CN211543878U - Undercarriage of aircraft dual redundancy receive and releases controlling device - Google Patents
Undercarriage of aircraft dual redundancy receive and releases controlling device Download PDFInfo
- Publication number
- CN211543878U CN211543878U CN201922388228.3U CN201922388228U CN211543878U CN 211543878 U CN211543878 U CN 211543878U CN 201922388228 U CN201922388228 U CN 201922388228U CN 211543878 U CN211543878 U CN 211543878U
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- override
- casing
- retraction
- command
- 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.)
- Active
Links
Images
Landscapes
- Mechanical Control Devices (AREA)
Abstract
The utility model provides an undercarriage of aircraft dual redundancy receive and releases controlling device, have undercarriage normal receive and releases the operation function and the two kinds of functions of override putting down, the device includes the casing, normally receive and releases the handle, micro-gap switch and override put the instruction switch, normally receive and release the handle and override and put the instruction switch and install outside the casing, normally receive and release the handle and pass through the guide way on the casing and be connected with the micro-gap switch of casing inside, micro-gap switch is connected with the undercarriage controller outside the casing, override is put the instruction switch and is exported the undercarriage controller outside the casing with override through the wire.
Description
Technical Field
The application belongs to the field of control over retraction and extension of an aviation undercarriage, and particularly relates to a design of an undercarriage retraction and extension control device with dual redundancy of an airplane.
Background
The landing gear is an important component of the airplane, and the retraction function of the landing gear plays a key role in the takeoff and landing of the airplane. Particularly, when the landing gear is in landing, if the landing gear cannot be put down, the airplane can be forced to land seriously, the airplane is damaged, and personnel are injured and killed.
The landing gear retraction control system for an aircraft typically includes a normal retraction system and an emergency retraction system. In the normal retraction system, a driver controls a normal retraction handle to send an undercarriage normal retraction/extension instruction, the instruction is collected by a controller, information such as airplane wheel load signals, undercarriage and cabin door position states and the like needs to be combined, and after logic calculation, a retraction instruction is sent to an actuator. When the hydraulic energy source of the aircraft fails or a logic control device in the controller fails, a driver needs to perform emergency release operation on the undercarriage to ensure that the undercarriage is smoothly put down and safely landed. However, the emergency release system generally adopts a set of independent emergency energy for pressure supply, and is generally arranged in a cargo hold or an equipment hold of an airplane due to space limitation of the airplane, so that the operation of a driver is inconvenient.
In the aircraft landing gear retraction control system, if an electric control part in the normal retraction system is in error in logic calculation of a controller or under the condition of incomplete information of the aircraft and the like, the aircraft cannot correctly send a landing gear retraction instruction. Because the undercarriage can not be put down to seriously influence the landing of the airplane, the reliability of the system can be effectively improved by increasing the redundancy of the undercarriage retraction control device, and great help is provided for the safety of the airplane.
Disclosure of Invention
The utility model provides an undercarriage of dual redundancy receive and releases controlling device, through setting up normal receive and release handle and override command switch, increase undercarriage receive and release controlling device redundancy, increase system reliability.
The utility model provides an undercarriage of aircraft dual redundancy receive and releases controlling device, have the undercarriage and normally receive and releases the operating function and two kinds of functions are put down in the override, a serial communication port, the device includes the casing, normally receive and release the handle, micro-gap switch and override put command switch, normally receive and release the handle and override and put command switch and install outside the casing, normally receive and release the handle and pass through the guide way on the casing and be connected with the micro-gap switch of casing inside, micro-gap switch is connected with the undercarriage controller outside the casing, override is put command switch and is exported the override through the wire and put the undercarriage controller outside the casing.
When a driver sends a normal undercarriage retraction command, the normal retraction handle is operated to drive the microswitch connected with the normal retraction handle to send a command, the command is collected by the controller, the command and other state information of the airplane are logically resolved, and then a corresponding command is sent to the actuating mechanism.
When the normal retraction function fails, for example, under the conditions of controller logic calculation error or other incomplete information of the airplane and the like, a normal retraction command cannot be sent, the override command switch can be toggled to send an undercarriage override command, and after the command is collected by the controller, the undercarriage override command is directly sent to the actuating mechanism without logic calculation.
The utility model has the advantages that: by designing the undercarriage retracting and releasing control device with dual redundancy of the airplane, the undercarriage retracting and releasing control device has two functions of normal retracting and releasing of the undercarriage and override releasing of the undercarriage, a normal retracting and releasing instruction of the undercarriage can be sent, and when the normal retracting and releasing function fails, the override releasing switch can be shifted to achieve the override releasing function of the undercarriage. The utility model discloses simple structure, the function mutual independence has improved system reliability, at military, civilian field, can use in landing gear receive and releases control system.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic diagram of the principle of a dual redundant landing gear retraction control device for an aircraft.
Fig. 2 is a schematic layout of a housing panel.
The numbering in the figures illustrates: 1 normal receive and release handle, 2 override command switch, 3 casing, 4 micro-gap switch, 5 guide way, 6 panels.
Detailed Description
Referring to the attached drawings, the airplane dual-redundancy landing gear retraction control device comprises a shell 3, a normal retraction handle 1, a microswitch 4 and an override command switch 2. Normally receive and release handle 1 and override and put instruction switch 2 and all set up on the panel 6 of casing 3, on the panel 6 of casing, be equipped with the guide way 6 that normally receive and release handle 1, micro-gap switch 4 arranges in casing 3, and normally receive and release handle 1 is located the end in the casing and is related with micro-gap switch 4, and micro-gap switch 4 passes through the wire and is connected with the outer controller of casing, and override and put instruction switch 2 and be connected with the outer controller of casing through another independent wire. When the undercarriage is normally retracted and extended, the normal retraction handle 1 is operated to drive the microswitch 4 connected with the normal retraction handle to send an undercarriage retraction and extension instruction, the undercarriage retraction and extension instruction is collected by the controller and logically resolved with other state information of the airplane, and then a corresponding instruction is sent to an actuator of the undercarriage.
