CN207759003U - A kind of unmanned plane brake control system based on servo-hydraulic transmission - Google Patents
A kind of unmanned plane brake control system based on servo-hydraulic transmission Download PDFInfo
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- CN207759003U CN207759003U CN201721922455.4U CN201721922455U CN207759003U CN 207759003 U CN207759003 U CN 207759003U CN 201721922455 U CN201721922455 U CN 201721922455U CN 207759003 U CN207759003 U CN 207759003U
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Abstract
Present disclose provides a kind of unmanned plane brake control systems based on servo-hydraulic transmission, including fax servo-drive system, brake hydraulic pipe-line system and sensing system.The unmanned plane brake control system based on servo-hydraulic transmission of the disclosure is simple in structure, it is easy to control, lighter in weight, its system response time is fast, it can quickly and efficiently realize that UAV Landing cunning runs the differential brake function that deceleration, Brake stop and auxiliary are rectified a deviation, suitable for using the large and medium-sized unmanned plane of conventional hydraulic brake and having the unmanned repacking of man-machine brake system.
Description
Technical field
The disclosure belongs to brake control technology field, and in particular to a kind of unmanned plane brake control based on servo-hydraulic transmission
System processed.
Background technology
Different from small drone, for large and medium-sized unmanned plane because load capacity is big, endurance is long, and voyage is remote etc. is favored advantages day,
Many-sided mission requirements such as logistics transportation, rescue and relief work, investigation mapping, forest fire protection, agricultural sprinkling can be met, in Military and civil fields
It plays an important role.
Current large and medium-sized unmanned plane generally runs landing mode using tradition is sliding, and brake system is controlled as important subsystem
The braking that aircraft is slided when running deceleration in the process, the differential correction in ground and not working to stop.As unmanned air vehicle technique develops,
Under the impact of the New technical uses such as electrical brake, hydraulic brake system still has that fast response time, load stiffness be big, braking effect
The advantages that rate is high, therefore it is still widely used for the design and repacking of large and medium-sized unmanned plane.
Utility model content
(1) technical problems to be solved
Present disclose provides it is a kind of based on servo-hydraulic transmission unmanned plane brake control system, at least partly solve with
The technical issues of upper proposed.
(2) technical solution
According to one aspect of the disclosure, a kind of unmanned plane brake control system based on servo-hydraulic transmission, including：Electricity
Servo-drive system 100 is passed, including：Rotating arm Servo-controller 110 is fixed on aircraft main force support structure, by exporting rocking arm 120
It is connect with hydraulic actuator 210, receives the output signal of flight-control computer, drive the piston rod of hydraulic actuator 210
Compression generates pressure；Brake hydraulic pipe-line system 200, including hydraulic actuator 210, by internal brake-fluid pressure oil by liquid
In the pressure transmission to external brake system component for pressing pressurized strut 210, brake function is realized；And sensing system
300, one end is connected to brake hydraulic pipe-line system 200, and the other end accesses flight-control computer, acquires brake hydraulic pipeline
Pressure in system 200, and convert pressure signal to electric signal and feed back to flight-control computer.
In some embodiments of the present disclosure, fax servo-drive system 100 includes：Two rotating arm Servo-controllers 110,
It is fixed on steering engine mounting plate 140 by the auricle of quadrangle, steering engine mounting plate 140 is fixed on installation guide rail 150, installs guide rail
150 are fixed on by guide rail reinforcing rib and support bending plate 160 on aircraft main force support structure.
In some embodiments of the present disclosure, rotating arm Servo-controller 110 is electronic double remaining rotations of output torque
Rocking arm Servo-controller.
In some embodiments of the present disclosure, there are one output shaft, two rotating arms to watch for rotating arm Servo-controller 110
It takes steering engine 110 to be symmetrically installed in the form of output shaft is coaxial, respectively the brake of control left and right；Rotating arm Servo-controller 110 it is defeated
There is rectangular keyway on shaft surface, for connecting output rocking arm 120；Electric interfaces are provided on rotating arm Servo-controller 110,
It is connected to rudder control device by aviation plug, receives the output signal of flight-control computer.
