CN103308295A - Control and check test method for flight control mechanical control system - Google Patents
Control and check test method for flight control mechanical control system Download PDFInfo
- Publication number
- CN103308295A CN103308295A CN2013101941703A CN201310194170A CN103308295A CN 103308295 A CN103308295 A CN 103308295A CN 2013101941703 A CN2013101941703 A CN 2013101941703A CN 201310194170 A CN201310194170 A CN 201310194170A CN 103308295 A CN103308295 A CN 103308295A
- Authority
- CN
- China
- Prior art keywords
- control
- control system
- fuselage wing
- test method
- stick force
- 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.)
- Pending
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to the field of control systems of aviation aircrafts and particularly relates to a control and check test method for a flight control mechanical control system. The test process of the control and check test method is controlled at a steering column and foot boards and the influence on the whole control system caused by the deformation of aerofoils of an aircraft body is fully considered. According to the control and check test method disclosed by the invention, a column force of the steering column and pedal force data of the foot boards can be measured; the influence on the control system caused by the deformation of the aerofoils of the aircraft body can be reflected in a data and diagram form; gradation loading and gradation measurement can be realized by controlling at the steering column and the foot boards; column force curves under the condition that the aerofoils of the aircraft body are not loaded and under the condition that the aerofoils of the aircraft body are loaded to 67 percent of limit load can be drawn by the column force measured at each-stage loading phase; whether the clamping stagnation phenomenon exists in the control system or not is judged by using the column force curves obtained by analyzing; and if the clamping stagnation condition exists in the control system, the clamping stagnation condition can be visually reflected from a curve graph.
Description
Technical field
The invention belongs to aviation aircraft control system field, particularly relate to a kind of mechanical manoeuvring system manipulation check test method that flies to control.
Background technology
It is by the ground control enclosure aircraft actuator to be handled that aircraft flies to control mechanical manoeuvring system manipulation check test method, realizes control surface deflection.The shortcoming of the method is: owing to only handling at the actuator place in the process of the test, do not examine for actuator front control system to put in place, can not fully examine whole control system to be subject to the influence degree of fuselage wing distortion; Secondly, the method can't be measured the stick force of jociey stick and the pedal power data of pedal, can not reflect that the distortion of fuselage wing is on the impact of control system; The method can't be measured the situation of change of cable tension in manipulation process; The method can not realize the classification measurement by simple and easy ground control enclosure primary control surface, can only realize opening and closing two manipulations.
Summary of the invention
The objective of the invention is: provide a kind of and can reflect accurately that frame deflection flies to control mechanical manoeuvring system to operating system impact a kind of and handles the check test method.
Technical scheme of the present invention is: a kind ofly fly to control mechanical manoeuvring system and handle the check test method, may further comprise the steps:
Step 1, control wheel and pedal are prepared corresponding charger, drive simulating person's normal manipulation;
Step 2, in the situation that the fuselage wing does not load, measure step by step according to the rank of five equilibrium and fly to control mechanical manoeuvring system stick force, bar displacement, strain data, cable tension and rudder face drift angle, draw not stick force bar displacement curve figure under the load condition of fuselage wing;
Step 3, according to the serious load condition of the fuselage wing of selecting, the fuselage wing is loaded into limit load;
Step 4, measure step by step according to the rank of five equilibrium and to fly to control mechanical manoeuvring system stick force, bar displacement, strain data, cable tension and rudder face drift angle, draw stick force bar displacement curve figure under the fuselage wing load condition;
Advantage of the present invention is: process of the test of the present invention is handled at jociey stick and pedal place, fully examines whole control system to be subject to the impact of fuselage wing distortion; The present invention can measure the stick force of jociey stick and the pedal power data of pedal, can reflect that with the form of data and chart the distortion of fuselage wing is on the impact of control system; The present invention can also measure the situation of change of cable tension in manipulation process, by tensiometer manual measurement frame sections cable tension, understands the situation that affects that cable tension is subjected to the distortion of fuselage wing.The present invention is by handling at jociey stick and pedal place, can realize hierarchical loading, classification is measured, the stick force that records by load phase at different levels, can draw out the fuselage wing not under the load condition and the fuselage wing be loaded into stick force curve in the 67% ultimate load situation, analyze the stick force curve that obtains, judge whether control system exists catching phenomenon, if there is the clamping stagnation situation in control system, can reflect from curve map intuitively.
