CN102001444B - Neutral position adjustment device of flight control system and neutral position setting method thereof - Google Patents
Neutral position adjustment device of flight control system and neutral position setting method thereof Download PDFInfo
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- CN102001444B CN102001444B CN201010550542.8A CN201010550542A CN102001444B CN 102001444 B CN102001444 B CN 102001444B CN 201010550542 A CN201010550542 A CN 201010550542A CN 102001444 B CN102001444 B CN 102001444B
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Abstract
The invention belongs to the adjustment and control techniques of a flight control system and relates to a neutral position adjustment device of the flight control system. The neutral position adjustment device of the flight control system comprises a moving part at the transfer site of the system, a fixed base and a neutral pin, wherein the moving part and the fixed base are internally provided with neutral position holes with consistent sizes, and the neutral position holes are integrally connected through the neutral pin; and bushings are pressed in the neutral position holes of the moving part and the fixed base. The neutral position adjustment device of the flight control system simplifies the system adjustment process, decreases the repeated work, shortens the system adjustment period, and ensures the favorable neutrality of a linear system of the control system and the adjustment state of the system. Furthermore, the invention provides a neutral position setting method of the flight control system.
Description
Technical field
The present invention is the adjustment control technology of flight control system, relates to a kind of flight control system neutral position setting device and neutral position method to set up thereof.
Background technology
Flight control system comprises elevator-control system, Aileron control system and rudder control system, realizes pitching, rolling and driftage for operating aircraft.As the critical function system of aircraft, the design of flight control system is vital, and it directly affects the flight safety of aircraft.
General big-and-middle-sized aircraft manual control system linear system is long, from driving compartment to rudder face between drive connection more complicated, need to pass through more intermediate conversion links, so system adjustment difficulty is large.Because too much drive system parts all can produce tolerance in manufacture, installation process, the result of tolerance accumulative total directly affects the system adjustment of aircraft, and system adjustment not only will reduce to minimum by parts manufacture, the location tolerance accumulative total in early stage, and to guarantee the good order and condition of maneuvering system.If transmission link is adjusted and not in placely will be needed more position to compensate, sometimes even the surplus of design compensation is all inadequate, the state that system is adjusted is just very undesirable, now just have a lot of positions and occur that off-gage phenomenon (for example: rudder face aperture is inadequate, pull rod screw is leaked button, parts side-to-side movement is asymmetric, system gap is little, system manipulation power uneven with etc.), make the final condition variation of system, have influence on whole system state, the final state that affects the maneuvering system of aircraft, and then affect the handling quality of aircraft, therefore the adjustment final condition of the maneuvering system of aircraft is quite important.
The shortcomings such as the conformability complicated owing to existing in system adjustment, the cycle long, the amount of doing over again is large, state of the system is difficult for guaranteeing, every machine system is adjusted state or proximity are poor, give design, produce and cause a lot of puzzlements, existing technology lacks actv. method of adjustment to flight control system, general by manually adjusting piecemeal, repeatedly work many, work capacity is large, and adjustment cycle is long.
Summary of the invention
The object of the invention is: provide one can simplify the adjustment of airplane operation system, reduce repeatedly work, the system adjustment cycle of making significantly shortens, can obtain the flight control system neutral position setting device of good state of the system.
In addition, the present invention also provides the neutral position method to set up in a kind of airplane operation system.
Technical scheme of the present invention is: a kind of flight control system neutral position setting device, it comprises system motion part, firm banking and middle vertical pin, wherein, be respectively arranged with the neutral position hole of consistent size in moving parts and firm banking, the two is connected to an entirety by middle vertical pin.
In the neutral position hole of moving parts and firm banking, be suppressed with lining.
Described moving parts and firm banking are the switch site of system.
A kind of flight control system neutral position method to set up, its step is as follows:
The first step: according to maneuvering system motion diagram, select important, the key link of maneuvering system and conversion links as the suitable set-point of neutral position setting device;
Second step: according to maneuvering system motion diagram, determine the moving parts neutral position at neutral position setting device set-point place;
The 3rd step: the center position according to moving parts with respect to firm banking, in moving parts and firm banking, design respectively neutral position hole, and the position, neutral position hole of moving parts and firm banking should be on same axis;
The 4th step: will be pressed in neutral position hole with the lining of stock left for machining, then moving parts and firm banking are assembled into a global facility;
The 5th step: the center position according to moving parts with respect to firm banking, the firm banking that is pressed with lining is reamed together with moving parts, require the coaxial and consistent size in neutral position hole in moving parts and firm banking;
The 6th step: in the time carrying out maneuvering system adjustment, the neutral position hole of middle vertical pin being inserted simultaneously to firm banking and moving parts, thereby the neutral position at definite this link place.
