft 13 of the main undercarriage are installed on a main undercarriage support post 11, and the third support 9 and the second support 7 are installed at the left end and the right end of the main undercarriage support post 11 respectively.
The emergency brake rotary joint 3 and the normal brake rotary joint 17 move around the circumference of the main landing gear rotating shaft 13.
The normal brake hose 6 and the emergency brake hose 12 move laterally along the main landing gear lateral rotation axis 14.
The normal brake hose 6 and the emergency brake hose 12 move circumferentially with the main landing gear leg 11 about the main landing gear fore-aft axis of rotation 13.
Each group of emergency brake rotary joint 3 and normal brake rotary joint 17 has the same structure and is composed of 3 relative motion joints, and the two ends of the emergency brake rotary joint are provided with mounting fixed points for the rotary joints to be arranged on the four brackets 15 and the main starting fairing 18.
The fourth bracket 15 is an L-shaped plate-shaped structure, is fixedly mounted on the main landing gear lateral rotating shaft 14, and moves along with the main landing gear lateral rotating shaft 14.
The normal brake medium hard conduit 4, the normal lower hard conduit 8, the emergency brake medium hard conduit 10 and the emergency brake medium hard conduit 16 are all 2169 stainless steel pipes for transmitting brake oil passages to the brake device.
The normal brake hose 6 and the emergency brake hose 12 are polytetrafluoroethylene hoses and are used for brake oil path transmission under single-plane motion between the third support 9 and the fourth support 15, between the second support 7 and the fourth support 15 and between the first support 5 and the second support 7;
the main landing gear strut 11 is a main fulcrum of the aircraft, is fixed on the aircraft body through a main landing gear front and rear rotating shaft 13, is retracted backwards, clings to the aircraft body and is stored in a landing gear fairing.
The emergency brake rotary joint 3 and the normal brake rotary joint 17 are kept relatively static with the airplane body.
The invention has the advantages that: the invention can avoid torsion in the movement process of only using the hydraulic hose, changes the complex movement track in the movement process of the undercarriage into circumferential and lateral movement, and can effectively prevent the hydraulic pipeline from being damaged by bird collision because the normal brake pipeline is completely arranged in the structural protection area in the main starting fairing and the rear area of the main undercarriage along the heading direction, and can effectively prevent the influence caused by tire explosion because the normal brake and the emergency brake are arranged in different channels, thereby being mainly suitable for the amphibious aircraft and other types of aircraft.
Drawings
Figure 1 is a front view of the oil circuit structure of the present invention,
FIG. 2 is a view showing the structure of the oil passage of the present invention in the direction of A
1-hard conduit on emergency brake, 2-hard conduit on normal brake, 3-rotary joint on emergency brake, 4-hard conduit in normal brake, 5-first support, 6-soft hose on normal brake, 7-second support, 8-hard conduit under normal brake, 9-third support, 10-hard conduit under emergency brake, 11-main landing gear support, 12-soft hose on emergency brake, 13-front and rear rotating shaft of main landing gear, 14-lateral rotating shaft of main landing gear, 15-fourth support, 16-hard conduit in emergency brake, 17-rotary joint on normal brake, 18-main fairing.
Detailed Description
The invention is further described below with reference to the accompanying drawings. (this part is the most complete part of the present invention, and covers all the contents including technical solutions, functions, actions, and the like, all of which can be written in)
As shown in fig. 1-2, the brake oil circuit structure of the amphibious aircraft comprises an emergency brake upper hard conduit 1, a normal brake upper hard conduit 2, an emergency brake rotary joint 3, a normal brake middle hard conduit 4, a support I5, a normal brake hose 6, a support II 7, a normal lower hard conduit 8, a support III 9, an emergency brake lower hard conduit 10, a main landing gear support 11, an emergency brake hose 12, a main landing gear front and rear rotary shaft 13, a main landing gear lateral rotary shaft 14, a support IV 15, an emergency brake middle hard conduit 16, a normal brake rotary joint 17 and a main lifting fairing 18; the emergency brake rotary joint 3 and the normal brake rotary joint 17 are connected with the emergency brake upper hard conduit 1 and the normal brake upper hard conduit 2 through the main lifting fairing 18, the emergency brake rotary joint 3 and the normal brake rotary joint 17 are arranged at the lower end of the support four 15, the support four 15 is fixed on the main undercarriage rotating shaft 14, when the main undercarriage is retracted and extended, the main undercarriage is driven by the front rotating shaft 13 and the rear rotating shaft 13, and the emergency brake rotary joint 3 and the normal brake rotary joint 17 move circumferentially relative to the undercarriage. One path of the lower end of the normal braking rotary joint 17 is transited to the first bracket 5 through the hard pipe 4 in normal braking, the oil path of the normal braking rotary joint 17 is led to the second bracket 7 through the normal braking hose 6 and is transmitted to the hard pipe 8 in normal braking through the pipe joint on the second bracket 7, and the normal braking hose 6 moves laterally around the lateral rotating shaft 14 of the main landing gear.
