CN103818549A - Automatic hydraulic braking pressure supply device for unmanned aerial vehicle - Google Patents
Automatic hydraulic braking pressure supply device for unmanned aerial vehicle Download PDFInfo
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- CN103818549A CN103818549A CN201210464139.2A CN201210464139A CN103818549A CN 103818549 A CN103818549 A CN 103818549A CN 201210464139 A CN201210464139 A CN 201210464139A CN 103818549 A CN103818549 A CN 103818549A
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- brake
- valve
- oil
- hydraulic pump
- hydraulic
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Abstract
The invention belongs to an unmanned aerial vehicle hydraulic technology, and relates to an automatic hydraulic braking pressure supply device for an unmanned aerial vehicle. The device comprises a hydraulic oil tank (1), a hydraulic constant delivery pump (2), a variable frequency motor (3), an oil filter (4), a brake valve (5), an overflow valve (6), a brake sensor (7) and an brake actuating cylinder (8), wherein a driving shaft of the hydraulic constant delivery pump (2) is connected with an output shaft of the variable frequency motor (3); an oil suction port of the hydraulic constant delivery pump (2) is connected with the oil tank (1); an oil outlet of the hydraulic constant delivery pump (2) is simultaneously connected with one end of the oil filter (4) and the overflow valve (6); the other end of the overflow valve (6) is connected with the oil tank (1); the other end of the oil filter (4) is connected with an inlet of the brake valve (5); an outlet of the brake valve (5) is connected with the brake sensor (7) and one end of the brake actuating cylinder (8) respectively. According to the device, the brake valve is low in cost, and has low requirements on the accuracy of oil, so that the device is low in failure rate and cost.
Description
Technical field
The invention belongs to unmanned plane hydraulic technique, relate to a kind of unmanned plane automatic hydraulic brake for pressure device.
Background technology
In existing unmanned plane brake gear, the general electrohydraulic control servo hydraulic system that adopts, come flow and the pressure of control system by controlling the opening of electrohydraulic servo valve and realize brake, this structural weight weight, complex structure, in the situation that not braking, pump idle running, by the off-load of electrohydraulic servo valve meta, Hydraulic Pump long-term work, affects life-span of Hydraulic Pump.This mode has 3 drawbacks:
(1) installation site is limited: hydraulic pump shaft must be connected with engine shaft, the nonoptional leeway, position of Hydraulic Pump, and the connection technological requirement of hydraulic pump shaft and engine shaft is high.
(2) the Hydraulic Pump race time is long: in not braking, Hydraulic Pump, also in idling conditions, has affected the efficiency of driving engine and the life-span of Hydraulic Pump.
(3) electrohydraulic servo valve is high to fluid accuracy requirement, and system failure rate is high, and cost is more expensive.
Summary of the invention
The technical problem to be solved in the present invention:
The object of the invention is to propose a kind of long service life, the unmanned plane automatic hydraulic brake that simple in structure, cost is low, installation site is not limited for pressure device.Technical solution of the present invention is, unmanned plane water brake comprises variable-frequency motor, quantitative hydraulic pump, oily filter, by pass valve, brake valve, brake pressure sensor and braking action cylinder for pressure device, the power of quantitative hydraulic pump is from variable-frequency motor, the axle drive shaft of quantitative hydraulic pump connects in variable-frequency motor, quantitative hydraulic pump oil suction is connected with fuel tank, the force feed mouth of quantitative hydraulic pump joins with one end and the by pass valve of oil filter, the other end of oil filter is connected with the entrance of brake valve, and the outlet of brake valve is connected with one end of brake pressure sensor and braking action cylinder respectively.The rotating speed of wheel is monitored by speed sensor, the rotating speed of variable-frequency motor, and the open and close of brake valve are by system for flight control computer control.
Technical scheme of the present invention:
The brake of unmanned plane automatic hydraulic is for pressure device, this device comprises hydraulic reservoir 1, quantitative hydraulic pump 2, variable-frequency motor 3, oil filter 4, brake valve 5, by pass valve 6, brake sensor 7, braking action cylinder 8, wherein, the axle drive shaft of quantitative hydraulic pump 2 is connected with the output shaft of variable-frequency motor 3, quantitative hydraulic pump 2 oil suctions are connected with fuel tank 1, the oil outlet of quantitative hydraulic pump 2 joins with one end and the by pass valve 6 of oil filter 4 simultaneously, the other end of by pass valve 6 is connected with fuel tank 1, the other end of oil filter 4 is connected with the entrance of brake valve 5, the outlet of brake valve 5 is connected with one end of brake pressure sensor 7 and braking action cylinder 8 respectively.Beneficial effect of the present invention:
The brake of unmanned plane automatic hydraulic is that pressure source is realized brake for the quantitative hydraulic pump of pressure device variable-frequency motor control, and the axle drive shaft of quantitative hydraulic pump does not need to be connected with engine shaft, and this connection mode is simple, and the position of brake gear is unrestricted.Unlatching and the delivery rate of controlling quantitative hydraulic pump by controlling the output speed of variable-frequency motor, energy consumption is low.Be equipped with pressure sensor and survey brake pressure, assurance chaufeur can be understood the real time information of brake gear.This brake gear has selected cost low, the brake valve low to fluid accuracy requirement, and therefore, this plant failure rate is low, and cost is low.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.Wherein, 1 is that hydraulic reservoir, 2 is that quantitative hydraulic pump, 3 is that variable-frequency motor, 4 is that oil filter, 5 is that brake valve, 6 is that by pass valve, 7 is that brake sensor, 8 is braking action cylinder.