Description of drawings
Fig. 1 is that the embodiment of the invention 1 middle machine body wing does not load/loads and reaches stick force bar displacement curve figure in the 67% ultimate load situation;
Fig. 2 is that the embodiment of the invention 2 middle machine body wings do not load/load and reach stick force bar displacement curve figure in the 67% ultimate load situation.
Embodiment
Below in conjunction with example and accompanying drawing the present invention is done and to describe in further detail.
A kind ofly fly to control mechanical manoeuvring system and handle the check test method, may further comprise the steps:
Step 1, control wheel and pedal are prepared corresponding charger, comprise pressurized strut and custom-designed control wheel bogusware and pedal bogusware, connect pressurized strut and control wheel bogusware and pedal bogusware, drive simulating person's normal manipulation;
Step 2, in the situation that the fuselage wing do not load, rank (generally will before push away backhitch process is divided into ten grades) according to five equilibrium loads step by step, the classification measurement flies to control mechanical manoeuvring system stick force, bar displacement, strain data, cable tension and rudder face drift angle, draws not load condition lower beam force curve figure of fuselage wing.Repeat this process three times;
Step 3, according to the maximum condition of fuselage wing distortion, select the serious load condition of fuselage wing, the fuselage wing is loaded into the limit load of respective loads situation, protect and carry;
Step 4, measure step by step according to the rank of five equilibrium and to fly to control mechanical manoeuvring system stick force, bar displacement, strain data, cable tension and rudder face drift angle, draw stick force bar displacement curve figure (explanation under the fuselage wing load condition, general fuselage wing requires to protect and carried 30 seconds, if can't finish corresponding control system in 30 seconds loads and surveying work, can adopt without hierarchical loading control system and walk continuously spectrum, the mode of real-time data collection is tested).
Step 6, comparative analysis step 2 and step 4 curve obtained figure if the stick force difference, illustrates then that flying to control mechanical manoeuvring system clamping stagnation occurs greater than 20%, otherwise fly to control mechanical manoeuvring system without catching phenomenon.
Embodiment 1: the situation that clamping stagnation is arranged.
The aircraft elevator-control system is handled check test, as shown in Figure 1.
Comprised the fuselage wing among Fig. 1 and do not loaded, and the fuselage wing is loaded on the stick force curve that records in two kinds of situations of 67% ultimate load.Can be clearly seen that among Fig. 1, when level V loaded, the fuselage wing was loaded on stick force in the 67% ultimate load situation and surpasses the fuselage wing load condition is not more than 20%, and this moment, there was catching phenomenon in elevator-control system.
Embodiment 2: without the situation of clamping stagnation.
Aircraft rudder control system manipulation check test, as shown in Figure 2.
Comprised the fuselage wing among Fig. 2 and do not loaded, and the fuselage wing is loaded on the stick force curve that records in two kinds of situations of 67% ultimate load.Can be clearly seen that among Fig. 2, the stick force curve that records in two kinds of situations does not have larger difference, the rudder control system in the situation that the distortion of fuselage wing without catching phenomenon.