The lower end of the emergency brake rotary joint 3 is transmitted to a fixed pipe joint on a fourth support 15 through a hard pipe 16 in the 2-way emergency brake, the oil way of the emergency brake rotary joint 16 is led to a third support 9 through an emergency brake hose 12, the oil way is transmitted to an emergency lower reaction pipe 10 through the pipe joint on the third support 9, and the emergency brake hose 12 moves laterally around a lateral rotating shaft 14 of the main landing gear.
The brake oil path arrangement method comprises a pipeline part and a pipeline supporting part, wherein the transmission path of the normal brake oil path is a normal brake upper hard conduit 2 → a normal brake rotary joint 17 → a normal brake middle hard conduit 4 → a normal brake hose 6 → a normal brake lower hard conduit 8, and the normal brake oil path comprises 2 oil paths; the emergency brake oil path transmission path is an emergency brake upper hard conduit 1 → a normal brake rotary joint 3 → an emergency brake middle hard conduit 16 → an emergency brake hose 12 → a normal lower hard conduit 10, and the emergency brake oil path comprises 2 oil paths.
The support supporting part consists of a first support 5, a second support 7, a third support 9, a fourth support 15 and a main lifting fairing 18; the landing gear is in the process of retracting, the landing gear moves circumferentially around a front rotating shaft 13 and a rear rotating shaft 13 of the main landing gear and moves laterally around a lateral rotating shaft 13 of the main landing gear, in the process of moving the landing gear, the lower ends of the emergency brake rotary joint 3 and the normal brake rotary joint, the hard pipes 4 in normal brake, the first support 5, the fourth support 15 and the hard pipes 16 in emergency brake all move circumferentially around the front rotating shaft 13 and the rear rotating shaft of the main landing gear, the normal brake hose 6, the second support 7, the hard pipes 8 in normal brake, the third support 9, the hard pipes 10 in emergency brake and the main landing gear strut 11 all move laterally around the lateral rotating shaft 13 of the main landing gear.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. A brake oil circuit structure of an amphibious aircraft is characterized by comprising an emergency brake upper hard conduit (1), a normal brake upper hard conduit (2), two groups of emergency brake rotary joints (3), a normal brake middle hard conduit (4), a support I (5), a normal brake hose (6), a support II (7), a normal lower hard conduit (8), a support III (9), an emergency brake lower hard conduit (10), a main undercarriage strut (11), an emergency brake hose (12), a main undercarriage front and rear rotary shaft (13), a main undercarriage lateral rotary shaft (14), a support IV (15), an emergency brake middle hard conduit (16), two groups of normal brake rotary joints (17) and a main lifting fairing (18); the upper ends of an emergency brake rotary joint (3) and a normal brake rotary joint (17) are connected with an emergency brake upper hard conduit (1) and a normal brake upper hard conduit (2) through a main lifting fairing (18), the lower ends of the emergency brake rotary joint (3) and the normal brake rotary joint (17) are installed on a support frame four (15), the support frame four (15) is fixed on a main undercarriage rotating shaft (14), one path of the lower end of the normal brake rotary joint (17) is transited to a support frame one (5) through a normal brake middle hard conduit (4), an oil path of the normal brake rotary joint (17) is led to a support frame two (7) through a normal brake hose (6), and is transmitted to a normal lower hard conduit (8) through a pipe joint on the support frame two (7); the lower end of the emergency brake rotary joint (3) is transmitted to the fixed pipe joint on the support four (15) through two paths of emergency brake medium-hard guide pipes (16), the oil way of the emergency brake rotary joint (3) is led to the support three (9) through an emergency brake hose (12), the emergency brake rotary joint is transmitted to an emergency lower reaction guide pipe (10) through a pipe joint on the support three (9), a front rotary shaft (13) and a rear rotary shaft (13) of a main undercarriage are installed on a main undercarriage supporting column (11), and the support three (9) and the support two (7) are installed at the left end and the right end of the main undercarriage supporting column (11) respectively.
2. An amphibious aircraft brake oil circuit structure according to claim 1, characterised in that said emergency brake swivel (3) and normal brake swivel (17) move circumferentially around the main landing gear rotation axis (13).
3. An amphibious aircraft brake circuit configuration according to claim 1, where said normal brake hose (6) and emergency brake hose (12) are moved laterally along the main landing gear lateral pivot axis (14).
4. An amphibious aircraft brake circuit configuration according to claim 1, where said normal brake hose (6) and emergency brake hose (1)2 move circumferentially about the main landing gear fore and aft axis of rotation (13) with the main landing gear leg (11).