The invention has the beneficial effects as follows: the present invention arranges neutral position by the conversion links place in flight control system the shortcoming such as the conformability that solved system adjustment complexity, the cycle is long, the amount of doing over again is large, state of the system is difficult for guaranteeing, every machine system is adjusted state or proximity are poor.Not only make the adjustment of system sectional, simplify system adjustment process, reduce and repeatedly work, shorten system adjustment cycle, and guarantee neutrality that maneuvering system linear system is good and the adjustment state of system.
Accompanying drawing explanation
Fig. 1 is aircraft outer panel Aileron control system motion diagram.
Fig. 2 is the scheme of installation of fan-shaped rocker arm assembly in outer panel Aileron control system;
Fig. 3 is the A-A cutaway view of Fig. 2;
Fig. 4 is sectional wheel structural representation;
Fig. 5 is the structural representation of support,
Wherein, 1-fan-shaped rocker arm assembly, 2-soft cable wire, 3-sectional wheel, 4-rocking arm, 5-rigid rod, 6-middle vertical pin, 7-support, 8-neutral position hole, 9-lining.
The specific embodiment
Flight control system neutral position setting device of the present invention comprises moving parts, firm banking, lining, the middle vertical pin by system switch site.Wherein, moving parts is arranged in firm banking, the two is fixed as an entirety by middle vertical pin, and described lining designs respectively the parts depreciation being caused while adjustment with minimizing system on moving parts and firm banking, the error between compensating motion part and firm banking.
In the time that maneuvering system is adjusted, utilize flight control system neutral position setting device that each important step of system is fixed on to neutral position, then the cylinder lever connecting rod length of the links of adjustment System, coarse adjustment system cable tension etc. make the input and output of system unified as the case may be, that is: the neutral position of rudder face and hand (pin) steering unit is unified, then make the neutral position of system links unified, after reunification, vertical pin in taking-up, carries out follow-up dynamic adjustment to the system neutral position for the treatment of.
Not every link setting in linear system of maneuvering system neutral position setting device of the present invention, what neither arrange is The more the better, because linear system is long, conversion links is many, cannot guarantee that each position can reach requirement, the neutral position of now likely having ignored the significant points of system, to system, adjustment makes troubles so on the contrary.Neutral position setting device is set inadequate or not in placely also can increase system adjust burden, so maneuvering system neutral position setting device is furnished with certain being particular about in linear system.
According to the feature of flight control system, driving compartment is analyzed to contrast to the drive path of rudder face, select the suitable point in linear system somewhere that neutral position device is set, then carry out the comprehensive analytic demonstration of pros and cons, final set-point of planning as a whole this device, as long as guarantee the linear system adjustment of these set-point center positions, system is adjusted state and just can be guaranteed.Generally, maneuvering system neutral position setting device is important using maneuvering system, key link and conversion links place be as suitable design point, wherein, rigid rod and soft cable wire transmission conversion place, system linear system commutation Amplitude Ratio larger part etc. are maneuvering system important step, are important, the key link of maneuvering system as jociey stick in maneuvering system (dish) steering unit, pin steering unit, reversible or irreversible servo-unit, drift angle restraint device, arm regulator, nonlinearizer, power-transfer clutch etc.
When the design of flight control system neutral position setting device, according under system analysis and unified coordination, at definite maneuvering system transmission link design neutral position device.Provide maneuvering system neutral position method of designing of the present invention below, its step is as follows:
The first step: according to maneuvering system motion diagram,, key link important using maneuvering system and conversion links are as the suitable set-point of neutral position setting device, and wherein, maneuvering system motion diagram is systematic schematic diagram;
Second step: according to maneuvering system motion diagram, determine the moving parts neutral position at neutral position setting device set-point place;
The 3rd step: the center position according to moving parts with respect to firm banking, in moving parts and firm banking, design respectively neutral position hole, and the position, neutral position hole of moving parts and firm banking should be on same axis;
The 4th step: will be pressed in neutral position hole with the lining of stock left for machining, then moving parts and firm banking are assembled into a global facility;
The 5th step: the center position according to moving parts with respect to firm banking, the firm banking that is pressed with lining is reamed together with moving parts, require the coaxial and consistent size in neutral position hole in moving parts and firm banking;
The 6th step: the moving parts and the firm banking that are assembled into one are installed aboard, in the time carrying out maneuvering system adjustment, the neutral position hole of middle vertical pin being inserted to firm banking and moving parts, thereby the neutral position at definite this link place.
In present embodiment, take outer panel Aileron control system as example, according to outer panel Aileron control system motion diagram (see figure 1), using the soft or hard conversion links of soft cable wire 1 and rigid rod 2 as suitable set-point.Again according to maneuvering system motion diagram, can see Derivative limit on the left or on the right and its center position (seeing a in Fig. 1, b, c position) of moving parts motion, thereby the neutral position of determining the fan-shaped rocker arm assembly of moving parts at set-point place, wherein, fan-shaped rocker arm assembly comprises sectional wheel and rocking arm; Then on sectional wheel and the support as firm banking, neutral position hole is set respectively, will be compressed in neutral position hole with the lining of stock left for machining, and fan-shaped rocker arm assembly docking is fixed on support; The sectional wheel that is pressed with lining is reamed together with support, require the coaxial and consistent size in the two neutral position hole; In the time carrying out maneuvering system adjustment, the neutral position hole by middle vertical pin through sectional wheel and support, thereby the neutral position at definite outer panel Aileron control system soft or hard conversion links place.
