CN105314128A - Hydraulic control system for helicopter ground integrated test bench - Google Patents
Hydraulic control system for helicopter ground integrated test bench Download PDFInfo
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- CN105314128A CN105314128A CN201510745758.2A CN201510745758A CN105314128A CN 105314128 A CN105314128 A CN 105314128A CN 201510745758 A CN201510745758 A CN 201510745758A CN 105314128 A CN105314128 A CN 105314128A
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Abstract
The invention discloses a hydraulic control system for a helicopter ground integrated test bench, and belongs to the technical field of helicopter tests. The system comprises an upper computer, an analog quantity I/O module and a steering engine controller; the upper computer is used for inputting an instruction and has a display processing function, the analog quantity I/O module is used for performing digital-to-analogue conversion, and the steering engine controller is used for receiving data transmitted by the analog quantity I/O module and controlling a main steering engine and a tail steering engine. The hydraulic control system for the helicopter ground integrated test bench further comprises a hydraulic system, a hydraulic pump in the hydraulic system serves as an accessory of a main speed reducer, an output shaft of the accessory of the main speed reducer is driven by an engine, the hydraulic pump is connected with the main steering engine and the tail steering engine through valves and pipelines, and the main steering engine, the tail steering engine and the hydraulic system all adopt airborne parts. According to the hydraulic control system for the helicopter ground integrated test bench, the real working condition of the helicopter hydraulic control system can be better simulated, the helicopter hydraulic control system can be better assessed, and meanwhile it is guaranteed that data of other test projects are truer and more effective.
Description
Technical field
The invention belongs to helicopter testing technique field, be specifically related to a kind of helicopter integrated ground test platform hydraulic control system.
Background technology
Hydraulic control system changes total distance, feathering, the power of tail-rotor distance and actuating unit as helicopter, its function and performance to helicopter airflight and ground experiment all of crucial importance.
Fly the helicopter controlled to adopting fax, the hydraulic control system relevant to flight attitude comprises hydraulic reservoir, Hydraulic Pump, valve and hydraulic tubing, driving leverage, flight control computer and main tail-rotor steering wheel.Hydraulic Pump under driving engine and the main drive subtracted for steering wheel action provides high pressure fuel source, pilot control collective-pitch lever, jociey stick and pedal, mechanical signal is converted into through flight control computer the electric signal controlling steering wheel after being converted into voltage signal again, steering wheel makes controlled flexible change pitch, and it forms schematic diagram and sees Fig. 1.Carry out integrated ground test project by which various, the test period reaches hundreds of hours, if handled at driving compartment by chaufeur, noise and vibration large, work under bad environment, the very easily tired and safety of chaufeur cannot ensure.
Of the prior art is driving engine, rotor system and driving system are fixed on T/S as test article to carry out every test to the test of helicopter hydraulic control system.Hydraulic control system comprises ground hydraulic pumping plant, upper computer, controller and servoamplifier, servovalve and main tail and handles oil cylinder.Ground hydraulic pumping plant provides high pressure fuel source, operating personal is in the input steering command of upper computer software interface, and via controller and servoamplifier are converted into current signal, control the aperture of servovalve, and then controlling the fore and aft motion that the piston rod of oil cylinder handled by the main tail-rotor in ground, Fig. 2 is shown in by schematic diagram.Hydraulic power unit and manipulation oil cylinder are ground non-standard, and can not simulate the real work state of hydraulic control system, systemic-function and performance cannot be verified.
Summary of the invention
In order to solve the problem, the invention provides a kind of helicopter integrated ground test platform hydraulic control system, comprise upper computer, analog quantity I/O module, steering engine controller become with control vane mechanism with the hydraulic efficiency pressure system on ground experiment machine.Concrete, comprising:
Upper computer, arranges instruction input function, and is provided with the function of feedback signal display;
Analog quantity I/O module, receives the instruction input of described upper computer, and this instruction input is converted to analog signal and sends to steering engine controller, meanwhile, also comprise the feedback signal receiving described steering engine controller, and this feedback signal is sent to upper computer;
Steering engine controller, receive the analog signal that described analog quantity I/O module is sent, and give described analog quantity I/O module by the feedback signal back of steering wheel, simultaneously, described steering engine controller also comprises servo drive unit and exciting unit, described servo drive unit is used for carrying out servocontrol to steering wheel and carrying out break-make process to servo loop, and described exciting unit is for sending excited signal to realize the excitation of steering wheel displacement pickup;
Main rudder machine and tail actuator, respond the control command of described steering engine controller,
Wherein, described helicopter integrated ground test platform hydraulic control system also comprises hydraulic efficiency pressure system, Hydraulic Pump in described hydraulic efficiency pressure system is by engine drive, and adjusted by main reduction gear, Hydraulic Pump is connected described main rudder machine and tail actuator by valve with pipeline, described main rudder machine, tail actuator and hydraulic efficiency pressure system all adopt airborne, and described main rudder machine comprises front main rudder machine, left main rudder machine and right main rudder machine.