5. An amphibious aircraft brake oil circuit structure according to claim 1, wherein each group of emergency brake swivel (3) and normal brake swivel (17) is identical in structure and comprises 3 relatively moving joints, and mounting fixing points are arranged at two ends of each group of emergency brake swivel and normal brake swivel for mounting the swivels on the bracket four (15) and the main starting fairing (18).
6. An amphibious aircraft brake oil circuit structure according to claim 1, wherein bracket four (15) is an L-shaped plate structure, fixedly mounted on the main landing gear lateral rotation shaft (14), and moves along with the main landing gear lateral rotation shaft (14).
7. The brake oil circuit structure of an amphibious aircraft according to claim 1, wherein the normal brake medium hard conduit (4), the normal lower hard conduit (8), the emergency brake lower hard conduit (10) and the emergency brake medium hard conduit (16) are all 2169 stainless steel pipes.
8. The brake oil circuit structure of an amphibious aircraft according to claim 1, wherein the normal brake hose (6) and the emergency brake hose (12) are polytetrafluoroethylene hoses for brake oil circuit transmission under single-plane motion between the third bracket (9) and the fourth bracket (), between the second bracket (7) and the fourth bracket (15), and between the first bracket (5) and the second bracket (7).
9. An amphibious aircraft brake oil circuit structure according to claim 1, wherein the main landing gear strut (11) is a main pivot of the aircraft, is fixed on the aircraft body through a main landing gear front and rear rotating shaft (13), and is retracted backwards, clings to the aircraft body and is stored in the landing gear fairing.
10. An amphibious aircraft brake oil circuit structure according to claim 1, wherein the emergency brake swivel 3 and the normal brake swivel 17 are held stationary relative to the aircraft body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111169064.0A CN113830295B (en) | 2021-09-30 | 2021-09-30 | Amphibious aircraft brake oil circuit structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111169064.0A CN113830295B (en) | 2021-09-30 | 2021-09-30 | Amphibious aircraft brake oil circuit structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113830295A true CN113830295A (en) | 2021-12-24 |
| CN113830295B CN113830295B (en) | 2023-04-14 |
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ID=78968296
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111169064.0A Active CN113830295B (en) | 2021-09-30 | 2021-09-30 | Amphibious aircraft brake oil circuit structure |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB606079A (en) * | 1946-04-10 | 1948-08-05 | Martin James | Operating aircraft landing gear |
| FR981654A (en) * | 1949-01-07 | 1951-05-29 | Siam | Improvements to the pipes of aircraft braking systems |
| GB732924A (en) * | 1952-10-23 | 1955-06-29 | Dowty Equipment Ltd | Improvements relating to conduits for fluid-operated brakes on aircraft multi-wheel bogie undercarriages |
| CN108058816A (en) * | 2017-11-03 | 2018-05-22 | 中航通飞研究院有限公司 | A kind of undercarriage hydraulic system |
| EP3527489A1 (en) * | 2018-02-20 | 2019-08-21 | Airbus Operations, S.L.U. | Hydraulic system for an aircraft |
| CN211252552U (en) * | 2019-12-30 | 2020-08-14 | 贵州通用航空有限责任公司 | Oil pipeline hidden strutting arrangement for aircraft that stops |
| CN112061382A (en) * | 2020-09-11 | 2020-12-11 | 中航飞机起落架有限责任公司 | Frame formula undercarriage brake hose connection structure |
-
2021
- 2021-09-30 CN CN202111169064.0A patent/CN113830295B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB606079A (en) * | 1946-04-10 | 1948-08-05 | Martin James | Operating aircraft landing gear |
| FR981654A (en) * | 1949-01-07 | 1951-05-29 | Siam | Improvements to the pipes of aircraft braking systems |
| GB732924A (en) * | 1952-10-23 | 1955-06-29 | Dowty Equipment Ltd | Improvements relating to conduits for fluid-operated brakes on aircraft multi-wheel bogie undercarriages |
| CN108058816A (en) * | 2017-11-03 | 2018-05-22 | 中航通飞研究院有限公司 | A kind of undercarriage hydraulic system |
| EP3527489A1 (en) * | 2018-02-20 | 2019-08-21 | Airbus Operations, S.L.U. | Hydraulic system for an aircraft |
| CN211252552U (en) * | 2019-12-30 | 2020-08-14 | 贵州通用航空有限责任公司 | Oil pipeline hidden strutting arrangement for aircraft that stops |
| CN112061382A (en) * | 2020-09-11 | 2020-12-11 | 中航飞机起落架有限责任公司 | Frame formula undercarriage brake hose connection structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113830295B (en) | 2023-04-14 |
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