CN101585411A - Hydraulic servo steering engine system - Google Patents
Hydraulic servo steering engine system Download PDFInfo
- Publication number
- CN101585411A CN101585411A CNA2009100599498A CN200910059949A CN101585411A CN 101585411 A CN101585411 A CN 101585411A CN A2009100599498 A CNA2009100599498 A CN A2009100599498A CN 200910059949 A CN200910059949 A CN 200910059949A CN 101585411 A CN101585411 A CN 101585411A
- Authority
- CN
- China
- Prior art keywords
- rudderpost
- steering engine
- servovalve
- hydraulic servo
- oil cylinder
- 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.)
- Granted
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- 238000006073 displacement reaction Methods 0.000 claims abstract description 6
- 239000002828 fuel tank Substances 0.000 description 8
- 239000012530 fluid Substances 0.000 description 5
- 238000009434 installation Methods 0.000 description 2
- 241000380131 Ammophila arenaria Species 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000004301 light adaptation Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000003068 static Effects 0.000 description 1
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Abstract
A hydraulic servo steering engine system belongs to the steering engine device of an aircraft. A direct current motor is fixed on a machine core, the direct current motor is connected with a hydraulic pump, a flow channel and an oil cavity are cast inside the machine core, and the oil cavity is interconnected. Four servo valves are mounted on the machine core axially and symmetrically, each servo valve is respectively connected with an oil cylinder, the piston rod of the oil cylinder is hinged with a connecting rod which is hinged with a rudderpost, the rudderpost is connected with an angular displacement sensor which is connected with a controller, and the controller is connected with the servo valves to form a one-to-four hydraulic servo control system. The invention has new principle, highly integrated structure, small volume, light weight, quick response and high reliability, and is applicable to different severe environments.
Description
Technical field:
Hydraulic servo steering engine system, the helm gear of genus aircraft.
Background technology:
Steering gear system is indispensable key components in the flight control system.Steering wheel is the actuating unit of controlling aircraft state of flight, and its manoevreability to aircraft plays a decisive role.The instruction that its executive control system is sent, the deflection of the control vane wing produces moment, and stable and controlling aircraft makes it fly by setting path.
Along with the development of some aircraft new product, some aircraft steering engine is had higher requirement: the operating environment that volume is little, in light weight, the response fast, micro-manipulation, adaptation are abominable, good dynamic and static performance, high reliability etc.Particularly very harsh requirement has been proposed for volume, weight.The steering gear system such as hydraulic efficiency servo, pneumatic servo or the DC machine Fu that have traditional aircraft now all can not well satisfy these requirements.
Summary of the invention:
The problem to be solved in the present invention is exactly to provide a kind of at above deficiency and has the principle novelty, system height is integrated, volume is little, in light weight, response is fast, reliability is high, can satisfy the steering gear system of harsh environment.Its technical scheme is as follows:
It is a fixing DC machine on movement, and DC machine connects Hydraulic Pump, at movement cast inside runner and oil pocket, and oil pocket is communicated with.Radial symmetry is installed four servovalves on movement, each servovalve all connects oil cylinder separately, the piston rod articulated linkage of oil cylinder, the rod hinge connection rudderpost, rudderpost joint angle displacement pickup, angular-motion transducer connects controller, and controller is connected with servovalve, constitutes the hydraulic servo control system of " drags four ".
Compared with prior art the beneficial effect that has of the present invention is:
1, principle of the invention novelty, system is with the installation basis of movement as whole steering wheel element, adopting a motor and a Hydraulic Pump to drive four rudderposts simultaneously rotates, the i.e. Closed Hydraulic servo control unit of " drags four ", each element, runner, fuel tank height are integrated on the movement, and no hydraulic pipe road has simplified system greatly, height lightweight and miniaturization can be realized, and the reliability of system can be improved;
2, owing to adopted the Hydraulic Servo Control and the simple mechanical linkage of high response, messenger chain is very short, and power circuit is few through element, and the response of system response and DC machine, Hydraulic Pump is irrelevant, can realize the height response control of system;
3, because the action of each rudderpost all is independently to be controlled by cover servovalve, oil cylinder, connecting rod mechanism, angular-motion transducer separately fully, the control that guarantees the action of each rudderpost all is independently.
