CN105314128B - A kind of helicopter integrated ground test platform hydraulic control system - Google Patents
A kind of helicopter integrated ground test platform hydraulic control system Download PDFInfo
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- CN105314128B CN105314128B CN201510745758.2A CN201510745758A CN105314128B CN 105314128 B CN105314128 B CN 105314128B CN 201510745758 A CN201510745758 A CN 201510745758A CN 105314128 B CN105314128 B CN 105314128B
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Abstract
The invention discloses a kind of helicopter integrated ground test platform hydraulic control system, belong to helicopter experimental technique field.The system includes：Host computer, to input instruction and possesses display processing function；Analog quantity I/O modules, carry out digital-to-analogue conversion；Steering engine controller, receives the data that analog quantity I/O modules are transmitted, and main rudder machine and tail actuator are controlled.Wherein, the helicopter integrated ground test platform hydraulic control system also includes hydraulic system, hydraulic pump in the hydraulic system as main reducing gear annex, master subtracts annex output shaft by engine driving, hydraulic pump connects the main rudder machine and tail actuator by valve and pipeline, and the main rudder machine, tail actuator and hydraulic system use airborne part.Helicopter integrated ground test platform hydraulic control system of the present invention can preferably helicopter simulating hydraulic control system real work state, preferably examine while helicopter hydraulic control system and ensure that the data of other pilot projects are more authentic and valid.
Description
Technical field
The invention belongs to helicopter experimental technique field, and in particular to a kind of helicopter integrated ground test platform hydraulic operation
System.
Background technology
Hydraulic control system as helicopter change always away from, feathering, tail-rotor away from power and executing agency, its function
It is all of crucial importance to helicopter airflight and ground experiment with performance.
To the helicopter using electric fly-by, the hydraulic control system related to flight attitude includes hydraulic oil container, hydraulic pressure
Pump, valve and fluid pressure line, driving leverage, flight control computer and main tail-rotor steering wheel.Hydraulic pump is in engine and the main drive subtracted
High pressure fuel source is provided for steering wheel action down, pilot control collective-pitch lever, control stick and pedal, mechanical signal are converted into voltage signal
It is converted into the electric signal of control steering wheel through flight control computer again afterwards, steering wheel makes controllable flexible change pitch, and it constitutes schematic diagram
See Fig. 1.Integrated ground test project is carried out by this way various, test period up to hundreds of hours, if being driven by driver
Cabin is manipulated, and noise and vibration are big, and working environment is severe, and driver is easily tired and safety can not ensure.
It is of the prior art to helicopter hydraulic control system experiment be using engine, rotor system and transmission system as
Testpieces, which is fixed on test-bed, carries out every experiment.Hydraulic control system includes ground hydraulic pumping plant, host computer, controller
Oil cylinder is manipulated with servo amplifier, servo valve and main tail.Ground hydraulic pumping plant provides high pressure fuel source, and operating personnel are soft in host computer
Part interface inputs control command, and via controller and servo amplifier are converted into current signal, controls the aperture of servo valve, and then control
The main tail-rotor in ground processed manipulates the stretching motion of the piston rod of oil cylinder, and schematic diagram is shown in Fig. 2.Hydraulic power unit is ground with manipulation oil cylinder
Non-standard, it is impossible to simulate the real work state of hydraulic control system, systemic-function and performance can not be verified.
The content of the invention
In order to solve the above problems, the invention provides a kind of helicopter integrated ground test platform hydraulic control system, bag
Include host computer, analog quantity I/O modules, steering engine controller and the hydraulic system on ground experiment machine and control vane mechanism into.Specifically
, including：
Host computer, sets instruction input function, and be provided with the function that feedback signal is shown；
Analog quantity I/O modules, receive the instruction input of the host computer, and the instruction input is converted into analog signal hair
Steering engine controller is given, meanwhile, in addition to the feedback signal of the steering engine controller is received, and the feedback signal is sent to
Position machine；
Steering engine controller, receives the analog signal that the analog quantity I/O modules are sent, and by the feedback signal back of steering wheel
To the analog quantity I/O modules, meanwhile, the steering engine controller also includes servo drive unit and exciting unit, described to watch
Taking driver element is used to carry out SERVO CONTROL and the carry out break-make processing to servo loop to steering wheel, and the exciting unit is used for
Excited signal is sent to realize the excitation of steering wheel displacement transducer；
Main rudder machine and tail actuator, respond the control instruction of the steering engine controller,
Wherein, the helicopter integrated ground test platform hydraulic control system also includes hydraulic system, the hydraulic system
In hydraulic pump be adjusted by engine driving, and by main reducing gear, hydraulic pump passes through valve and pipeline and connects the master
Steering wheel and tail actuator, the main rudder machine, tail actuator and hydraulic system use airborne part, and the main rudder machine includes preceding main rudder
Machine, left main rudder machine and right main rudder machine.