Claims (1)
1. one kind flies to control mechanical manoeuvring system manipulation check test method, it is characterized in that, may further comprise the steps:
Step 1, control wheel and pedal are prepared corresponding charger, drive simulating person's normal manipulation;
Step 2, in the situation that the fuselage wing does not load, measure step by step according to the rank of five equilibrium and fly to control mechanical manoeuvring system stick force, bar displacement, strain data, cable tension and rudder face drift angle, draw not stick force bar displacement curve figure under the load condition of fuselage wing;
Step 3, according to the serious load condition of the fuselage wing of selecting, the fuselage wing is loaded into limit load;
Step 4, measure step by step according to the rank of five equilibrium and to fly to control mechanical manoeuvring system stick force, bar displacement, strain data, cable tension and rudder face drift angle, draw stick force bar displacement curve figure under the fuselage wing load condition;
Step 5, comparative analysis step 2 and step 4 curve obtained figure if the stick force difference, illustrates then that flying to control mechanical manoeuvring system clamping stagnation occurs greater than 20%, otherwise fly to control mechanical manoeuvring system without catching phenomenon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101941703A CN103308295A (en) | 2013-01-05 | 2013-05-23 | Control and check test method for flight control mechanical control system |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310002840.7 | 2013-01-05 | ||
| CN201310002840 | 2013-01-05 | ||
| CN2013101941703A CN103308295A (en) | 2013-01-05 | 2013-05-23 | Control and check test method for flight control mechanical control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103308295A true CN103308295A (en) | 2013-09-18 |
Family
ID=49133760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013101941703A Pending CN103308295A (en) | 2013-01-05 | 2013-05-23 | Control and check test method for flight control mechanical control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103308295A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105091691A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Method for calibrating control system parameters of flight parameter system |
| CN108447334A (en) * | 2018-04-08 | 2018-08-24 | 中国民航大学 | A kind of flight control system transmission parts dismounting calibration training system |
| CN110987421A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Dynamic fatigue test support method for whole-machine main control system |
| CN110987422A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Component looseness checking method for aircraft control system dynamic fatigue test |
| CN110987420A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Operating force and operating displacement detection method |
| CN111122200A (en) * | 2019-12-31 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | On-site maintenance and inspection method for fatigue test of main control system of whole aircraft |
| CN112415979A (en) * | 2020-10-30 | 2021-02-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control test system, method, equipment and storage medium |
| 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 |
| CN112798271A (en) * | 2020-12-25 | 2021-05-14 | 兰州飞行控制有限责任公司 | Test equipment and test method for pitching operation of main flight control cockpit device |
| CN113955144A (en) * | 2021-09-16 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test loading and unloading protection method for main control system of airplane |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1607558A1 (en) * | 1989-04-11 | 1994-11-30 | В.А. Сумароков | Device for test strength of flap of aircraft |
| CN1512149A (en) * | 2002-12-31 | 2004-07-14 | 中国农业机械化科学研究院 | On-site calibrating test method and its device for landing gear load |
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| CN101769808A (en) * | 2010-03-08 | 2010-07-07 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft driving lever force measuring component and measuring method thereof |
| CN102141493A (en) * | 2010-12-14 | 2011-08-03 | 中国飞机强度研究所 | Test loading device of airplane joystick type control system |
| CN102645299A (en) * | 2012-05-11 | 2012-08-22 | 中国商用飞机有限责任公司 | Comprehensive testing device and method for rudder pedal force and angle in control cabin |
| CN102645324A (en) * | 2011-02-22 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane operation force and operation displacement simulating method |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
-
2013
- 2013-05-23 CN CN2013101941703A patent/CN103308295A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1607558A1 (en) * | 1989-04-11 | 1994-11-30 | В.А. Сумароков | Device for test strength of flap of aircraft |
| CN1512149A (en) * | 2002-12-31 | 2004-07-14 | 中国农业机械化科学研究院 | On-site calibrating test method and its device for landing gear load |
| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| CN101769808A (en) * | 2010-03-08 | 2010-07-07 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft driving lever force measuring component and measuring method thereof |
