CN103010452A - Wing folding control instrument - Google Patents
Wing folding control instrument Download PDFInfo
- Publication number
- CN103010452A CN103010452A CN2012105282787A CN201210528278A CN103010452A CN 103010452 A CN103010452 A CN 103010452A CN 2012105282787 A CN2012105282787 A CN 2012105282787A CN 201210528278 A CN201210528278 A CN 201210528278A CN 103010452 A CN103010452 A CN 103010452A
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- CN
- China
- Prior art keywords
- wing
- directional control
- rotor switch
- power supply
- control valve
- 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.)
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Abstract
The invention belongs to the technology of aircraft wing folding, and relates to a wing folding control instrument. The wing folding control instrument comprises a 24 V direct-current stabilized-voltage power supply, a three-position four-way electromagnetic directional valve, a two-position four-way electromagnetic directional valve and a stop valve, wherein the stop valve is connected with the 24 V direct-current stabilized-voltage power supply at the signal input end and connected with the two-position four-way electromagnetic directional valve through a control switch; and the two-position four-way electromagnetic directional valve is used for controlling a double-action actuating cylinder of an aircraft wing through the three-position four-way electromagnetic directional valve. The wing folding control instrument can be used for effectively controlling the motion state of the double-action actuating cylinder in the wing, is flexible and convenient to mount and simple to operate, and can reflect the wing folding frequency so as to solve the problem of wing folding control.
Description
Technical field
The invention belongs to the aircraft wingfold technology, relate to a kind of wing-folding controller.
Background technology
In the wing-folding breadboard, control double acting pressurized strut in the wing, controlled with this action to wing-folding/flatten/stop.
Because the wing-folding technology is domestic not yet launches concrete experimental investigation, and the foreign technology blockade is serious, is difficult to obtain detail file.
Summary of the invention
The objective of the invention is: provide double acting pressurized strut a kind of and in the wing to be connected, can control flexibly the actions such as fold/flattening/stop of wing, the controllability of Effective Raise test and the wing-folding controller of reliability.
Technical scheme of the present invention is: a kind of wing-folding controller, it comprises 24V DC regulated power supply, 3-position 4-way solenoid directional control valve, two-position four way change valve, shutoff valve, wherein, shutoff valve connects the 24V DC regulated power supply of signal input part, and shutoff valve connects the two-position four-way solenoid directional control valve through master cock, and the two-position four-way solenoid directional control valve is controlled the double acting pressurized strut of the aircraft wing again through three position four-way directional control valve.
Also comprise manual/auto rotor switch, fold/stop/launching rotor switch, counting machine and two solid-state relay, wherein, the manual/auto rotor switch that links to each other with the 24V DC regulated power supply through fold/stop/launching rotor switch after again by linking to each other with three position four-way directional control valve behind the solid-state relay of two parallel connections, described counting machine with fold/stop/launching rotor switch and link to each other.
Manual/auto rotor switch and fold/stop/launching also being connected with slug relay between the rotor switch output.
The signal input part of 24V DC regulated power supply also is provided with insurance.
Technique effect of the present invention is: wing-folding controller of the present invention can be controlled the double-acting pressurized strut state of kinematic motion in the wing effectively, and convenient and flexible installation is simple to operate, and can reflect that the wing-folding number of times is to solve the problem of controlling machine wingfold.
This control instrument has the following advantages:
1. undertaken folded wing pressurized strut running of hydraulic power oil direction and then realization are folded and the flattening operation by the 3-position 4-way solenoid directional control valve;
2. utilize the wing-folding control instrument to come controlling machine wingfold/flattening action, simple to operate, greatly reduce empirical risk;
3. whole loading system does not need too many manpower, only needs 2-3 people can finish the wing-folding breadboard, has improved test efficiency; Convenient and flexible installation and simple to operate.
Description of drawings
Fig. 1 is the principle schematic of wing-folding controller of the present invention;
Fig. 2 is wing-folding controller structural representation of the present invention,
Wherein, 1-24V DC regulated power supply, 2-solid-state relay, 3-3-position 4-way solenoid directional control valve, 4-two-position four-way solenoid directional control valve, 5-shutoff valve, 6-counting machine, 7-slug relay, 8-insurance, 9-indicator lamp, 10-shutoff valve switch, 11-source switch, 12-rotor switch.
The specific embodiment
Many the present invention are described further below in conjunction with accompanying drawing:
See also Fig. 1, wing-folding controller of the present invention comprises 24V DC regulated power supply, 3-position 4-way solenoid directional control valve, two-position four way change valve, shutoff valve, manual/auto rotor switch, fold/stops/launching rotor switch, counting machine and two solid-state relay.Wherein, the signal input part of 24V DC regulated power supply also is provided with insurance.Shutoff valve connects the 24V DC regulated power supply of signal input part, and shutoff valve connects the two-position four-way solenoid directional control valve through master cock, and the two-position four-way solenoid directional control valve is controlled the double acting pressurized strut of aircraft wing again through three position four-way directional control valve.The manual/auto rotor switch that links to each other with the 24V DC regulated power supply through fold/stop/launching rotor switch after again by linking to each other with three position four-way directional control valve behind the solid-state relay of two parallel connections, described counting machine with fold/stop/launching rotor switch and link to each other.In addition, manual/auto rotor switch and fold/stop/launching also being connected with slug relay between the rotor switch output.
