CN107757949A - One kind rotation becomes sensor test flight circuit - Google Patents
One kind rotation becomes sensor test flight circuit Download PDFInfo
- Publication number
- CN107757949A CN107757949A CN201710908527.8A CN201710908527A CN107757949A CN 107757949 A CN107757949 A CN 107757949A CN 201710908527 A CN201710908527 A CN 201710908527A CN 107757949 A CN107757949 A CN 107757949A
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- Prior art keywords
- signal
- rotation
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- becomes
- test
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention belongs to flying test bed engine testing system, and in particular to one kind rotation becomes sensor test flight circuit.Flying stand dynamoelectric accelerograph system needs two sets integrated control handles, and one is sleeved in the experimental cabin of empty station, another set of in the driving cabin of aircraft for aerial test run person manipulation by spreadsheet engine, for pilot guidance by spreadsheet engine.The rotation of the present invention becomes sensor test flight circuit, rotation to two groups of operating mechanisms becomes sensor signal and switches over control, currently valid rotation is become into sensor signal to send to engine controller, the test circuit includes structure identical electronic switch U1, U2, the manipulation signal of test run person and the manipulation signal of pilot are logical interlocks, when being all the way wherein useful signal, corresponding electronic switch conducting.Securely and reliably, cost is low, and switching is easy and effective.
Description
Technical field
The invention belongs to flying test bed engine testing system, and in particular to one kind rotation becomes sensor test flight electricity
Road.
Background technology
Flying stand dynamoelectric accelerograph system needs two sets of integrated control handles, and one is sleeved in the experimental cabin of empty station, for aerial
Test run person is manipulated by spreadsheet engine, another set of in the driving cabin of aircraft, for pilot guidance by spreadsheet engine.Look for novelty and grind
The dynamoelectric accelerograph control system and emergency system of system can receive the instruction of pilot, test run person's control crank respectively, realize behaviour
Control conversion between vertical handle, and give the signal of rotation change sensor in the currently active control crank to engine controller.
The content of the invention
The technical problems to be solved by the invention are：A kind of switching circuit safe and reliable, cost is low is proposed, to effectively behaviour
Rotation becomes the signal gating transmission of sensor in vertical handle.
The rotation of the present invention becomes sensor test flight circuit, and the rotation to two groups of operating mechanisms becomes sensor signal and switched over
Control, currently valid rotation is become into sensor signal and sent to engine controller, the test circuit includes structure identical electricity
Sub switch U1, U2, wherein electronic switch U1 receive the manipulation signal from test run person, and electronic switch U2 is received from pilot's
Manipulation signal, and electronic switch U1, U2 output signal are sent to engine controller；The manipulation signal of the test run person and
The manipulation signal of pilot is logical interlock, when being all the way wherein useful signal, corresponding electronic switch conducting.
The control pin of the electronic switch U1 receives test run person and manipulates useful signal, receives the rotation that pin receives test run person
Become sensor signal, the rotation of test run person is become sensor signal and sent to engine controller by output pin.
The reception pin of the electronic switch U1 connects the signal cosine output that the rotation from test run person becomes sensor respectively
The signal cosine that winding height, rotation become sensor exports low winding, the sinusoidal output winding height of the signal of rotation change sensor, rotation change sensing
The sinusoidal output winding of the signal of device is low.
The control pin of the electronic switch U2 receives pilot guidance useful signal, receives the rotation that pin receives pilot
Become sensor signal, the rotation of pilot is become sensor signal and sent to engine controller by output pin.
The reception pin of the electronic switch U2 connects the signal cosine output that the rotation from pilot becomes sensor respectively
The signal cosine that winding height, rotation become sensor exports low winding, the sinusoidal output winding height of the signal of rotation change sensor, rotation change sensing
The sinusoidal output winding of the signal of device is low.
The priority of pilot guidance useful signal manipulates useful signal higher than test run person.