In some embodiments of the present disclosure, output rocking arm 120 includes：Mounting seat, is provided with circular hole among it, in circular hole
It is provided with rectangular keyway, the output shaft for being connected to rotating arm Servo-controller 110；And auricle, pass through bolt and work
Dynamic cylinder angle fork connector 130 connects.
In some embodiments of the present disclosure, there is an ears piece in one end of pressurized strut angle fork connector 130, spiral shell in the band of one end
Line, wherein there is one end of ears piece to be connect with output rocking arm 120 by bolt, tapped one end and hydraulic actuator 210
Piston rod is connected through a screw thread.
In some embodiments of the present disclosure, brake hydraulic pipe-line system 200 includes：Original fluid pressure line system on aircraft
System, including：Hydraulic actuator 210, one side is provided with port；And newly-increased hydraulic plumbing system component, including hydraulic oil pipe
230；Metal threeway 260, both ends connection extend to external original machine hydraulic oil pipe and brake system group from interior of aircraft
The external original machine hydraulic oil pipe of part；And metallic pipe coupling 220, it is used for hydraulic oil pipe 230, hydraulic actuator 210 and metal three
Connection between logical 260.
In some embodiments of the present disclosure, hydraulic actuator 210 is cylindrical tube shape body, and inside includes piston, resets bullet
Spring, sealing ring, snap ring, washer and gland；One end piston rod of hydraulic actuator 210 passes through with pressurized strut angle fork connector 130
It is threadedly coupled, output rocking arm 120 drives the piston rod compression piston of hydraulic actuator 210 to transmit brake pressure, when discharge degree
Then resetted by the resetting spring in hydraulic actuator 210；
The other end of hydraulic actuator 210 is connect by bolt with the top auricle of hydraulic actuation tube stent 240, and hydraulic pressure is made
The front foot of dynamic tube stent 240 is fixed on aircraft bulkhead upper surface platform, and the rear foot is fixed on holder bottom plate 250, holder bottom plate 250
Left and right edges be bolted on the main force support structure of aircraft bulkhead.
In some embodiments of the present disclosure, sensing system 300 includes：Pressure sensor 310, built-in sensing element
Part；One end of pressure sensor 310 is pressure interface, and the other end is electric interfaces；Pressure interface by the screw thread of outer surface with
260 intermediate ends of metal threeway connect；Electric interfaces are connected to flight-control computer by hydrostatic sensor matching plug 320.
In some embodiments of the present disclosure, flight-control computer is sent out by rudder control device to rotating arm steering engine 110
Command signal, 110 output shaft of rotating arm steering engine drive output rocking arm 120 to rotate respective angles, the fork connection of driving pressurized strut angle
130 compression piston bar of part, piston rod are passed through by the brake-fluid pressure oil in piston compression hydraulic pressurized strut 210, brake-fluid pressure oil
Hydraulic oil pipe 230 transmits to brake on brake pressure to skidding component, meanwhile, pressure sensor 310 is by brake pressure
Signal is converted to voltage signal Real-time Feedback to flight control computer, and flight control computer exports new brake according to aircraft floor speed
Amount signal gives rudder control device, and control rotating arm Servo-controller 110 drives output rocking arm 120 to execute new braking commands, so anti-
Again until aircraft stops, rotating arm Servo-controller 110 finally executes the instruction that gets off the brakes.
(3) advantageous effect
It can be seen from the above technical proposal that a kind of unmanned plane brake control system based on servo-hydraulic transmission of the disclosure
System at least has the advantages that one of them：
(1) in the unmanned plane brake control system of the disclosure, fax servo-drive system passes through hydraulic actuator and brake hydraulic
Pipe-line system connects, and sensing system is connect by metal threeway with brake hydraulic pipe-line system, simple in structure, easy to control,
Lighter in weight；
(2) it is full of brake-fluid pressure oil in the unmanned plane brake control system pipeline of the disclosure, pressurized strut pressure transmission is arrived
On external brake system component, brake is completed, fast response time, load stiffness is big, and braking efficiency is high；
(3) in the unmanned plane brake control system of the disclosure, rotating arm Servo-controller totally two, two electric interfaces point
Not Lian Jie rudder control device, two rotating arm Servo-controllers independently control left and right brake, be independent of each other, fully meet unmanned plane
Deceleration, Brake stop function and the differential brake function for realizing auxiliary correction are alightinged run, is suitable for using conventional hydraulic brake
Large and medium-sized unmanned plane and the existing unmanned repacking for having man-machine brake system.