When the normal retraction function fails, for example, under the conditions of logic calculation error of the controller or incomplete information of other airplanes and the like, the controller fails to send a normal retraction command, a driver can toggle the override command switch 2 to send an undercarriage override command, the command is transmitted to the controller through a lead, and the override command is directly sent to an actuator of the undercarriage without logic calculation.
The normal retraction operation and the landing gear override operation are independent and do not interfere with each other.
Claims (4)
1. The utility model provides an undercarriage of aircraft dual redundancy receive and releases controlling device, have the undercarriage and normally receive and releases the operating function and two kinds of functions are put down in the override, a serial communication port, the device includes the casing, normally receive and release the handle, micro-gap switch and override put command switch, normally receive and release the handle and override and put command switch and install outside the casing, normally receive and release the handle and pass through the guide way on the casing and be connected with the micro-gap switch of casing inside, micro-gap switch is connected with the undercarriage controller outside the casing, override is put command switch and is exported the override through the wire and put the undercarriage controller outside the casing.
2. The dual-redundancy undercarriage control device of claim 1, wherein when the undercarriage is normally retracted and extended, the normal retraction handle is operated to drive the microswitch connected with the normal retraction handle, and after the microswitch collects a retraction command, the microswitch transmits the normal retraction command to the undercarriage controller through a wire.
3. An aircraft dual redundancy landing gear retraction and extension operating device according to claim 1, wherein when the aircraft is landing and if the normal landing gear function fails, the override command switch can be toggled to issue a landing gear override command, which is transmitted to the controller via a wire, and the controller will issue the landing gear override command directly to the actuator.
4. An aircraft dual-redundancy landing gear retraction and extension operating device according to claim 1, wherein the normal retraction operation and the landing gear override operation are independent of each other and do not interfere with each other.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201922388228.3U CN211543878U (en) | 2019-12-26 | 2019-12-26 | Undercarriage of aircraft dual redundancy receive and releases controlling device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201922388228.3U CN211543878U (en) | 2019-12-26 | 2019-12-26 | Undercarriage of aircraft dual redundancy receive and releases controlling device |
Publications (1)
Publication Number | Publication Date |
---|---|
CN211543878U true CN211543878U (en) | 2020-09-22 |
Family
ID=72510031
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201922388228.3U Active CN211543878U (en) | 2019-12-26 | 2019-12-26 | Undercarriage of aircraft dual redundancy receive and releases controlling device |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN211543878U (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112407257A (en) * | 2020-12-04 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Dual-redundancy electric retraction and extension method and device of undercarriage |
CN113060276A (en) * | 2021-03-19 | 2021-07-02 | 昆山航理机载设备股份有限公司 | Undercarriage handle mechanism for aircraft |
-
2019
- 2019-12-26 CN CN201922388228.3U patent/CN211543878U/en active Active
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112407257A (en) * | 2020-12-04 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Dual-redundancy electric retraction and extension method and device of undercarriage |
CN112407257B (en) * | 2020-12-04 | 2021-06-22 | 北京北航天宇长鹰无人机科技有限公司 | Dual-redundancy electric retraction and extension method and device of undercarriage |
CN113060276A (en) * | 2021-03-19 | 2021-07-02 | 昆山航理机载设备股份有限公司 | Undercarriage handle mechanism for aircraft |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4528831B2 (en) | Aircraft landing leg operating system and aircraft equipped with such a system | |
CN211543878U (en) | Undercarriage of aircraft dual redundancy receive and releases controlling device | |
CA2727592C (en) | Flight control system for an aircraft | |
EP3056396B1 (en) | Multi-thread emergency park brake system | |
CN106672217A (en) | Architecture of landing gear control system of aircraft | |
US8807480B2 (en) | Method of extending aircraft undercarriages in emergency mode | |
CN204527619U (en) | A kind of multifunctional unit shackle lock | |
CN201606331U (en) | Landing gear uplock for airplanes | |
CN205010480U (en) | Unmanned aerial vehicle undercarriage composite control system | |
CN103640692A (en) | Handle-based autonomous control method of training plane undercarriage system | |
EP3445649A1 (en) | Aircraft landing gear assembly with electromechanical actuation and aircraft provided with such assembly | |
CN203681866U (en) | Side lock mechanism of unmanned aircraft landing gear | |
CN103158866A (en) | A method of managing systems associated with the landing gear of an aircraft | |
CN110667826B (en) | High-lift distributed telex control system | |
CN111142369A (en) | Fly-by-wire flight control system capable of meeting airworthiness requirement | |
US20240253809A1 (en) | Systems for harvesting rotational wheel energy for landing gear retraction | |
CN111268150B (en) | Duct type ram air turbine emergency energy system | |
CN109850134B (en) | Aircraft landing gear system | |
CN204452925U (en) | A kind of integrated form undercarriage control priority acccess control switch | |
CN108058815B (en) | Simple and flexible control mechanism capable of realizing retraction of undercarriage | |
CN217260648U (en) | Unmanned aerial vehicle undercarriage dual-redundancy folding and unfolding control system and unmanned aerial vehicle | |
CN104369860A (en) | Integrated type retracting-dropping priority control switch of landing gear | |
CN118182824B (en) | Emergency hydraulic system for landing gear of airplane and airplane | |
CN109319096A (en) | It can ensure the aircraft brake-by-wire system and control method of take-off line brake | |
CN216353892U (en) | Fireproof control panel for airplane |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
GR01 | Patent grant | ||
GR01 | Patent grant |