CN201592781U - Aircraft seat ejection control device - Google Patents
Aircraft seat ejection control device Download PDFInfo
- Publication number
- CN201592781U CN201592781U CN2009202176224U CN200920217622U CN201592781U CN 201592781 U CN201592781 U CN 201592781U CN 2009202176224 U CN2009202176224 U CN 2009202176224U CN 200920217622 U CN200920217622 U CN 200920217622U CN 201592781 U CN201592781 U CN 201592781U
- Authority
- CN
- China
- Prior art keywords
- control circuit
- relay
- backup
- ejection
- main relay
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)
Abstract
The utility model relates to improvement for an aircraft seat ejection control device, which belongs to the electrical control technology. The aircraft seat ejection control device comprises a computer ejection sequence control circuit and a main relay; a backup relay same with the main relay is parallelly connected onto the main relay; a fixed time control circuit is in series connection with the backup relay; and an input end of the fixed time control circuit is connected with an output end of a seat ejection pulling device. The aircraft seat ejection control device employs a logic circuit for fixing delay time as a backup circuit of the computer sequence control circuit; and when the computer ejection sequence control circuit is not in work, the backup logic fixed time control circuit can still complete starting seat ejection sequences by delaying transmitting control signals in fixed time according to the maximum output time of the computer ejection sequence control circuit and driving the backup relay.
Description
Technical field
The utility model belongs to Electrical Control Technology, relates to the improvement of aircraft seat being launched control setup.
Background technology
Present aircraft seat ejection sequence control unit is made up of a computing machine ejection sequence control circuit and a relay that is controlled by the computer program control circuit.When the computer program control circuit receives after seat fire pulls signal, (V-t) sends control signal according to speed time curve, drives relay, connects seat fire and starts power supply Vout, starts the seat fire program.Its shortcoming is: a link (hardware and software) fault in the computer program control circuit, will there be control signal output, and can't drive relay work, can not start the seat fire program.
Summary of the invention
The purpose of this utility model is: a kind of aircraft seat that proposes the fixed delay time that a kind of safety is good, probability failure is low, reliability is high launches control setup.
The technical solution of the utility model is: aircraft seat launches control setup and comprises a computing machine ejection sequence control circuit and main relay, the mouth of computing machine ejection sequence control circuit is connected with the input end of main relay, the power input of main relay starts power output end with seat fire and is connected, and the input end of computing machine ejection sequence control circuit is connected with the mouth that seat fire pulls device; Backup relay identical in parallel on main relay with main relay, the set time control circuit is connected with the backup relay, and the input end of set time control circuit is connected with the mouth that seat fire pulls device.
The set time of set time control circuit is identical with the peak output time of computing machine ejection sequence control circuit.
Advantage that the utlity model has and beneficial effect, the utility model comprises the fallback circuit of the decision circuit of the fixed delay time that a kind of safety is good, probability failure is low, reliability is high as the computer program control circuit, when computing machine ejection sequence control circuit fault is not worked, backup logic set time control circuit postpones to send control signal according to set time peak output time of computing machine ejection sequence control circuit, drive the backup relay, still can finish startup seat fire program.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
The specific embodiment
Below the present invention is described in further details.With reference to figure 1, aircraft seat launches control setup, comprise a computing machine ejection sequence control circuit 1 and main relay 2, the control signal output ends of computing machine ejection sequence control circuit 1 is connected with the signal input end of main relay 2, the power input of main relay 2 starts power supply Vout with seat fire and is connected, and the actuation signal input end of computing machine ejection sequence control circuit 1 pulls signal output part with seat fire and is connected; When computing machine ejection sequence control circuit 1 fault was not worked, backup logic set time control circuit 4 postponed to send control signal according to the set time, drove backup relay 3 and started the seat fire program.
After aircraft seat pulls the device startup,
(1) under the normal circumstances, aircraft seat launches control and sends control signal by computing machine ejection sequence control circuit 1 according to speed time curve (V-t), drives main relay 2 and starts the seat fire program;
When (2) computing machine ejection sequence control circuit 1 fault was not worked, backup logic set time control circuit 4 postponed maximum time according to speed time curve (V-t) and sends control signal, drives backup relay 3 and starts the seat fire programs.