Description of the drawings
Fig. 1 is unmanned plane brake control system assembly diagram in the embodiment of the present disclosure.
Fig. 2 a are the overall structure isometric of fax servo-drive system in unmanned plane brake control system in the embodiment of the present disclosure
View.
Fig. 2 b are the overall structure front view of fax servo-drive system in unmanned plane brake control system in the embodiment of the present disclosure.
Fig. 2 c are the right brake overall structure of fax servo-drive system in unmanned plane brake control system in the embodiment of the present disclosure
Side view.
Fig. 3 is rotating arm Servo-controller front view in unmanned plane brake control system in the embodiment of the present disclosure.
Fig. 4 is steering engine mounting plate front view in unmanned plane brake control system in the embodiment of the present disclosure.
Fig. 5 is to export rocking arm front view in the embodiment of the present disclosure in unmanned plane brake control system.
Fig. 6 is that connector front view is pitched at pressurized strut angle in unmanned plane brake control system in the embodiment of the present disclosure.
Fig. 7 a are to install guide rail and reinforcing rib front view in the embodiment of the present disclosure in unmanned plane brake control system.
Fig. 7 b are to install guide rail and reinforcing rib side view in the embodiment of the present disclosure in unmanned plane brake control system.
Fig. 8 a are to support bending plate front view in the embodiment of the present disclosure in unmanned plane brake control system.
Fig. 8 b are to support bending plate side view in the embodiment of the present disclosure in unmanned plane brake control system.
Fig. 9 is hydraulic actuator front view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 10 is metallic pipe coupling side view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 11 is hydraulic oil pipe side view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 12 a are hydraulic actuation tube stent front view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 12 b are hydraulic actuator holder side view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 13 is hydraulic actuation tube stent bottom plate front view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 14 is metal threeway side view in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 15 is sensing system schematic diagram in unmanned plane brake control system in the embodiment of the present disclosure.
Figure 16 is hydrostatic sensor electric interfaces matching plug side in unmanned plane brake control system in the embodiment of the present disclosure
View.
Figure 17 is hydrostatic sensor side view in unmanned plane brake control system in the embodiment of the present disclosure.
【Embodiment of the present disclosure main element symbol description in attached drawing】
100- fax servo-drive systems；
110- rotating arm Servo-controllers；120- exports rocking arm；
Pitch connector in 130- pressurized struts angle；140- steering engine mounting plates；
150- installs guide rail；160- supports bending plate；
200- brake hydraulic pipe-line systems；
210- hydraulic actuators；220- metallic pipe couplings；
230- hydraulic oil pipes；240- hydraulic actuation tube stents；
250- holder bottom plates；260- metal threeways；
300- sensing systems；
310- hydrostatic sensors；320- hydrostatic sensor matching plugs.
Specific implementation mode
Present disclose provides a kind of unmanned plane brake control systems based on servo-hydraulic transmission, including fax servo system
System, brake hydraulic pipe-line system and sensing system.The unmanned plane brake control system based on servo-hydraulic transmission of the disclosure
Simple in structure, easy to control, lighter in weight, system response time is fast, can quickly and efficiently realize that UAV Landing is slided and run
Slow down, Brake stop and auxiliary correction differential brake function, be suitable for use the large and medium-sized unmanned plane of conventional hydraulic brake with
And there is the unmanned repacking of man-machine brake system.
To make the purpose, technical scheme and advantage of the disclosure be more clearly understood, below in conjunction with specific embodiment, and reference
The disclosure is further described in attached drawing.
Disclosure some embodiments will be done with reference to appended attached drawing in rear and more comprehensively describe to property, some of but not complete
The embodiment in portion will be shown.In fact, the various embodiments of the disclosure can be realized in many different forms, and should not be construed
To be limited to this several illustrated embodiment；Relatively, these embodiments are provided so that the disclosure meets applicable legal requirement.
In an exemplary embodiment of the disclosure, a kind of unmanned plane brake control being driven based on servo-hydraulic is provided
System processed.