Preferably, described instruction input comprises total distance, horizontal feathering, longitudinal feathering, tail-rotor input apart from the instruction of four-way.
In such scheme preferably, described feedback signal comprises described total distance, longitudinal feathering, horizontal feathering, tail-rotor distance and steering wheel displacement and steering wheel electric current.
In such scheme preferably, described upper computer comprises described total distance, longitudinal feathering, horizontal feathering and tail-rotor distance instruction transformation is the displacement commands of steering wheel.
In such scheme preferably, main pitch steering command is converted into the matrix relationship of main rudder machine displacement commands and is
Wherein, Δ L
1for front main rudder machine displacement, Δ L
2for left main rudder machine displacement, Δ L
3for right main rudder machine displacement, a
ijfor constant (i, j are the integer of 1 ~ 3), θ
0.7for total distance, θ
sfor horizontal feathering, θ
cfor longitudinal feathering.
Tail-rotor is Δ L apart from the instruction morphing pass for tail-rotor steering wheel displacement commands
4=b θ
w,
Wherein, Δ L
4for tail-rotor steering wheel displacement, b is constant, θ
wfor tail-rotor distance.
In such scheme preferably, the displacement commands that described analog quantity I/O module sends to the analog signal of steering engine controller to comprise front main rudder machine, left main rudder machine, right main rudder machine and tail actuator exports.
In such scheme preferably, the feedback signal that described analog quantity I/O module receives described steering engine controller comprises the displacement of steering wheel, electric current and pressure feedback.
Innovative point of the present invention is:
The first, long-range input and the condition monitoring carrying out steering command of operating personal;
The second, analog quantity I/O module and steering engine controller are non-standard de-sign;
3rd, three main oar steering wheels and a tail-rotor steering wheel all adopt airborne;
4th, hydraulic efficiency pressure system adopts airborne.
Adopt the hydraulic control system in the present invention, compared with the operating pattern on helicopter machine, operating personal is away from noise, and working environment improves, and personal safety is protected; Compared with traditional helicopter integrated ground test platform hydraulic control system, can the real work state of helicopter simulating hydraulic control system better, ensure that the data of other Test items are more authentic and valid while examining helicopter hydraulic control system better.
Accompanying drawing explanation
Fig. 1 is that on conventional helicopters machine, hydraulic control system forms structural representation.
Fig. 2 is that prior art helicopter integrated ground test platform hydraulic control system forms schematic diagram.
Fig. 3 be originally be invention one preferred embodiment helicopter integrated ground test platform hydraulic control system form schematic diagram.
Fig. 4 is helicopter integrated ground test platform maneuvering system software front interface block diagram embodiment illustrated in fig. 3.
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Hydraulic control system in the present invention is become with control vane mechanism with the hydraulic efficiency pressure system on ground experiment machine by upper computer, analog quantity I/O module, steering engine controller, and accompanying drawing 3 is shown in by System's composition sketch.On machine, Hydraulic Pump is for main tail-rotor steering wheel provides high pressure fuel source under driving engine and master subtract drive, and operator is at interior input and the condition monitoring completing steering command in upper computer software interface of observing and controlling away from T/S.Adopt the present invention can greatly improve operator's working environment, ensure personal security, simulate the real work state of hydraulic control system simultaneously better.
The helicopter integrated ground test platform hydraulic control system of the present embodiment mainly comprises:
Upper computer, arranges instruction input function, and is provided with the function of feedback signal display;
Analog quantity I/O module, receives the instruction input of described upper computer, and this instruction input is converted to analog signal and sends to steering engine controller, meanwhile, also comprise the feedback signal receiving described steering engine controller, and this feedback signal is sent to upper computer; It should be noted that, analog quantity I/O module channels number must be greater than the port number of needs.
Steering engine controller, receive the analog signal that described analog quantity I/O module is sent, and give described analog quantity I/O module by the feedback signal back of steering wheel, simultaneously, described steering engine controller also comprises servo drive unit and exciting unit, described servo drive unit is used for carrying out servocontrol to steering wheel and carrying out break-make process to servo loop, and described exciting unit is for sending excited signal to realize the excitation of steering wheel displacement pickup; In the present embodiment, the instruction of steering wheel displacement movement spectrum is passed to 4 steering wheels by steering engine controller in electrical signal form, controls 3 main oar steering wheels and 1 tail-rotor steering wheel and composes according to the motion of regulation and move, and accurately can control movement position.Be understandable that, it must possess the power-handling capability of four steering wheel servovalves.