4, the system of each rudderpost action of independent control forms big closed loop by servovalve, angular-motion transducer, oil cylinder etc., form little closed loop by servovalve and himself controller, the big nested little closed loop of closed loop, constitute two closed loop servo controls, can feed back, compensate the rudder displacement error, realize the accuracy control of rudder displacement;
5, because system adopts the hydraulic closed system, and pressure compensator has been installed on fuel tank, the air bag of pressure compensator places fuel tank, pressure compensator can dash venting to its air bag by valve, make gasbag pressure keep certain value, thereby make the pressure of fuel tank fluid keep certain limit, make system's oil suction pressure not be subjected to the influence of aerial huge pressure variation on the one hand, can in time compensate the fluid volume that fuel tank causes because of system's leakage of oil and the variation of pressure on the other hand, thereby guarantee that whole hydraulic efficiency servo is not subjected to the influence of aircraft environment air pressure conditions, has improved the stability of system;
Description of drawings:
Fig. 1 is a structure principle chart of the present invention;
Fig. 2 is a structural representation of the present invention;
Fig. 3 is the left-hand view of Fig. 2;
Fig. 4 is the dextrad view of Fig. 2;
Fig. 5 is the Z-Z view of Fig. 4.
1 is DC machine among the figure, the 2nd, and oil cylinder, the 3rd, piston rod, the 4th, connecting rod, the 5th, rudderpost, the 6th, angular-motion transducer, the 7th, Hydraulic Pump, the 8th, servovalve, the 9th, movement, the 10th, oil pocket, the 11st, air bag, the 12nd, pressure compensator, the 13rd, valve, the 14th, by pass valve, the 15th, controller, the 16th, shell.
The specific embodiment:
Referring to accompanying drawing, the present invention passes through fixedly DC machine 1 of shell 16 on movement 9, movement 9 is a foundry goods, it is the installation basis of whole steering wheel element, DC machine 1 connects Hydraulic Pump 7, specifically is that the shell of Hydraulic Pump 7 links to each other with the motor housing pin or directly integrated (being not limited thereto the form that is connected).At a plurality of runners of movement 9 cast inside and oil pocket 10, oil pocket 10 is as the fuel tank of hydraulic efficiency pressure system.Radial symmetry is installed four servovalves 8 on movement 9, each servovalve 8 all connects oil cylinder 2 separately, oil cylinder 2 is fixed on the movement 9, piston rod 3 articulated linkage 4 of oil cylinder, connecting rod 4 hinged rudderposts 5, rudderpost 5 radial symmetry are installed on the movement 9, can rotate relative to movement 9, rudderpost 5 joint angle displacement pickups 6, angular-motion transducer 6 connects controller 15, controller 15 is connected with servovalve 8, and thread cartridge by pass valve 14 also is installed on movement 9.Servovalve 8, angular-motion transducer 6, oil cylinder 2, connecting rod 4, rudderpost 5 constitute the moving system of each rudderpost, the moving system of each rudderpost is formed big closed loop by servovalve 8, angular-motion transducer 6, oil cylinder 2, connecting rod 4, rudderpost 5, form little closed loop by servovalve 8 and himself controller, the big nested little closed loop of closed loop constitutes two closed loop servo-control systems.Each runner is communicated with each Hydraulic Elements oil cylinder 2, servovalve 8, Hydraulic Pump 7, oil pocket 10, by pass valve 14 according to Fig. 1, and also has runner to be communicated with between each oil pocket 10.Controller 15 is fixedly mounted on gap in the steering wheel shell 16 (as the gap location of servovalve).Pressure compensator 12 is housed on oil pocket 10, pressure compensator 12 comprises air bag 11 and the valve 13 that is installed on the air bag 11, air bag 11 places oil pocket 10, the air inlet/outlet of valve 13 is positioned on the shell, can dash venting to its air bag 11 by valve 13, make air bag 11 pressure keep certain value, thereby make the pressure of fuel tank fluid keep certain limit, make system's oil suction pressure not be subjected to the influence of aerial huge pressure variation on the one hand, can in time compensate the fluid volume that fuel tank causes because of system's leakage of oil and the variation of pressure on the other hand, thereby guarantee that whole hydraulic efficiency servo is not subjected to the influence of aircraft environment air pressure conditions, has improved the stability of system.
Working process of the present invention is: DC machine 1 drives Hydraulic Pump 7 to system's fuel feeding, give servovalve 8 instructions by controller 15, opening by control servovalve 8, the fluid that control enters oil cylinder 2 flows to and flow, thereby control oil cylinder piston bar 3 stretches out, retraction speed, piston rod drivening rod 4 promotes rudderpost 5 and rotates, and the deflection speed of rudderpost and deflecting direction are determined by the servovalve flow.Four servovalves can be realized the independent control of four rudderposts.