Fig. 1 is unmanned plane brake control system assembly diagram in the embodiment of the present disclosure.As shown in Figure 1, the base of the disclosure
Include in the unmanned plane brake control system of servo-hydraulic transmission：
Fax servo-drive system 100, including：
Rotating arm Servo-controller 110 is fixed on aircraft main force support structure, by exporting rocking arm 120 and hydraulic actuation
Cylinder 210 connects, and receives the output signal of flight-control computer, and the piston rod compression of driving hydraulic actuator 210 generates pressure
Power；
Brake hydraulic pipe-line system 200 is connect with hydraulic actuator 210, by internal brake-fluid pressure oil by hydraulic pressure
In the pressure transmission of pressurized strut 210 to external brake system component, brake function is realized, fast response time, load is just
Degree is big, and braking efficiency is high；And
Sensing system 300, one end are connected to brake hydraulic pipe-line system 200, and other end access flight control calculates
Machine acquires the pressure in brake hydraulic pipe-line system 200, and converts pressure signal to electric signal and feed back to flight control calculating
Machine.
The each component part for the unmanned plane brake control system that the present embodiment is driven based on servo-hydraulic individually below
It is described in detail.
Fig. 2 a, Fig. 2 b are the overall structure etc. of fax servo-drive system in unmanned plane brake control system in the embodiment of the present disclosure
Axis surveys view and front view.Fig. 2 c are the right brake of fax servo-drive system in unmanned plane brake control system in the embodiment of the present disclosure
Overall structure side view.As shown in Fig. 2 a, 2b, 2c, fax servo-drive system 100 includes：Two rotating arm Servo-controllers 110,
Two output rocking arms, 120, two pressurized strut angles fork 130, one pieces of connector installation guide rails 150 of steering engine mounting plate 140, two and
Four pieces of support bending plates 160.
Fig. 3 is the front view of rotating arm Servo-controller in unmanned plane brake control system in the embodiment of the present disclosure, such as Fig. 3
Shown, there are one output shafts for rotating arm Servo-controller 110, and two rotating arm Servo-controllers 110 are with the coaxial shape of output shaft
Formula is symmetrically installed, and is fixed on steering engine mounting plate 140 by the auricle of quadrangle, and steering engine mounting plate 140 is fixed on installation guide rail
On 150, installation guide rail 150 is fixed on by guide rail reinforcing rib and support bending plate 160 on aircraft main force support structure.Steering engine is installed
The structure chart of plate 140 is as shown in Figure 4.
Rotating arm Servo-controller 110 is electronic double remaining rotating arm Servo-controllers of output torque.Rotating arm is watched
There is rectangular keyway on the output shaft surface for taking steering engine 110, for connecting output rocking arm 120.It is arranged on rotating arm Servo-controller 110
There are electric interfaces, rudder control device, the output signal for receiving flight-control computer are connected to by aviation plug.Two rotations
Left and right brake can be controlled respectively by turning rocking arm Servo-controller 110, be independent of each other independently of each other, fully met UAV Landing cunning race and subtracted
Speed and Brake stop function and the differential brake function for realizing auxiliary correction.
Fig. 5 is the front view for exporting rocking arm in the embodiment of the present disclosure in unmanned plane brake control system, as shown in figure 5, defeated
Go out rocking arm 120 and use alloy steel material, is made of mounting seat and auricle, mounting seat is provided with circular hole, is provided in circular hole rectangular
Keyway is connected on the output shaft of rotating arm Servo-controller 110 and is locked by the locking nut of shaft end, and auricle passes through bolt
It is connect with pressurized strut angle fork connector 130, auricle hole, angle fork connector connecting hole and the bolt-clearance for exporting rocking arm 120 coordinate
Ensure relative motion.
Fig. 6 is that connector front view is pitched at pressurized strut angle in unmanned plane brake control system in the embodiment of the present disclosure.Such as Fig. 6 institutes
Show, pressurized strut angle pitches connector 130 and alloy steel material, one end is used to have ears piece one end band internal thread, ears piece to lean on bolt
It is connect with output rocking arm 120, tapped one end and the piston rod of hydraulic actuator 210 are connected through a screw thread and use locking screw
Mother's locking.