Main rudder machine and tail actuator, respond the control command of described steering engine controller,
Wherein, described helicopter integrated ground test platform hydraulic control system also comprises hydraulic efficiency pressure system, Hydraulic Pump Hydraulic Pump in described hydraulic efficiency pressure system is as the annex of main reduction gear, master subtracts annex output shaft by engine drive, Hydraulic Pump is connected described main rudder machine and tail actuator by valve with pipeline, and described main rudder machine, tail actuator and hydraulic efficiency pressure system all adopt airborne.
In the present embodiment, described instruction input comprises total distance, horizontal feathering, longitudinal feathering, tail-rotor input apart from the instruction of four-way.
Described feedback signal comprises described total distance, longitudinal feathering, horizontal feathering, tail-rotor distance and steering wheel displacement and steering wheel electric current.
It is the displacement commands of steering wheel that described upper computer comprises described total distance, longitudinal feathering, horizontal feathering and tail-rotor distance instruction transformation.
The matrix relationship that main pitch steering command is converted into main rudder machine displacement commands is
Wherein, Δ L
1for front main rudder machine displacement, Δ L
2for left main rudder machine displacement, Δ L
3for right main rudder machine displacement, a
ijfor constant (i, j are the integer of 1 ~ 3), θ
0.7for total distance, θ
sfor horizontal feathering, θ
cfor longitudinal feathering.
Tail-rotor is Δ L apart from the instruction morphing pass for tail-rotor steering wheel displacement commands
4=b θ
w,
Wherein, Δ L
4for tail-rotor steering wheel displacement, b is constant, θ
wfor tail-rotor distance.
In such scheme preferably, the displacement commands that described analog quantity I/O module sends to the analog signal of steering engine controller to comprise front main rudder machine, left main rudder machine, right main rudder machine and tail actuator exports.
In such scheme preferably, the feedback signal that described analog quantity I/O module receives described steering engine controller comprises the displacement of steering wheel, electric current and pressure feedback.
Innovative point of the present invention is:
The first, long-range input and the condition monitoring carrying out steering command of operating personal;
The second, analog quantity I/O module and steering engine controller are non-standard de-sign;
3rd, three main oar steering wheels and a tail-rotor steering wheel all adopt airborne;
4th, hydraulic efficiency pressure system adopts airborne.
Adopt the hydraulic control system in the present invention, compared with the operating pattern on helicopter machine, operating personal is away from noise, and working environment improves, and personal safety is protected; Compared with traditional helicopter integrated ground test platform hydraulic control system, can the real work state of helicopter simulating hydraulic control system better, ensure that the data of other Test items are more authentic and valid while examining helicopter hydraulic control system better.
Helicopter integrated ground test platform maneuvering system software front interface as shown in Figure 4.The steering command input area input total distance of operating personal at interface, the steering command of horizontal feathering, longitudinal feathering, tail-rotor distance, monitor current operation state and steering wheel parameter in operation state curve display space and steering wheel status display area; Background program realizes the mutual conversion of steering command and steering wheel displacement commands.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (7)
1. a helicopter integrated ground test platform hydraulic control system, is characterized in that, comprising:
Upper computer, arranges instruction input function, and is provided with the function of feedback signal display;
Analog quantity I/O module, receives the instruction input of described upper computer, and this instruction input is converted to analog signal and sends to steering engine controller, meanwhile, also comprise the feedback signal receiving described steering engine controller, and this feedback signal is sent to upper computer;
Steering engine controller, receive the analog signal that described analog quantity I/O module is sent, and give described analog quantity I/O module by the feedback signal back of steering wheel, simultaneously, described steering engine controller also comprises servo drive unit and exciting unit, described servo drive unit is used for carrying out servocontrol to steering wheel and carrying out break-make process to servo loop, and described exciting unit is for sending excited signal to realize the excitation of steering wheel displacement pickup;
Main rudder machine and tail actuator, respond the control command of described steering engine controller,
Wherein, described helicopter integrated ground test platform hydraulic control system also comprises hydraulic efficiency pressure system, Hydraulic Pump in described hydraulic efficiency pressure system is as the annex of main reduction gear, its output shaft is by engine drive, Hydraulic Pump is connected described main rudder machine and tail actuator by valve with pipeline, described main rudder machine, tail actuator and hydraulic efficiency pressure system all adopt airborne, and described main rudder machine comprises front main rudder machine, left main rudder machine and right main rudder machine.