When it is low level that test run person, which manipulates useful signal output end, electronic switch U1 four switches are both turned on, by S1
Signal to S4 inputs delivers to D1 to D4 output ends respectively.
When pilot guidance useful signal output end is low level, electronic switch U2 four switches are both turned on, by S1
Signal to S4 inputs delivers to D1 to D4 output ends respectively.
The beneficial effects of the invention are as follows：Securely and reliably, cost is low, and switching is easy and effective.
Brief description of the drawings
Fig. 1 is the circuit theory diagrams of the present invention.
Embodiment
The present invention is described in further details below.Referring to Fig. 1, one kind rotation becomes sensor test flight circuit, it by
Electronic switch U1 and U2 are formed；Electronic switch U1 control pin IN1 to IN4 connections manipulate useful signal, electricity from test run person
Sub switch U1 also includes receiving pin S1 to S4, and S1 connections become the signal of sensor from the rotation installed in test run person's control crank
Cosine output winding is high, and the signal cosine that S2 connections become sensor from the rotation installed in test run person's control crank exports winding
Low, the sinusoidal output winding of signal that S3 connections become sensor from the rotation installed in test run person's control crank is high, and S4 connections come from
The sinusoidal output winding of signal that rotation installed in test run person's control crank becomes sensor is low, and electronic switch U1 also includes output pin
The rotation that engine controller is delivered in D1 to D4, D1 connection becomes the effective cosine output winding high RST of sensor manipulation, and D2 connections are sent
Rotation to engine controller becomes the effective cosine output winding low signal of sensor manipulation, and engine controller is delivered in D3 connections
The effectively sinusoidal output winding high RST of rotation change sensor manipulation, the rotation change sensor manipulation that engine controller is delivered in D4 connections have
The sinusoidal output winding low signal of effect.
Electronic switch U2 control pin IN1 to IN4 is all connected with the pilot guidance useful signal from controller, electronics
Switching U2 also includes receiving pin S1 to S4, and S1 connections become from the rotation installed in pilot guidance handle more than the signal of sensor
String output winding is high, and the signal cosine output winding that S2 connections become sensor from the rotation installed in pilot guidance handle is low,
The sinusoidal output winding of signal that S3 connections become sensor from the rotation installed in pilot guidance handle is high, and S4 connections carry out self installation
Low in the sinusoidal output winding of signal of the rotation change sensor of pilot guidance handle, electronic switch U2 also includes output pin D1 extremely
The rotation that engine controller is delivered in D4, D1 connection becomes the effective cosine output winding high RST of sensor manipulation, and hair is delivered in D2 connections
The rotation of motivation controller becomes sensor and manipulates effective cosine output winding low signal, and the rotation that engine controller is delivered in D3 connections becomes
Sensor manipulates effectively sinusoidal output winding high RST, and the rotation change sensor that engine controller is delivered in D4 connections manipulates effectively just
String exports winding low signal.
The operation principle of the present invention is that it is interlock logic that test run person, which manipulates useful signal and pilot guidance useful signal,.
When it is low level that test run person, which manipulates useful signal output end, electronic switch U1 four switches are both turned on, and S1 to S4 is inputted
The signal at end delivers to D1 to D4 output ends respectively.When pilot guidance useful signal output end is low level, electronic switch U2
Four switches be both turned on, S1 to S4 inputs signal is delivered into D1 to D4 output ends respectively.
One embodiment of the present of invention, described U1 and U2 can select DG201 electronic switches.
Claims (6)
1. one kind rotation becomes sensor test flight circuit, it is characterised in that：Rotation of the test circuit to two groups of operating mechanisms, which becomes, to be passed
Sensor signal switches over control, and currently valid rotation is become into sensor signal sends to engine controller, the test circuit
Including structure identical electronic switch U1, U2, wherein electronic switch U1 receives the manipulation signal from test run person, electronic switch U2
The manipulation signal from pilot is received, and electronic switch U1, U2 output signal are sent to engine controller；The examination
The manipulation signal of car person and the manipulation signal of pilot are logical interlocks, when being all the way wherein useful signal, corresponding electricity
Sub switch turns on.