Preferably, the instruction input include always away from, horizontal feathering, longitudinal direction feathering, tail-rotor be away from four-way
Instruction input.
In such scheme preferably, the feedback signal includes described always away from, longitudinal feathering, horizontal cycle change
Away from, tail-rotor away from and steering wheel displacement and steering wheel electric current.
In such scheme preferably, include will be described always away from, longitudinal feathering, the change of transverse direction cycle for the host computer
Away from and tail-rotor away from instruction be converted to the displacement commands of steering wheel.
In such scheme preferably, the matrix relationship that main pitch control command is converted into main rudder machine displacement commands is
Wherein, Δ L1For preceding main rudder machine displacement, Δ L2For left main rudder machine displacement, Δ L3For right main rudder machine displacement, aij
For constant (i, j are 1~3 integer), θ0.7For always away from θsFor horizontal feathering, θcFor longitudinal feathering.
Tail-rotor away from it is instruction morphing be that the relations of tail-rotor steering wheel displacement commands is Δ L4=b θw,
Wherein, Δ L4For tail-rotor steering wheel displacement, b is constant, θwFor tail-rotor away from.
In such scheme preferably, the analog signal that the analog quantity I/O modules are sent to steering engine controller includes
Preceding main rudder machine, left main rudder machine, the displacement commands output of right main rudder machine and tail actuator.
In such scheme preferably, the analog quantity I/O modules receive the feedback signal bag of the steering engine controller
Include displacement, electric current and the pressure feedback of steering wheel.
The innovative point of the present invention is：
First, operating personnel remotely carry out input and the condition monitoring of control command；
Second, analog quantity I/O modules and steering engine controller are non-standard de-sign；
3rd, three main oar steering wheels and a tail-rotor steering wheel use airborne part；
4th, hydraulic system uses airborne part.
Using the hydraulic control system in the present invention, compared with the operating pattern on helicopter machine, operating personnel are remote to make an uproar
Sound, working environment is improved, and personal safety is protected；With traditional helicopter integrated ground test platform hydraulic control system
Compare, can preferably helicopter simulating hydraulic control system real work state, preferably examine helicopter hydraulic operation system
Ensure that the data of other pilot projects are more authentic and valid while system.
Brief description of the drawings
Fig. 1 is that hydraulic control system constitutes structural representation on conventional helicopters machine.
Fig. 2 is that prior art helicopter integrated ground test platform hydraulic control system constitutes schematic diagram.
It is originally that the helicopter integrated ground test platform hydraulic control system for inventing a preferred embodiment constitutes signal that Fig. 3, which is,
Figure.
Fig. 4 is the helicopter integrated ground test platform steerable system software front interface block diagram of embodiment illustrated in fig. 3.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
Hydraulic control system in the present invention is on host computer, analog quantity I/O modules, steering engine controller and ground experiment machine
Hydraulic system and control vane mechanism into system constitutes sketch and sees accompanying drawing 3.Hydraulic pump is in the case where engine and master subtract drive on machine
Main tail-rotor steering wheel provides high pressure fuel source, and operator completes in the observing and controlling away from test-bed in upper computer software interface
The input of control command and condition monitoring.Operator's working environment can be substantially improved using the present invention, it is ensured that personal security, together
When preferably simulate the real work state of hydraulic control system.
