CN109292111A - A kind of teleputer air refuelling state control rate detection method - Google Patents
A kind of teleputer air refuelling state control rate detection method Download PDFInfo
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- CN109292111A CN109292111A CN201810827315.1A CN201810827315A CN109292111A CN 109292111 A CN109292111 A CN 109292111A CN 201810827315 A CN201810827315 A CN 201810827315A CN 109292111 A CN109292111 A CN 109292111A
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- teleputer
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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
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The present invention relates to a kind of teleputer air refuelling state control rate detection methods, it is offeed telex computer operation power supply and air refuelling state verification environment using teleputer test platform, the corresponding analog voltage of each angular speed parameter is given using angular velocity signal setting potentiometer, inertial navigation output is simulated by rotary transformer module, aspect angle signal is provided, finally successively measure each angular speed, tailplane servo-control signal output voltage values under attitude angle, realize that the control rate under air refuelling state is verified by the corresponding relationship of this voltage value and tailplane deflection angle.The present invention is offeed telex computer air refuelling state verification environment by teleputer test platform, reduce the demand to test resource, it is measured and is verified using servo-control signal voltage value and the corresponding relationship of horizontal displacement angular deflection simultaneously, precision is high, being capable of the true air refuelling environment of approximate simulation.
Description
Technical field
The present invention relates to teleputer detection field, specifically a kind of teleputer air refuelling state control
Rate detection method.
Background technique
Aircraft Air oiling technology effectively increases voyage on the basis of reducing aircraft takeoffs and landings number, refuels for effectively control
State is got off the plane posture, and fly-by-wire control rate is also required to carry out adaptation.Currently, teleputer adds in the air
The detection of oil condition control rate is realized by the method for " testing on machine ".
" testing on machine " method is: aviation power supply, liquid feeding pressure can work normally flight control system.Connect aircraft
Air refuelling state drives the angular-rate sensor in fly-by-wire to give different angular speed and joins using angular speed turntable
Numerical value, by measuring the deflection angle of tailplane, verifying angular speed controls the additional gain of tailplane.By inertial navigation rigidity
It is mounted on 3-dimensional freedom platform, gives carriage angle using 3-dimensional freedom platform, by the deflection angle for measuring tailplane
Degree, ratio control planning between the displacement of verifying pitch lever and pitch angle.This method testing requirement condition is more, must mostly specially when operation
Industry, multi agent cooperation are completed, and consumption is high, at low cost.And angle measurement error is big, measuring accuracy is not high.
Summary of the invention
In order to solve the above technical problem, the present invention provides a kind of teleputer air refuelling state control rate detection sides
Method.
The technical problems to be solved by the invention are realized using following technical scheme:
A kind of teleputer air refuelling state control rate detection method, comprising steps of
A) power supply is provided for teleputer work using teleputer test platform, signal input interface is provided, it is defeated
Signal measurement interface out realizes the test environment of air refuelling state；
B) " air refuelling state ", " being stretched out by beam hanger " status switch adjunct circuit are connected, control teleputer enters
Air refuelling state；
C) fixed angular speed analog signal is given using angular speed simulation potentiometer, measures corresponding tailplane servo deflection control
Voltage processed；
D) additional rotary transformer is utilized, the aspect angle signal of simulation inertial navigation output measures corresponding tailplane
Servo deflection control voltage；
E) is calculated by corresponding tailplane and is watched for the additional gain control rate of tailplane by angular speed under fueling state
Clothes deflection control voltage output value meets range, whether correct verifies its control rate；
F) by pitch lever displacement under fueling state and carriage angle signal proportion control rate, corresponding horizontal tail is calculated
Wing servo deflection control voltage output value meets range, whether correct verifies its control rate.
Test environment includes that air refuelling state opens electric switch, angular speed simulation potentiometer, attitude angle in the step a)
Rotary transformer is simulated, the air refuelling state opens electric switch and is connected with teleputer detection platform simulation control oiling shape
State opens control, and the angular speed simulation potentiometer is connected to the teleputer detection platform simulation angular speed variation, institute
It states attitude angle simulation rotary transformer and is connected to the teleputer detection platform simulation inertial navigation attitude angle, the fax calculates
Machine testing platform is connected with tested teleputer, and the teleputer detection platform is provided to the tested teleputer
Working power and air refuelling test condition parameters obtain tailplane servo control by the tested teleputer calculation processing
Voltage processed, measures tailplane servo voltage using voltmeter and whether verify range correct.