| CN102141493A (en) * | 2010-12-14 | 2011-08-03 | 中国飞机强度研究所 | Test loading device of airplane joystick type control system |
| CN102645324A (en) * | 2011-02-22 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane operation force and operation displacement simulating method |
| CN102645299A (en) * | 2012-05-11 | 2012-08-22 | 中国商用飞机有限责任公司 | Comprehensive testing device and method for rudder pedal force and angle in control cabin |
| CN102680221A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test method for full-aircraft main operating system of aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 卢京明等: "飞机主操纵系统疲劳试验载荷监控方法研究――应变数据分析法", 《飞机设计》, no. 2, 30 June 2006 (2006-06-30) * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105091691A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Method for calibrating control system parameters of flight parameter system |
| CN108447334A (en) * | 2018-04-08 | 2018-08-24 | 中国民航大学 | A kind of flight control system transmission parts dismounting calibration training system |
| CN110987421A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Dynamic fatigue test support method for whole-machine main control system |
| CN110987422A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Component looseness checking method for aircraft control system dynamic fatigue test |
| CN110987420A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Operating force and operating displacement detection method |
| CN110987420B (en) * | 2019-12-25 | 2021-11-02 | 中国航空工业集团公司西安飞机设计研究所 | Operating force and operating displacement detection method |
| CN111122200A (en) * | 2019-12-31 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | On-site maintenance and inspection method for fatigue test of main control system of whole aircraft |
| CN112415979A (en) * | 2020-10-30 | 2021-02-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control test system, method, equipment and storage medium |
| CN112415979B (en) * | 2020-10-30 | 2021-11-09 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Flight control test system, method, equipment and storage medium |
| 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 |
| CN112798271A (en) * | 2020-12-25 | 2021-05-14 | 兰州飞行控制有限责任公司 | Test equipment and test method for pitching operation of main flight control cockpit device |
| CN113955144A (en) * | 2021-09-16 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Fatigue test loading and unloading protection method for main control system of airplane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103308295A (en) | Control and check test method for flight control mechanical control system | |
| CN104298804A (en) | Flight load design method | |
| CN110654569B (en) | Load simulation simplification method for helicopter tail section fatigue test | |
| CN103287574A (en) | Control method of high-lift device of airplane | |
| CN106800095B (en) | Method is determined based on the telescopic landing gear calibration load of buffer compression travel | |
| Bauknecht et al. | Wind tunnel test of a rotorcraft with lift compounding | |
| Britt et al. | Wind tunnel test of a very flexible aircraft wing | |
| Ouellette | Flight dynamics and maneuver loads on a commercial aircraft with discrete source damage | |
| CN112149299B (en) | Optimized analysis method for test flight task for data packet development of flight simulator | |
| McDonald et al. | Carrier Landing Simulation using Detailed Aircraft and Landing | |
| Chinvorarat et al. | Static testing for composite wing of a two-seater seaplane | |
| CN105335574A (en) | Aircraft interior cabin door load design method | |
| Mangalam et al. | Unsteady aerodynamic observables for gust load alleviation | |
| Kurukularachchi et al. | Stability and control analysis in twin-boom vertical stabilizer Unmanned Aerial Vehicle (UAV) | |
| Leski et al. | Development of load spectrum for full scale fatigue test of a trainer aircraft | |
| Gripp et al. | Configuration of aerodynamics model in flight simulator to investigate Pilot-Induced Oscillations and Loss of Control | |
| Pytka et al. | Measurement of forces and moments acting on aircraft landing gear wheel | |
| Ouellette et al. | Flight dynamics and structural load distribution for a damaged aircraft | |
| Nguyen et al. | A Frequency-Domain Approach to Analysing Dynamic Deep Stall Recovery | |
| Cumnuantip et al. | Methods for the quantification of aircraft loads in DLR-Project iLOADS | |
| Wan et al. | Static aeroelastic analysis of a high-aspect-ratio wing based on wind-tunnel experimental aerodynamic forces | |
| Soetanto et al. | Study the Strength of Material and Composite Structures of Belly-Landing Mini UAV | |
| Cook et al. | Integrated approach to assessment of transonic abrupt wing stall for advanced aircraft | |
| Kater | Mathematical modeling, motion planning and control of elastic structures with piezoelectric elements | |
| Suleman et al. | Active aeroelastic aircraft structures |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130918 |