2. rotation according to claim 1 becomes sensor test flight circuit, it is characterised in that：The control of the electronic switch U1
Tubulation pin receives test run person and manipulates useful signal, receives the rotation change sensor signal that pin receives test run person, and output pin will try
The rotation of car person becomes sensor signal and sent to engine controller.
3. rotation according to claim 2 becomes sensor test flight circuit, it is characterised in that：The electronic switch U1's connects
Closed tube pin connects the rotation from test run person and becomes the signal cosine output winding height of sensor, revolves the signal cosine for becoming sensor respectively
It is low to export the sinusoidal output winding of signal that the sinusoidal output winding of signal that winding is low, rotation becomes sensor is high, rotation becomes sensor.
4. rotation according to claim 1 becomes sensor test flight circuit, it is characterised in that：The control of the electronic switch U2
Tubulation pin receives pilot guidance useful signal, receives the rotation change sensor signal that pin receives pilot, and output pin will fly
The rotation of office staff becomes sensor signal and sent to engine controller.
5. rotation according to claim 4 becomes sensor test flight circuit, it is characterised in that：The electronic switch U2's connects
Closed tube pin connects the rotation from pilot and becomes the signal cosine output winding height of sensor, revolves the signal cosine for becoming sensor respectively
It is low to export the sinusoidal output winding of signal that the sinusoidal output winding of signal that winding is low, rotation becomes sensor is high, rotation becomes sensor.
6. the rotation according to any one of claim 1-5 becomes sensor test flight circuit, it is characterised in that：Pilot grasps
The priority of vertical useful signal manipulates useful signal higher than test run person.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710908527.8A CN107757949A (en) | 2017-09-29 | 2017-09-29 | One kind rotation becomes sensor test flight circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710908527.8A CN107757949A (en) | 2017-09-29 | 2017-09-29 | One kind rotation becomes sensor test flight circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107757949A true CN107757949A (en) | 2018-03-06 |
Family
ID=61267856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710908527.8A Pending CN107757949A (en) | 2017-09-29 | 2017-09-29 | One kind rotation becomes sensor test flight circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107757949A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201580259U (en) * | 2009-12-18 | 2010-09-15 | 中国第一汽车集团公司 | Controller for switching accelerator pedal and remote accelerator |
| CN201587331U (en) * | 2009-12-14 | 2010-09-22 | 上海三一科技有限公司 | Energy-saving engine control device for crane |
| WO2013183063A2 (en) * | 2012-06-01 | 2013-12-12 | Mahindra & Mahindra Limited | Power-economy mode control system for a vehicle |
| CN204283629U (en) * | 2014-11-03 | 2015-04-22 | 中国飞行试验研究院 | Flying stand dynamoelectric accelerograph system |
| CN106452397A (en) * | 2016-09-29 | 2017-02-22 | 上海福赛特机器人有限公司 | Redundancy selection switch used in robot safety circuit, controller and relay |
-
2017
- 2017-09-29 CN CN201710908527.8A patent/CN107757949A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201587331U (en) * | 2009-12-14 | 2010-09-22 | 上海三一科技有限公司 | Energy-saving engine control device for crane |
| CN201580259U (en) * | 2009-12-18 | 2010-09-15 | 中国第一汽车集团公司 | Controller for switching accelerator pedal and remote accelerator |
| WO2013183063A2 (en) * | 2012-06-01 | 2013-12-12 | Mahindra & Mahindra Limited | Power-economy mode control system for a vehicle |
| CN204283629U (en) * | 2014-11-03 | 2015-04-22 | 中国飞行试验研究院 | Flying stand dynamoelectric accelerograph system |
| CN106452397A (en) * | 2016-09-29 | 2017-02-22 | 上海福赛特机器人有限公司 | Redundancy selection switch used in robot safety circuit, controller and relay |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180306 |
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| RJ01 | Rejection of invention patent application after publication |