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is elaborated.The brake of unmanned plane automatic hydraulic comprises hydraulic reservoir 1 for pressure device, quantitative hydraulic pump 2, variable-frequency motor 3, oil filter 4, brake valve 5, by pass valve 6, brake sensor 7, braking action cylinder 8, the axle drive shaft of quantitative hydraulic pump 2 connects in the output shaft of variable-frequency motor 3, and quantitative hydraulic pump 2 oil suctions are connected with fuel tank 1, and the oil outlet of quantitative hydraulic pump 2 joins with one end and the by pass valve 6 of oil filter 4, the other end of oil filter 4 is connected with the entrance of brake valve 5, and the outlet of brake valve 5 is connected with one end of brake pressure sensor 7 and braking action cylinder 8 respectively.
Water brake supplies pressure device pressure from quantitative hydraulic pump 2, the axle drive shaft of quantitative hydraulic pump 2 connects in the output shaft of variable-frequency motor 3, the change of the output shaft rotating speed of variable-frequency motor 3 changes the drive shaft speed of quantitative hydraulic pump 2, thereby has controlled the flow of quantitative hydraulic pump 2.In the time that flight control system is sent brake instruction, variable-frequency motor 3 starts, quantitative hydraulic pump 2 pressure oil output, and brake valve 5 is changed, and pressure oil enters braking action cylinder 8 by brake valve 5, realizes brake.Brake is experienced brake pressure for the pressure sensor 7 in pressure device, and by pass valve 6 guarantees not overvoltage of brake gear.
The speed sensor of installing on wheel braking is experienced wheel speed, and this speed is fed back to flight control system, according to the output shaft rotating speed of controlled reset variable-frequency motor 3, meets thereby change the flow of quantitative hydraulic pump 2 requirement of braking by flight control system.
Claims (1)
1. the brake of unmanned plane automatic hydraulic is for pressure device, it is characterized in that, this device comprises hydraulic reservoir (1), quantitative hydraulic pump (2), variable-frequency motor (3), oil filter (4), brake valve (5), by pass valve (6), brake sensor (7), braking action cylinder (8), wherein, the axle drive shaft of quantitative hydraulic pump (2) is connected with the output shaft of variable-frequency motor (3), quantitative hydraulic pump (2) oil suction is connected with fuel tank (1), the oil outlet of quantitative hydraulic pump (2) joins with one end and the by pass valve (6) of oil filter (4) simultaneously, the other end of by pass valve (6) is connected with fuel tank (1), the other end of oil filter (4) is connected with the entrance of brake valve (5), the outlet of brake valve (5) is connected with one end of brake pressure sensor (7) and braking action cylinder (8) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210464139.2A CN103818549A (en) | 2012-11-16 | 2012-11-16 | Automatic hydraulic braking pressure supply device for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210464139.2A CN103818549A (en) | 2012-11-16 | 2012-11-16 | Automatic hydraulic braking pressure supply device for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103818549A true CN103818549A (en) | 2014-05-28 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210464139.2A Pending CN103818549A (en) | 2012-11-16 | 2012-11-16 | Automatic hydraulic braking pressure supply device for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN103818549A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2531866A (en) * | 2014-08-15 | 2016-05-04 | Gulfstream Aerospace Corp | Apparatus and method for controlling a hydraulic brake of an aircraft |
| CN109017726A (en) * | 2018-07-24 | 2018-12-18 | 东南大学 | A kind of automatic driving vehicle general brake system and control method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB757705A (en) * | 1953-04-02 | 1956-09-26 | Electro Hydraulics Ltd | Fluid pressure operated systems |
| GB2344390A (en) * | 1998-12-03 | 2000-06-07 | Toyota Motor Co Ltd | A hydraulic braking system wherein a pump motor PWM frequency is below or above the upper audibility limit depending on the braking conditions. |
| CN1391146A (en) * | 2002-07-23 | 2003-01-15 | 浙江大学 | Electro-hydraulic control system and method based on frequency-conversion speed regulation |
| CN102092472A (en) * | 2011-01-20 | 2011-06-15 | 北京航空航天大学 | Self-energy feeding type brake device for airplanes |
| CN102442430A (en) * | 2011-11-01 | 2012-05-09 | 哈尔滨飞机工业集团有限责任公司 | Aircraft hydraulic anti-skid braking pressure supply device |
-
2012
- 2012-11-16 CN CN201210464139.2A patent/CN103818549A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB757705A (en) * | 1953-04-02 | 1956-09-26 | Electro Hydraulics Ltd | Fluid pressure operated systems |
| GB2344390A (en) * | 1998-12-03 | 2000-06-07 | Toyota Motor Co Ltd | A hydraulic braking system wherein a pump motor PWM frequency is below or above the upper audibility limit depending on the braking conditions. |
| CN1391146A (en) * | 2002-07-23 | 2003-01-15 | 浙江大学 | Electro-hydraulic control system and method based on frequency-conversion speed regulation |
| CN102092472A (en) * | 2011-01-20 | 2011-06-15 | 北京航空航天大学 | Self-energy feeding type brake device for airplanes |
| CN102442430A (en) * | 2011-11-01 | 2012-05-09 | 哈尔滨飞机工业集团有限责任公司 | Aircraft hydraulic anti-skid braking pressure supply device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2531866A (en) * | 2014-08-15 | 2016-05-04 | Gulfstream Aerospace Corp | Apparatus and method for controlling a hydraulic brake of an aircraft |
| GB2531866B (en) * | 2014-08-15 | 2018-01-03 | Gulfstream Aerospace Corp | Apparatus and method for controlling a hydraulic brake of an aircraft |
| CN109017726A (en) * | 2018-07-24 | 2018-12-18 | 东南大学 | A kind of automatic driving vehicle general brake system and control method |
| CN109017726B (en) * | 2018-07-24 | 2020-12-01 | 东南大学 | Universal braking system for unmanned vehicle and control method |
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Application publication date: 20140528 |