Please refer to Fig. 2, Fig. 3, Fig. 4 and Fig. 5, wherein Fig. 2 is the scheme of installation of fan-shaped rocker arm assembly in outer panel Aileron control system, and Fig. 3 is the A-A cutaway view of Fig. 2, and Fig. 4 and Fig. 5 are respectively the structural representations of sectional wheel and support.Wherein, described sectional wheel setting is arranged in support, and both fix by bearing.In neutral position hole on neutral position hole and support on sectional wheel, be all suppressed with lining, and the two is coaxially relative, connected by neutral position pin, thus the neutral position at definite outer panel Aileron control system soft or hard conversion links place, can effectively guarantee the neutral position state of system in system adjustment.Wherein, the described lining aperture specification normalisation of trying one's best, so that the later stage is used the pin of standard as the middle vertical pin at this place, can reduce costs.
In addition, flight control system neutral position setting device of the present invention can also design in the mechanisms such as servo-unit, aileron drift angle restraint device, power-transfer clutch, the work capacity repeatedly when the system that can effectively reduce is adjusted.The shortcomings such as the conformability that the invention solves that system adjustment complexity, cycle are long, the amount of doing over again is large, state of the system is difficult for guaranteeing, every machine system is adjusted state or proximity are poor, not only make the adjustment of system sectional, simplification system adjustment process, shortening system adjustment cycle, and guarantee the neutrality of maneuvering system linear system and the adjustment state of system.
Flight control system neutral position setting device of the present invention is verified on certain serial emphasis model aircraft, through relevant departments' reaction, system adjustment process is simplified, repeatedly working, obviously minimizing, system adjustment cycle shorten greatly, state of the system also easily guarantees, reaction effect is good, has good prospect of the application.
Claims (1)
1. a flight control system neutral position method to set up, is characterized in that, step is as follows:
The first step: according to maneuvering system motion diagram, select important, the key link of maneuvering system and conversion links as the suitable setting of neutral position setting device;
Second step: according to maneuvering system motion diagram, determine the moving parts neutral position at neutral position setting device set-point place;
The 3rd step: the center position according to moving parts with respect to firm banking designs respectively neutral position hole in moving parts and firm banking;
The 4th step: the lining with stock left for machining is pressed into respectively in the neutral position hole on moving parts and firm banking, then moving parts and firm banking is assembled into a global facility;
The 5th step: the center position according to moving parts with respect to firm banking, the firm banking that is pressed with lining is reamed together with moving parts, require the coaxial and consistent size in neutral position hole in moving parts and firm banking;
The 6th step: in the time carrying out maneuvering system adjustment, the neutral position hole of middle vertical pin being inserted simultaneously to firm banking and moving parts, thereby the neutral position at definite this link place.
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| CN201010550542.8A CN102001444B (en) | 2010-11-19 | 2010-11-19 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
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| CN201010550542.8A CN102001444B (en) | 2010-11-19 | 2010-11-19 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
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| CN102001444A CN102001444A (en) | 2011-04-06 |
| CN102001444B true CN102001444B (en) | 2014-06-11 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103661923B (en) * | 2013-11-28 | 2016-03-30 | 江西洪都航空工业集团有限责任公司 | A kind of half hidden elevating rudder rocking arm |
| CN106184718B (en) * | 2015-04-29 | 2018-10-12 | 陕西飞机工业（集团）有限公司 | A kind of airplane synthetic manipulation device |
| CN105460225B (en) * | 2015-11-26 | 2017-12-12 | 庆安集团有限公司 | A kind of Fault Isolation mechanism for elevator |
| CN108082448B (en) * | 2017-11-03 | 2022-10-28 | 中航通飞研究院有限公司 | Nonlinear compensation device of double-cavity hydraulic booster |
| CN109521689B (en) * | 2018-03-16 | 2022-03-15 | 陕西飞机工业（集团）有限公司 | Design method of airplane double-redundancy quick-pressure adjustment type control surface angle control system |
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| CN109436302A (en) * | 2018-10-12 | 2019-03-08 | 陕西飞机工业（集团）有限公司 | A kind of transmission mechanism between cable wire and pull rod |
| CN111284727A (en) * | 2018-12-07 | 2020-06-16 | 中航贵州飞机有限责任公司 | Testing device for moment arm regulator of airplane control system |
| CN111017237B (en) * | 2019-12-19 | 2023-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Mechanical operation alarm device conformal with airfoil |
| CN111268098B (en) * | 2020-03-17 | 2022-03-11 | 景德镇陶瓷大学 | Aircraft hydraulic machinery load mechanism |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Shaanxi, Hanzhoung Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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