Fig. 7 a, 7b be the front view of installation guide rail and reinforcing rib in unmanned plane brake control system in the embodiment of the present disclosure,
Side view.As shown in Fig. 7 a, 7b, installation guide rail 150 uses 7 line aluminium alloys, is that leading portion upper and lower surface is smooth, back segment lower surface band
The long straight guide of groove.Reinforcing rib is riveted on installation 150 leading portion of guide rail, and installation 150 back segment of guide rail is fixed by bolts to aircraft master
On load-carrying construction.
Fig. 8 a, 8b are to support bending plate front view, side view in the embodiment of the present disclosure in unmanned plane brake control system.Such as
Shown in Fig. 8 a, 8b, support bending plate 160 is " L " shape square plate, and two pieces of support 160 long sides of bending plate are bonded reinforcing rib both sides respectively
By being bolted fixation, short side is then bolted on aircraft main force support structure frame.Guide rail reinforcing rib is top flange
Polygon aluminium alloy plate.
Brake hydraulic pipe-line system 200, a part are original hydraulic plumbing system on aircraft, including hydraulic actuator 210
With original fluid pressure line, another part is the hydraulic plumbing system component increased newly, including metallic pipe coupling 220, hydraulic oil pipe
230, hydraulic actuation tube stent 240, holder bottom plate 250 and metal threeway 260.
Hydraulic oil pipe 230 and metallic pipe coupling 220 by fax servo-drive system 100, brake hydraulic pipe-line system 200 and sense
Device system 300 is linked to be complete unmanned plane brake control system, simple in structure, easy to control, lighter in weight.
Wherein, the top of hydraulic actuator 210 is connect by bolt with the top auricle of hydraulic actuation tube stent 240, liquid
The front foot of pressure start tube stent 240 is fixed on aircraft bulkhead upper surface platform, and the rear foot is fixed on holder bottom plate 250, holder bottom
250 left and right edges of plate are bolted on the main force support structure of aircraft bulkhead.
Fig. 9 is hydraulic actuator front view in the unmanned plane brake control system.As shown in figure 9, hydraulic actuator 210
For cylindrical tube shape body, inside further include piston, resetting spring, sealing ring, snap ring, washer, gland.Hydraulic actuator 210
Side is provided with input/output port, is connected through a screw thread with metallic pipe coupling 220, accesses hydraulic actuator 210 brake since then
In hydraulic oil pipe system 200.210 one end of hydraulic actuator is connect by bolt with hydraulic actuation tube stent 240, hydraulic actuator
210 can rotate around bolt.The other end piston rod of hydraulic actuator 210 is connected with pressurized strut angle fork connector 130 by screw thread
It connects, output rocking arm 120 drives the piston rod compression piston of hydraulic actuator 210 to transmit brake pressure, then by liquid when discharge degree
The resetting spring in pressurized strut 210 is pressed to reset.
The structure of metallic pipe coupling 220 is as shown in Figure 10, is used for hydraulic oil pipe 230, hydraulic actuator 210 and metal three
Connection between logical 260.
Figure 11 is hydraulic oil pipe side view in unmanned plane brake control system in the embodiment of the present disclosure.As shown in figure 11, liquid
Pressuring oil pipe 230 is mainly politef hose, and the tapped metal horn mouth in one end of tube head passes through with externally threaded gold
Belong to pipe fitting 220 to connect with 200 other component of hydraulic plumbing system.
It should be noted that for the brake hydraulic pipe-line system of different aircaft configurations, it can be by increasing hose and gold
Belong to pipe fitting and carries out indefinite extension.
Hydraulic actuation tube stent 240 uses 7 line aluminium alloys, front and back foot to be bolted on aircraft bulkhead and holder respectively
On bottom plate 250, holder bottom plate 250 is fixed on aircraft main force support structure.The structure of hydraulic actuation tube stent 240 such as Figure 12 a,
Shown in 12b.
Holder bottom plate 250 uses alloy steel material, bottom surface to use the design of three reinforcing ribs at stress concentration position,
It is bolted on the main force support structure of aircraft.The reaction force that piston rod is compressed pressurized strut power by entire design passes through institute
It states holder and mounting plate passes to aircraft main force support structure, ensure that pressurized strut reliable operation, part will not occur obviously to deform.Branch
The structure of frame bottom plate 250 is as shown in figure 13.