Claims (6)
1, a kind of hydraulic servo steering engine system, it is characterized in that going up fixedly DC machine (1) at movement (9), DC machine (1) connects Hydraulic Pump (7), at movement (9) cast inside runner and oil pocket (10), go up radial symmetry at movement (9) four servovalves (8) are installed, each servovalve (8) all connects oil cylinder (2) separately, the piston rod of oil cylinder (3) articulated linkage (4), the hinged rudderpost of connecting rod (4) (5), rudderpost (5) joint angle displacement pickup (6), angular-motion transducer (6) connects controller (15), and controller (15) is connected with servovalve (8), constitutes the hydraulic servo control system of " drags four ".
2,, it is characterized in that rudderpost (5) radial symmetry is installed on the movement (9) according to the described hydraulic servo steering engine system of claim 1.
3,, it is characterized in that on movement (9), being equipped with by pass valve (14) according to the described hydraulic servo steering engine system of claim 1.
4, according to the described hydraulic servo steering engine system of claim 1, it is characterized in that on oil pocket (10), being equipped with pressure compensator (12), pressure compensator (12) comprises air bag (11) and is installed in valve (13) on the air bag (11), air bag (11) places oil pocket (10), and the air inlet/outlet of valve (13) is positioned on the shell.
5,, it is characterized in that each runner is communicated with each Hydraulic Elements oil cylinder (2), servovalve (8), Hydraulic Pump (7), oil pocket (10), by pass valve (14) according to claim 1 or 3 described hydraulic servo steering engine systems.
6, according to the described hydraulic servo steering engine system of claim 1, it is characterized in that servovalve (8), angular-motion transducer (6), oil cylinder (2), connecting rod (4), rudderpost (5) constitute the moving system of each rudderpost, the moving system of each rudderpost is formed big closed loop by servovalve (8), angular-motion transducer (6), oil cylinder (2), connecting rod (4), rudderpost (5), form little closed loop by servovalve (8) and himself controller, the big nested little closed loop of closed loop constitutes two closed loop servo-control systems.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100599498A CN101585411B (en) | 2009-07-10 | 2009-07-10 | Hydraulic servo steering engine system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100599498A CN101585411B (en) | 2009-07-10 | 2009-07-10 | Hydraulic servo steering engine system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101585411A true CN101585411A (en) | 2009-11-25 |
| CN101585411B CN101585411B (en) | 2011-04-13 |
Family
ID=41369886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009100599498A Active CN101585411B (en) | 2009-07-10 | 2009-07-10 | Hydraulic servo steering engine system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101585411B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089724A (en) * | 2011-10-27 | 2013-05-08 | 北京精密机电控制设备研究所 | High-pressure large-flow four-redundancy servo valve |
| CN104454787A (en) * | 2014-10-15 | 2015-03-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Steering engine hydraulic state monitoring system and monitoring method |
| CN106494609A (en) * | 2016-11-24 | 2017-03-15 | 兰州飞行控制有限责任公司 | A kind of steering wheel clutch adhesive/off-state control circuit |
-
2009
- 2009-07-10 CN CN2009100599498A patent/CN101585411B/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103089724A (en) * | 2011-10-27 | 2013-05-08 | 北京精密机电控制设备研究所 | High-pressure large-flow four-redundancy servo valve |
| CN103089724B (en) * | 2011-10-27 | 2015-07-15 | 北京精密机电控制设备研究所 | High-pressure large-flow four-redundancy servo valve |
| CN104454787A (en) * | 2014-10-15 | 2015-03-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Steering engine hydraulic state monitoring system and monitoring method |
| CN106494609A (en) * | 2016-11-24 | 2017-03-15 | 兰州飞行控制有限责任公司 | A kind of steering wheel clutch adhesive/off-state control circuit |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101585411B (en) | 2011-04-13 |
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Address after: 611730 Tianrun Road 1228, Chengdu High-tech Zone, Sichuan Province Patentee after: Sichuan Shengteng Yuanchuang Mechanical and Electrical Technology Research Co., Ltd. Address before: 611731 Sichuan city of Chengdu province high tech Zone Kexinlu No. 6 Patentee before: Sichuan Province Chengdu Pushi Electromechanical Technology Research Co., Ltd. |