Claims (1)
1. an aircraft seat launches control setup, comprise a computing machine ejection sequence control circuit [1] and main relay [2], the mouth of computing machine ejection sequence control circuit [1] is connected with the input end of main relay [2], the power input of main relay [2] starts power output end with seat fire and is connected, and the input end of computing machine ejection sequence control circuit [1] is connected with the mouth that seat fire pulls device; It is characterized in that: go up backup relay [3] identical in parallel with main relay [2] at main relay [2], set time control circuit [4] is connected with backup relay [3], and the input end of set time control circuit [4] is connected with the mouth that seat fire pulls device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202176224U CN201592781U (en) | 2009-09-29 | 2009-09-29 | Aircraft seat ejection control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202176224U CN201592781U (en) | 2009-09-29 | 2009-09-29 | Aircraft seat ejection control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201592781U true CN201592781U (en) | 2010-09-29 |
Family
ID=42774845
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202176224U Expired - Fee Related CN201592781U (en) | 2009-09-29 | 2009-09-29 | Aircraft seat ejection control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201592781U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620762A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Ejection life-saving control method |
| CN106005438A (en) * | 2016-07-27 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Pilot ejection escape control system and aircraft with same |
| CN106005439A (en) * | 2016-07-27 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Pilot ejection escape control system of parallel double-seat aircraft and aircraft |
-
2009
- 2009-09-29 CN CN2009202176224U patent/CN201592781U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620762A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Ejection life-saving control method |
| CN106005438A (en) * | 2016-07-27 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Pilot ejection escape control system and aircraft with same |
| CN106005439A (en) * | 2016-07-27 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Pilot ejection escape control system of parallel double-seat aircraft and aircraft |
| CN106005439B (en) * | 2016-07-27 | 2019-01-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of two-seater aircraft pilot ejection lifesaving control system arranged side by side and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106951336B (en) | MCU (microprogrammed control Unit) resetting method, device and system | |
| CN201592781U (en) | Aircraft seat ejection control device | |
| CN104778108A (en) | Device and method for abnormal power failure circulating testing of server system | |
| CN104268044A (en) | Method and device for performing loop test on normal startup and shutdown of server system | |
| CN207538973U (en) | A kind of soft opening device of large-scale wind electricity set yaw | |
| CN105159436A (en) | Industrial personal computer power on-off control apparatus and control method | |
| CN103259845B (en) | Improving one's methods of the data backup task of interruption Network Based | |
| CN204438934U (en) | A kind of electronic detonator initiating remote control network | |
| CN104579063A (en) | Delay control circuit for generator set and control method | |
| CN104002857A (en) | Electro-mechanical coupling power-assisted steering system for plug-in type hybrid power bus and control method thereof | |
| CN203416199U (en) | Centrifuge emergency brake circuit structure | |
| CN104457462A (en) | Control system for initiation networks of electronic detonators | |
| CN102221867A (en) | Circuit for realizing computer soft off and control method thereof | |
| CN104648147A (en) | Automotive button starting system and method | |
| CN201041994Y (en) | Soft starter for fire control water pump low-speed tour check | |
| CN202334547U (en) | Dual-network access physical isolation online switch device based on USB bus | |
| CN113778210A (en) | MCU-based ACPI management method, system and equipment | |
| CN102003378A (en) | Novel start control circuit for double-winding compressor | |
| CN203114489U (en) | Bulldozer starting safety protection device | |
| CN107905287B (en) | Digger engine start-stop control system and control method | |
| CN215297506U (en) | Be used for automatic detection device of helicopter electrical system | |
| CN204705873U (en) | Without riveted joint time can automatic time delay shut down vehicle frame riveting machine | |
| CN203005317U (en) | Disconnection delay system for vehicle controller | |
| CN106685309B (en) | Heavy-load horizontal loading drive control system and control method | |
| CN210577735U (en) | Automatic drive controller time delay outage system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100929 Termination date: 20160929 |