Figure 14 is metal threeway side view in unmanned plane brake control system in the embodiment of the present disclosure.As shown in figure 14, golden
Belong to threeway 260 and use surface treated 7 line aluminium alloy material, among it end connection hydrostatic sensor 310, by brake hydraulic
Pipe-line system 200 is connected with sensing system 300, and the connection of remaining both ends extends to external hydraulic oil pipe from interior of aircraft
The external hydraulic oil pipe with brake system component, connection type are to be threadedly coupled.
Figure 15 is sensing system schematic diagram in unmanned plane brake control system in the embodiment of the present disclosure.As shown in figure 15,
Sensing system 300 includes pressure sensor 310 and hydrostatic sensor matching plug 320.Hydrostatic sensor matching plug 320
Side view is as shown in figure 16.
Figure 17 is sensor schematic in unmanned plane brake control system in the embodiment of the present disclosure.As shown in figure 17, pressure
Sensing element built in sensor 310, one end are that pressure interface one end is electric interfaces, screw thread and the gold of pressure interface outer surface
Belong to 260 intermediate ends of threeway to connect by locking nut, electric interfaces are connected to winged by hydrostatic sensor matching plug signal wire
Row control computer.Pressure sensor 310 acquires the pressure in brake hydraulic pipe-line system 200, and converts pressure signal to
Electric signal feeds back to flight-control computer.
Based on servo-hydraulic transmission unmanned plane brake control system start when：Flight-control computer is given by rudder control device
Rotating arm steering engine 110 sends out command signal, and 110 output shaft of rotating arm steering engine drives output rocking arm 120 to rotate respective angles,
Pressurized strut angle is driven to pitch 130 compression piston bar of connector, piston rod passes through the brake hydraulic in piston compression hydraulic pressurized strut 210
Oil, brake-fluid pressure oil are transmitted by hydraulic oil pipe 230 on brake pressure to the brake callipers of skidding component, driving brake card
Brake block movement in pincers, brake block is squeezed with airplane wheel brake disk generates frictional force to make wheel braking.Hydrostatic sensor 310
Brake pressure signal is converted into voltage signal Real-time Feedback to flight control computer, flight control computer is defeated according to aircraft floor speed
Going out new braking amount signal gives rudder control device, control rotating arm Servo-controller 110 that output rocking arm 120 is driven to execute new brake control
System, repeatedly until aircraft stops, rotating arm Servo-controller 110 finally executes the instruction that gets off the brakes.
It should be noted that the installation of entire fax servo-drive system 100 and hydraulic actuator 210 was not loaded in nature
State.
It should be noted that the Servo-controller for different aircaft configurations installs retaining element, it can be according to bulkhead and master
Load-carrying construction pattern carries out connection design and material selection of different shapes.
It is also to be noted that for it is all by tap rivet connection parts ensure rotating arm Servo-controller and its
The smooth no protrusion of installation surface of his equipment.
So far, the unmanned plane brake control system introduction based on servo-hydraulic transmission of the first embodiment of the present disclosure finishes.
So far, attached drawing is had been combined the embodiment of the present disclosure is described in detail.According to above description, art technology
Personnel should have clear understanding to the unmanned plane brake control system based on servo-hydraulic transmission of the disclosure.
It should be noted that in attached drawing or specification text, the realization method for not being painted or describing is affiliated technology
Form known to a person of ordinary skill in the art, is not described in detail in field.In addition, the above-mentioned definition to each element and method is simultaneously
It is not limited only to various concrete structures, shape or the mode mentioned in embodiment, those of ordinary skill in the art can carry out letter to it
It singly changes or replaces.
In conclusion present disclose provides a kind of unmanned plane brake control system based on servo-hydraulic transmission, including electricity
Pass servo-drive system, brake hydraulic pipe-line system and sensing system.The unmanned plane brake based on servo-hydraulic transmission of the disclosure
Control system architecture is simple, easy to control, and lighter in weight, system response time is fast, can quickly and efficiently realize unmanned plane
The differential brake function that deceleration, Brake stop and auxiliary are rectified a deviation is alightinged run, is suitable for using the large and medium-sized of conventional hydraulic brake
Unmanned plane and the unmanned repacking for having man-machine brake system.