Status switch adjunct circuit includes the first triode, the second triode, first triode in the step b)
Be NPN type triode with the second triode ,+15V power supply is connected with after first resistor be connected with second resistance after be grounded, described the
The one end of two resistance remotely is state ON switching signal output point A1, and the one end of the second resistance remotely is connected to institute
State the collector of the first triode, the emitter-base bandgap grading of first triode is connected to the collector of second triode, and described
The emitter grounding of two triodes, the base stage of first triode input B20 signal, and B20 signal is that fueling state is connected in simulation
Signal, virtual value are+27V, and the base stage of second triode inputs A20 signal, and A20 signal is simulation by beam hanger stretching state
Signal, virtual value are+27V, and A20, B20 signal is controlled by individual electric switch and carries out analog signal access.
Angular speed is rate of pitch in the step c), and obtaining for rate of pitch includes using antihunt circuit, pitching
Rate correction circuit, antihunt circuit include that damping resistance circuit and state ON switch, the switch of the state ON switch
State is controlled by the signal of state ON switching signal output point A1, and low level conducting, high level is closed, the pitch angle speed
Degree signal is inputted by B1 endpoint, operates limitation signal from the output pitching of B2 endpoint after damping resistance circuit, B2 endpoint continues
It connects after being connected to the state ON switch after one layer of damping resistance circuit, rate of pitch revise signal is exported by B3 point.
The beneficial effects of the present invention are: the present invention is detected using the teleputer mode of disembarking, will not on aircraft other
System and equipment impact and accidental damage；Input signal is provided using potentiometer and rotary transformer, is simulated on aircraft
The actual physical of sensor element moves, convenient for operation；Using the method substitution of measurement tailplane servo-control signal voltage
Tailplane deflection angle is measured, measuring accuracy is improved.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is test macro connection figure of the invention；
Fig. 2 is status switch circuit diagram of the invention；
Fig. 3 is pitch angle output circuit figure of the invention.
Specific embodiment
In order to be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below it is right
The present invention is further described.
A kind of teleputer air refuelling state control rate detection method, comprising steps of
A) power supply is provided for teleputer work using teleputer test platform, signal input interface is provided, it is defeated
Signal measurement interface out realizes the test environment of air refuelling state；
B) " air refuelling state ", " being stretched out by beam hanger " status switch adjunct circuit are connected, control teleputer enters
Air refuelling state；
C) fixed angular speed analog signal is given using angular speed simulation potentiometer, measures corresponding tailplane servo deflection control
Voltage processed；
D) additional rotary transformer is utilized, the aspect angle signal of simulation inertial navigation output measures corresponding tailplane
Servo deflection control voltage；
E) is calculated by corresponding tailplane and is watched for the additional gain control rate of tailplane by angular speed under fueling state
Clothes deflection control voltage output value meets range, whether correct verifies its control rate；
F) by pitch lever displacement under fueling state and carriage angle signal proportion control rate, corresponding horizontal tail is calculated
Wing servo deflection control voltage output value meets range, whether correct verifies its control rate.
Further, need to realize the test environmental structure of air refuelling state, test system as shown in Figure 1 in step a)
System connection figure:
Test environmental structure includes that air refuelling state opens electric switch, angular speed simulation potentiometer, attitude angle simulation rotation
Transformer, the air refuelling state open electric switch and are connected with the simulation control fueling state unlatching control of teleputer detection platform
System, the angular speed simulation potentiometer are connected to the teleputer detection platform simulation angular speed variation, the attitude angle
Simulation rotary transformer is connected to the teleputer detection platform simulation inertial navigation attitude angle, and the teleputer detection is flat
Platform is connected with tested teleputer, and the teleputer detection platform provides working power to the tested teleputer
With air refuelling test condition parameters, tailplane servo control voltage is obtained by the tested teleputer calculation processing,
Tailplane servo voltage is measured using voltmeter and verifies whether range is correct, and traditional measurement mode is surveyed by mechanical
The pitch angle of tailplane is measured, this method there are large error, watch by the tailplane for being not directly measured teleputer
The precision of clothes control voltage is high.
Further, it needs to control teleputer in step b) and enters air refuelling state, it is therefore desirable to use state
It switchs adjunct circuit and transmits signal, status switch circuit diagram as shown in Figure 2:
Under air refuelling state, emulation mode is needed to switch, including is stretched out switch state, oil filling pipe connection switch by beam hanger
State, status switch adjunct circuit are arranged on BP3-551 plate, including the first triode Q1, the second triode Q2, and described
One triode Q1 and the second triode Q2 is NPN type triode, and+15V power supply is connected with the second electricity after being connected with first resistor R1
It is grounded after resistance R2, the one end of the second resistance R2 remotely is state ON switching signal output point A1, the second resistance
The one end of R2 remotely is connected to the collector of the first triode Q1, and the emitter-base bandgap grading of the first triode Q1 is connected to described
The base stage of the collector of second triode Q2, the emitter grounding of the second triode Q2, the first triode Q1 inputs B20
Signal, B20 signal are that fueling state signal is connected in simulation, and virtual value is+27V, and the base stage of the second triode Q2 inputs A20
Signal, A20 signal are simulations by beam hanger stretching status signal, and virtual value is+27V, and A20, B20 signal is by individual electric switch
Control carries out analog signal access.