2. helicopter integrated ground test platform hydraulic control system as claimed in claim 1, is characterized in that: described instruction input comprises total distance, horizontal feathering, longitudinal feathering, tail-rotor input apart from the instruction of four-way.
3. helicopter integrated ground test platform hydraulic control system as claimed in claim 2, is characterized in that: described feedback signal comprises described total distance, longitudinal feathering, horizontal feathering, tail-rotor distance and steering wheel displacement and steering wheel electric current.
4. helicopter integrated ground test platform hydraulic control system as claimed in claim 3, is characterized in that: it is the displacement commands of steering wheel that described upper computer comprises described total distance, longitudinal feathering, horizontal feathering and tail-rotor distance instruction transformation.
5. helicopter integrated ground test platform hydraulic control system as claimed in claim 4, is characterized in that: the matrix relationship that main pitch steering command is converted into main rudder machine displacement commands is
Wherein, Δ L
1for front main rudder machine displacement, Δ L
2for left main rudder machine displacement, Δ L
3for right main rudder machine displacement, a
ijfor constant (i, j are the integer of 1 ~ 3), θ
0.7for total distance, θ
sfor horizontal feathering, θ
cfor longitudinal feathering.
Tail-rotor is Δ L apart from the instruction morphing pass for tail-rotor steering wheel displacement commands
4=b θ
w,
Wherein, Δ L
4for tail-rotor steering wheel displacement, b is constant, θ
wfor tail-rotor distance.
6. helicopter integrated ground test platform hydraulic control system as claimed in claim 1, is characterized in that: the displacement commands that described analog quantity I/O module sends to the analog signal of steering engine controller to comprise front main rudder machine, left main rudder machine, right main rudder machine and tail actuator exports.
7. helicopter integrated ground test platform hydraulic control system as claimed in claim 1, is characterized in that: the feedback signal that described analog quantity I/O module receives described steering engine controller comprises the displacement of steering wheel, electric current and pressure feedback.
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105905315A (en) * | 2016-06-14 | 2016-08-31 | 苏州环球集团飞行机器人有限公司 | Unmanned helicopter test monitoring and control cabin |
| CN106553768A (en) * | 2016-11-30 | 2017-04-05 | 中国直升机设计研究所 | A kind of main oar steering wheel benchmark method of adjustment |
| CN106697305A (en) * | 2016-12-15 | 2017-05-24 | 哈尔滨飞机工业集团有限责任公司 | Duct reinforcing structure |
| CN108100234A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter tail rotor servo actuator benchmark method of adjustment |
| CN108918174A (en) * | 2018-08-16 | 2018-11-30 | 无锡市航鹄科技有限公司 | Steering gear flat synthetic performance evaluation system and its test method |
| CN109213004A (en) * | 2018-11-15 | 2019-01-15 | 中国直升机设计研究所 | A method of building the engine Real-Time Model of Helicopter Simulator |
| CN112278318A (en) * | 2020-09-22 | 2021-01-29 | 长沙五七一二飞机工业有限责任公司 | Helicopter hydraulic steering engine tester and test method |
| CN112407325A (en) * | 2020-11-10 | 2021-02-26 | 北京航空航天大学 | Instruction exciter for evaluating seaworthiness conformity of civil aircraft stability control characteristic |
| CN112498738A (en) * | 2020-12-11 | 2021-03-16 | 中国直升机设计研究所 | Helicopter flight control system transfer characteristic test method |
| CN112558585A (en) * | 2020-11-27 | 2021-03-26 | 中国商用飞机有限责任公司 | Automatic balancing control system, method and device for simulated flight of iron bird test bed |
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| CN112278318B (en) * | 2020-09-22 | 2022-05-17 | 长沙五七一二飞机工业有限责任公司 | Helicopter hydraulic steering engine tester and test method |
| CN112407325A (en) * | 2020-11-10 | 2021-02-26 | 北京航空航天大学 | Instruction exciter for evaluating seaworthiness conformity of civil aircraft stability control characteristic |
| CN112558585A (en) * | 2020-11-27 | 2021-03-26 | 中国商用飞机有限责任公司 | Automatic balancing control system, method and device for simulated flight of iron bird test bed |
| CN112498738A (en) * | 2020-12-11 | 2021-03-16 | 中国直升机设计研究所 | Helicopter flight control system transfer characteristic test method |
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