It should also be noted that, the direction term mentioned in embodiment, for example, "upper", "lower", "front", "rear", " left side ",
" right side " etc. is only the direction of refer to the attached drawing, not is used for limiting the protection domain of the disclosure.Through attached drawing, identical element by
Same or similar reference numeral indicates.When that understanding of this disclosure may be caused to cause to obscure, conventional structure will be omitted
Or construction.
And the shape and size of each component do not reflect actual size and ratio in figure, and only illustrate the embodiment of the present disclosure
Content.In addition, in the claims, any reference mark between bracket should not be configured to the limit to claim
System.
Furthermore word "comprising" does not exclude the presence of element or step not listed in the claims.Before element
Word "a" or "an" does not exclude the presence of multiple such elements.
The word of specification and ordinal number such as " first ", " second ", " third " etc. used in claim, with modification
Corresponding element, itself is not meant to that the element has any ordinal number, does not also represent the suitable of a certain element and another element
Sequence in sequence or manufacturing method, the use of those ordinal numbers are only used for enabling the element with certain name and another tool
There is the element of identical name that can make clear differentiation.
Similarly, it should be understood that in order to simplify the disclosure and help to understand one or more of each open aspect,
Above in the description of the exemplary embodiment of the disclosure, each feature of the disclosure is grouped together into single implementation sometimes
In example, figure or descriptions thereof.However, the method for the disclosure should be construed to reflect following intention：It is i.e. required to protect
The disclosure of shield requires features more more than the feature being expressly recited in each claim.More precisely, as following
Claims reflect as, open aspect is all features less than single embodiment disclosed above.Therefore,
Thus the claims for following specific implementation mode are expressly incorporated in the specific implementation mode, wherein each claim itself
All as the separate embodiments of the disclosure.
Particular embodiments described above has carried out further in detail the purpose, technical solution and advantageous effect of the disclosure
It describes in detail bright, it should be understood that the foregoing is merely the specific embodiment of the disclosure, is not limited to the disclosure, it is all
Within the spirit and principle of the disclosure, any modification, equivalent substitution, improvement and etc. done should be included in the guarantor of the disclosure
Within the scope of shield.
Claims (10)
1. a kind of unmanned plane brake control system based on servo-hydraulic transmission, including：
Fax servo-drive system (100), including：
Rotating arm Servo-controller (110), is fixed on aircraft main force support structure, by exporting rocking arm (120) and hydraulic actuation
Cylinder (210) connection, receives the output signal of flight-control computer, drives the piston rod pressure of the hydraulic actuator (210)
Contracting generates pressure；
Brake hydraulic pipe-line system (200), including the hydraulic actuator (210), by internal brake-fluid pressure oil by institute
It states in the pressure transmission to external brake system component of hydraulic actuator (210), realizes brake function；And
Sensing system (300), one end are connected to the brake hydraulic pipe-line system (200), other end access flight control
Computer acquires the pressure in brake hydraulic pipe-line system (200), and converts pressure signal to electric signal and feed back to flight control
Computer processed.
2. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein
The fax servo-drive system (100) includes：
Two rotating arm Servo-controllers (110), are fixed on by the auricle of quadrangle on steering engine mounting plate (140), institute
It states steering engine mounting plate (140) to be fixed on installation guide rail (150), the installation guide rail (150) passes through guide rail reinforcing rib and support
Bending plate (160) is fixed on aircraft main force support structure.
3. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein the rotation is shaken
Arm Servo-controller (110) is electronic double remaining rotating arm Servo-controllers of output torque.
4. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein
There are one output shafts for the rotating arm Servo-controller (110), and described two rotating arm Servo-controllers (110) are to export
The coaxial form of axis is symmetrically installed, respectively the brake of control left and right；
There is rectangular keyway on the output shaft surface of the rotating arm Servo-controller (110), for connecting the output rocking arm
(120)；
Electric interfaces are provided on the rotating arm Servo-controller (110), rudder control device is connected to by aviation plug, are received
The output signal of flight-control computer.
5. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein the output is shaken
Arm (120) includes：
Mounting seat is provided with circular hole, rectangular keyway is provided in circular hole, among it for being connected to rotating arm Servo-controller
(110) on output shaft；And
Auricle is pitched connector (130) with the pressurized strut angle by bolt and is connect.
6. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein
There are ears piece, one end band internal thread, wherein have one end of ears piece in one end of the pressurized strut angle fork connector (130)
It is connect with the output rocking arm (120) by bolt, the piston rod of tapped one end and the hydraulic actuator (210) passes through
It is threadedly coupled.
7. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein the brake-fluid
Hydraulic pipe (200) includes：
Original hydraulic plumbing system on aircraft, including：
Hydraulic actuator (210), one side is provided with port；And
Newly-increased hydraulic plumbing system component, including
Hydraulic oil pipe (230)；
Metal threeway (260), both ends connection extend to external original machine hydraulic oil pipe and brake system from interior of aircraft
The external original machine hydraulic oil pipe of component；And
Metallic pipe coupling (220) is used for the hydraulic oil pipe (230), the hydraulic actuator (210) and the metal threeway
(260) connection between.
8. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein
The hydraulic actuator (210) be cylindrical tube shape body, inside include piston, resetting spring, sealing ring, snap ring, washer and
Gland；
One end piston rod of the hydraulic actuator (210) is connected through a screw thread with pressurized strut angle fork connector (130), institute
Stating output rocking arm (120) drives the piston rod compression piston of the hydraulic actuator (210) to transmit brake pressure, when discharge degree
Then resetted by the resetting spring in the hydraulic actuator (210)；
The other end of the hydraulic actuator (210) is connected by the top auricle of bolt and the hydraulic actuation tube stent (240)
It connects, the front foot of the hydraulic actuation tube stent (240) is fixed on aircraft bulkhead upper surface platform, and the rear foot is fixed on holder bottom plate
(250) on, the left and right edges of the holder bottom plate (250) are bolted on the main force support structure of aircraft bulkhead.
9. the unmanned plane brake control system according to claim 7 based on servo-hydraulic transmission, wherein
The sensing system (300) includes：
Pressure sensor (310), built-in sensing element；
One end of the pressure sensor (310) is pressure interface, and the other end is electric interfaces；
The pressure interface is connect by the screw thread of outer surface with metal threeway (260) intermediate ends；
The electric interfaces are connected to flight-control computer by hydrostatic sensor matching plug (320).
10. the unmanned plane brake control system according to claim 1 based on servo-hydraulic transmission, wherein
Flight-control computer sends out command signal, the rotating arm by rudder control device to the rotating arm steering engine (110)
Steering engine (110) output shaft drives the output rocking arm (120) to rotate respective angles, drives the pressurized strut angle fork connector
(130) compression piston bar, piston rod compress the brake-fluid pressure oil in the hydraulic actuator (210), brake hydraulic by piston
Oil is transmitted by the hydraulic oil pipe (230) and is braked on brake pressure to skidding component, meanwhile, the pressure sensing
Brake pressure signal is converted to voltage signal Real-time Feedback to flight control computer by device (310), and flight control computer is according to aircraft
Face velocity exports new braking amount signal and gives rudder control device, controls rotating arm Servo-controller (110) the driving output and shakes
Arm (120) executes new braking commands, and repeatedly until aircraft stops, the rotating arm Servo-controller (110) is finally held
The capable instruction that gets off the brakes.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146621A (en) * | 2017-12-29 | 2018-06-12 | 中国科学院工程热物理研究所 | A kind of unmanned plane brake control system based on servo-hydraulic transmission |
| CN109533301A (en) * | 2018-12-11 | 2019-03-29 | 中航工业南京伺服控制系统有限公司 | A kind of aircraft brake system |
-
2017
- 2017-12-29 CN CN201721922455.4U patent/CN207759003U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146621A (en) * | 2017-12-29 | 2018-06-12 | 中国科学院工程热物理研究所 | A kind of unmanned plane brake control system based on servo-hydraulic transmission |
| CN108146621B (en) * | 2017-12-29 | 2023-12-29 | 中国科学院工程热物理研究所 | Unmanned aerial vehicle brake control system based on servo hydraulic transmission |
| CN109533301A (en) * | 2018-12-11 | 2019-03-29 | 中航工业南京伺服控制系统有限公司 | A kind of aircraft brake system |
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