The wing-folding controller adopts the power supply of 24V DC regulated power supply, is serially connected with simultaneously indicator lamp and power safety.The target of this wing-folding controller is hydraulic power, and wherein the shutoff valve in the oil circuit control circuit is used for controlling the incoming signal of two-position four-way solenoid directional control valve, and is connected with the 3-position 4-way solenoid directional control valve, carries out the switch control of hydraulic circuit.This controller has manually and automatic two kinds of master modes, under manual mode, its rotor switch is connected with the 3-position 4-way solenoid directional control valve by solid-state relay, control the circuit commutation in the 3-position 4-way solenoid directional control valve, drive double acting pressurized strut receiving/releasing, thereby realize folding/the flattening action of aircraft wing, folding/flattening of aircraft wing moved once, and then rolling counters forward once.Under automatic mode, manual/auto rotor switch is connected with solid-state relay by slug relay, and the remaining circuit part is the same with manual mode.
See also Fig. 2, wherein the 3-position 4-way solenoid directional control valve is connected in the wing double acting pressurized strut, comes controlling machine wingfold/flatten/stop action; Two-position four-way solenoid directional control valve and shutoff valve come oil circuit control conducting/halted state; Indicator lamp is used to refer to current state position (comprising: power supply, shutoff valve, automatic/hand, the state such as fold/flatten/stop); Insurance comes protective circuit safety; Switch (comprising shutoff valve switch and source switch) is used for control shutoff valve and power supply disconnection/conducting state; Solid-state relay is used for wing-folding/flattening/danger signal, and slug relay is used under automatic mode the output of signal being delayed time; Counting machine is used for the counting of wing-folding number of times; Rotor switch is used for controlling the function of 3-position 4-way solenoid directional control valve and manual/auto conversion etc.
Wing-folding controller of the present invention is connected with double acting pressurized strut in the wing, and what it can control wing flexibly fold/flattens/stop action, improves accuracy and the reliability of control.Open the switch of 24V power supply and shutoff valve, the two-position four way change valve conducting, thus make the oil circuit conducting of the double acting pressurized strut in the aircraft wing; Simultaneously, by fold/stopping/flattening the signal input of rotor switch control 3-position 4-way solenoid directional control valve, make again in the aircraft wing double acting pressurized strut carry out the receiving/releasing action, thereby the aircraft wing is folded/flatten action.
Claims (4)
1. wing-folding controller, it is characterized in that, comprise 24V DC regulated power supply, 3-position 4-way solenoid directional control valve, two-position four way change valve, shutoff valve, wherein, shutoff valve connects the 24V DC regulated power supply of signal input part, and shutoff valve connects the two-position four-way solenoid directional control valve through master cock, and the two-position four-way solenoid directional control valve is controlled the double acting pressurized strut of aircraft wing again through three position four-way directional control valve.
2. wing-folding controller according to claim 1, it is characterized in that, also comprise manual/auto rotor switch, fold/stop/launching rotor switch, counting machine and two solid-state relay, wherein, the manual/auto rotor switch that links to each other with the 24V DC regulated power supply through fold/stop/launching rotor switch after again by linking to each other with three position four-way directional control valve behind the solid-state relay of two parallel connections, described counting machine with fold/stop/launching rotor switch and link to each other.
3. wing-folding controller according to claim 2 is characterized in that, manual/auto rotor switch and fold/stop/launching also being connected with slug relay between the rotor switch output.
4. wing-folding controller according to claim 3 is characterized in that, the signal input part of 24V DC regulated power supply also is provided with insurance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210528278.7A CN103010452B (en) | 2012-12-10 | 2012-12-10 | Wing folding control instrument |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210528278.7A CN103010452B (en) | 2012-12-10 | 2012-12-10 | Wing folding control instrument |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103010452A true CN103010452A (en) | 2013-04-03 |
| CN103010452B CN103010452B (en) | 2015-05-27 |
Family
ID=47959683
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210528278.7A Active CN103010452B (en) | 2012-12-10 | 2012-12-10 | Wing folding control instrument |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103010452B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103612743A (en) * | 2013-12-04 | 2014-03-05 | 中国飞机强度研究所 | Novel wing folding controller and control method thereof |
| CN110546476A (en) * | 2018-04-27 | 2019-12-06 | 深圳市大疆创新科技有限公司 | Folding equipment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5452643A (en) * | 1992-01-30 | 1995-09-26 | The Boeing Company | Hydraulic power drive unit |
| US20020074459A1 (en) * | 2000-04-17 | 2002-06-20 | Wolfgang Gleine | Pressure control system for a pressure-expandable displacement element |
| US7066428B1 (en) * | 2004-03-08 | 2006-06-27 | Haggard Roy A | Unfolding wing for air-launched, low speed air vehicles |
| WO2011011089A1 (en) * | 2009-07-22 | 2011-01-27 | Aerovironment Inc. | Reconfigurable aircraft |
| CN102556336A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Wing fast unfolding device for folding-wing unmanned plane |
-
2012
- 2012-12-10 CN CN201210528278.7A patent/CN103010452B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5452643A (en) * | 1992-01-30 | 1995-09-26 | The Boeing Company | Hydraulic power drive unit |
| US20020074459A1 (en) * | 2000-04-17 | 2002-06-20 | Wolfgang Gleine | Pressure control system for a pressure-expandable displacement element |
| US7066428B1 (en) * | 2004-03-08 | 2006-06-27 | Haggard Roy A | Unfolding wing for air-launched, low speed air vehicles |
| WO2011011089A1 (en) * | 2009-07-22 | 2011-01-27 | Aerovironment Inc. | Reconfigurable aircraft |
| CN102556336A (en) * | 2011-12-30 | 2012-07-11 | 北京理工大学 | Wing fast unfolding device for folding-wing unmanned plane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103612743A (en) * | 2013-12-04 | 2014-03-05 | 中国飞机强度研究所 | Novel wing folding controller and control method thereof |
| CN110546476A (en) * | 2018-04-27 | 2019-12-06 | 深圳市大疆创新科技有限公司 | Folding equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103010452B (en) | 2015-05-27 |
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| C14 | Grant of patent or utility model | ||
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