The helicopter integrated ground test platform hydraulic control system of the present embodiment mainly includes：
Host computer, sets instruction input function, and be provided with the function that feedback signal is shown；
Analog quantity I/O modules, receive the instruction input of the host computer, and the instruction input is converted into analog signal hair
Steering engine controller is given, meanwhile, in addition to the feedback signal of the steering engine controller is received, and the feedback signal is sent to
Position machine；It should be noted that analog quantity I/O module channels number must be more than the port number needed.
Steering engine controller, receives the analog signal that the analog quantity I/O modules are sent, and by the feedback signal back of steering wheel
To the analog quantity I/O modules, meanwhile, the steering engine controller also includes servo drive unit and exciting unit, described to watch
Taking driver element is used to carry out SERVO CONTROL and the carry out break-make processing to servo loop to steering wheel, and the exciting unit is used for
Excited signal is sent to realize the excitation of steering wheel displacement transducer；In the present embodiment, steering engine controller composes steering wheel displacement movement
Instruction passes to 4 steering wheels in electrical signal form, 3 main oar steering wheels of control and 1 tail-rotor steering wheel according to the motion of regulation compose into
Row motion, and movement position can accurately be controlled.It is understood that it must possess the driving of four steering wheel servo valves
Ability.
Main rudder machine and tail actuator, respond the control instruction of the steering engine controller,
Wherein, the helicopter integrated ground test platform hydraulic control system also includes hydraulic system, the hydraulic system
In hydraulic pump hydraulic pump as main reducing gear annex, master subtract annex output shaft by engine driving, hydraulic pump passes through valve
The main rudder machine and tail actuator are connected with pipeline, the main rudder machine, tail actuator and hydraulic system use airborne part.
In the present embodiment, the instruction input include always away from, horizontal feathering, longitudinal direction feathering, tail-rotor be away from four-way
The instruction input in road.
The feedback signal include it is described always away from, longitudinal feathering, transverse direction feathering, tail-rotor away from and steering wheel displacement with
And steering wheel electric current.
The host computer include will it is described always away from, longitudinal feathering, horizontal feathering and tail-rotor be away from instructing conversion
For the displacement commands of steering wheel.
The matrix relationship that main pitch control command is converted into main rudder machine displacement commands is
Wherein, Δ L1For preceding main rudder machine displacement, Δ L2For left main rudder machine displacement, Δ L3For right main rudder machine displacement, aij
For constant (i, j are 1~3 integer), θ0.7For always away from θsFor horizontal feathering, θcFor longitudinal feathering.
Tail-rotor away from it is instruction morphing be that the relations of tail-rotor steering wheel displacement commands is Δ L4=b θw,
Wherein, Δ L4For tail-rotor steering wheel displacement, b is constant, θwFor tail-rotor away from.
In such scheme preferably, the analog signal that the analog quantity I/O modules are sent to steering engine controller includes
Preceding main rudder machine, left main rudder machine, the displacement commands output of right main rudder machine and tail actuator.
In such scheme preferably, the analog quantity I/O modules receive the feedback signal bag of the steering engine controller
Include displacement, electric current and the pressure feedback of steering wheel.
The innovative point of the present invention is：
First, operating personnel remotely carry out input and the condition monitoring of control command；
Second, analog quantity I/O modules and steering engine controller are non-standard de-sign；
3rd, three main oar steering wheels and a tail-rotor steering wheel use airborne part；
4th, hydraulic system uses airborne part.
Using the hydraulic control system in the present invention, compared with the operating pattern on helicopter machine, operating personnel are remote to make an uproar
Sound, working environment is improved, and personal safety is protected；With traditional helicopter integrated ground test platform hydraulic control system
Compare, can preferably helicopter simulating hydraulic control system real work state, preferably examine helicopter hydraulic operation system
Ensure that the data of other pilot projects are more authentic and valid while system.
Helicopter integrated ground test platform steerable system software front interface is as shown in Figure 4.Manipulation of the operating personnel at interface
The input of instruction input area always away from, horizontal feathering, longitudinal direction feathering, tail-rotor away from control command, in operation state curve
Viewing area and steering wheel status display area are monitored to current operation state and steering wheel parameter；Background program realizes control command
With the mutual conversion of steering wheel displacement commands.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (7)
1. a kind of helicopter integrated ground test platform hydraulic control system, it is characterised in that including：
Host computer, sets instruction input function, and be provided with the function that feedback signal is shown；
Analog quantity I/O modules, receive the instruction input of the host computer, and the instruction input is converted into analog signal are sent to
Steering engine controller, meanwhile, include receiving the feedback signal of the steering engine controller, and the feedback signal is sent to upper
Machine；
Steering engine controller, receives the analog signal that the analog quantity I/O modules are sent, and by the feedback signal back of steering wheel to institute
Analog quantity I/O modules are stated, meanwhile, the steering engine controller also includes servo drive unit and exciting unit, and the servo is driven
Moving cell is used to carry out steering wheel SERVO CONTROL and the carry out break-make processing to servo loop, and the exciting unit is used to send
Excited signal is to realize the excitation of steering wheel displacement transducer；
Main rudder machine and tail actuator, respond the control instruction of the steering engine controller,
Wherein, the helicopter integrated ground test platform hydraulic control system also includes in hydraulic system, the hydraulic system
Hydraulic pump is as the annex of main reducing gear, and its output shaft is by engine driving, and hydraulic pump passes through valve and pipeline connects the master
Steering wheel and tail actuator, the main rudder machine, tail actuator and hydraulic system use airborne part, and the main rudder machine includes preceding 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, it is characterised in that：The instruction is defeated
Enter including always away from, horizontal feathering, the longitudinal instruction input of feathering, tail-rotor away from four-way.
3. helicopter integrated ground test platform hydraulic control system as claimed in claim 2, it is characterised in that：The feedback letter
Number include it is described always away from, longitudinal feathering, transverse direction feathering, tail-rotor away from and steering wheel displacement and steering wheel electric current.
4. helicopter integrated ground test platform hydraulic control system as claimed in claim 3, it is characterised in that：The host computer
Including by it is described always away from, longitudinal feathering, horizontal feathering and tail-rotor the displacement commands of steering wheel are converted to away from instruction.
5. helicopter integrated ground test platform hydraulic control system as claimed in claim 4, it is characterised in that：Main pitch is manipulated
Instruction morphing is that the matrix relationship of main steering wheel displacement commands is
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Wherein, Δ L1For preceding main rudder machine displacement, Δ L2For left main rudder machine displacement, Δ L3For right main rudder machine displacement, aijTo be normal
Number (i, j are 1~3 integer), θ0.7For always away from θsFor horizontal feathering, θcFor longitudinal feathering；
Tail-rotor away from it is instruction morphing be that the relations of tail-rotor steering wheel displacement commands is Δ L4=b θw,
Wherein, Δ L4For tail-rotor steering wheel displacement, b is constant, θwFor tail-rotor away from.
6. helicopter integrated ground test platform hydraulic control system as claimed in claim 1, it is characterised in that：The analog quantity
The analog signal that I/O modules are sent to steering engine controller includes the displacement of preceding main rudder machine, left main rudder machine, right main rudder machine and tail actuator
Instruction output.
7. helicopter integrated ground test platform hydraulic control system as claimed in claim 1, it is characterised in that：The analog quantity
The feedback signal that I/O modules receive the steering engine controller includes displacement, electric current and the pressure feedback of steering wheel.
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| CN201510745758.2A CN105314128B (en) | 2015-11-04 | 2015-11-04 | A kind of helicopter integrated ground test platform hydraulic control system |
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| CN105314128B true CN105314128B (en) | 2017-08-29 |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105905315B (en) * | 2016-06-14 | 2017-12-29 | 苏州环球电梯机械传动有限公司 | A kind of depopulated helicopter test monitoring control cabinet |
| CN106553768B (en) * | 2016-11-30 | 2018-10-02 | 中国直升机设计研究所 | A kind of main paddle steering engine 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 |
| CN108918174B (en) * | 2018-08-16 | 2020-01-10 | 无锡市航鹄科技有限公司 | Comprehensive performance evaluation system of rudder engine room and test method thereof |
| 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 |
| 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 |
| CN112407325B (en) * | 2020-11-10 | 2022-03-29 | 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 |
| CN112498738B (en) * | 2020-12-11 | 2022-10-18 | 中国直升机设计研究所 | Helicopter flight control system transfer characteristic test method |
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