Further, it needs to give fixed angular speed analog signal in step c), pitch angle output circuit figure as shown in Figure 3:
Pitch angle output circuit includes correcting circuit using antihunt circuit, rate of pitch, and antihunt circuit is arranged in BP3-
551 with two pieces of circuit boards of BT-457-01, and antihunt circuit includes damping resistance circuit and state ON switch SW, the state
The switch state for connecting switch is controlled by the signal of state ON switching signal output point A1, and low level conducting, high level closes
It closes, the rate of pitch signal is inputted by B1 endpoint, operates clipping from the output pitching of B2 endpoint after damping resistance circuit
Signal, B2 endpoint continue connect one layer of damping resistance circuit after be connected to the state ON switch SW after, by B3 point export bow
Elevation angle speed revise signal.
Further, lead the first triode Q1 simultaneously with the second triode Q2 when A20, B20 signal input+27V simultaneously
Logical, state ON switching signal output point A1 is equivalent to ground connection at this time, and signal voltage is similar to 0V, and the enabled conducting state connects
It opens up and closes SW, simulation fueling state starts, and rate of pitch circuit enters adjust automatically state；When A20, B20 signal at least
One side is not+27V, then state ON switching signal output point A1 will not be grounded, i.e. air refuelling does not start, and the state connects
It opens up and closes SW disconnection, the adjusting of air refuelling rate of pitch will not be got involved in airplane telex computer.
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and what is described in the above embodiment and the description is only the present invention
Principle, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these variation and
Improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention is by appended claims and its equivalent
Object defines.
Claims (9)
1. a kind of teleputer air refuelling state control rate detection method, which is characterized in that comprising steps of
A) power supply is provided for teleputer work using teleputer test platform, signal input interface, output letter is provided
Number measurement interface, realize air refuelling state test environment；
B) " air refuelling state ", " being stretched out by beam hanger " status switch adjunct circuit are connected, control teleputer enters aerial
Fueling state；
C) fixed angular speed analog signal is given using angular speed simulation potentiometer, measures corresponding tailplane servo deflection control electricity
Pressure；
D) additional rotary transformer is utilized, the aspect angle signal of simulation inertial navigation output measures corresponding tailplane servo
Deflection control voltage；
E) it is inclined to be calculated to the additional gain control rate of tailplane by angular speed under fueling state for corresponding tailplane servo
Turn control voltage output value meets range, whether correct verifies its control rate；
F) it by pitch lever displacement under fueling state and carriage angle signal proportion control rate, calculates corresponding tailplane and watches
Clothes deflection control voltage output value meets range, whether correct verifies its control rate.
2. a kind of teleputer air refuelling state control rate detection method according to claim 1, it is characterised in that:
Test environment includes that air refuelling state opens electric switch, angular speed simulation potentiometer, attitude angle simulation rotation in the step a)
Transformer.
3. a kind of teleputer air refuelling state control rate detection method according to claim 2, it is characterised in that:
The air refuelling state opens electric switch and is connected with the simulation control fueling state unlatching control of teleputer detection platform.
4. a kind of teleputer air refuelling state control rate detection method according to claim 2, it is characterised in that:
The angular speed simulation potentiometer is connected to the teleputer detection platform simulation angular speed variation.
5. a kind of teleputer air refuelling state control rate detection method according to claim 2, it is characterised in that:
The attitude angle simulation rotary transformer is connected to the teleputer detection platform simulation inertial navigation attitude angle.
6. a kind of teleputer air refuelling state control rate detection method according to claim 1, it is characterised in that:
The teleputer detection platform is connected with tested teleputer, and the teleputer detection platform is to the tested electricity
It passes computer and working power and air refuelling test condition parameters is provided, water is obtained by the tested teleputer calculation processing
Horizontal tail wing servo control voltage, measures tailplane servo voltage using voltmeter and whether verify range correct.
7. a kind of teleputer air refuelling state control rate detection method according to claim 1, it is characterised in that:
Status switch adjunct circuit includes the first triode (Q1), the second triode (Q2), first triode in the step b)
It (Q1) is NPN type triode with the second triode (Q2) ,+15V power supply is connected with second resistance after being connected with first resistor (R1)
(R2) it is grounded afterwards, the one end of the second resistance (R2) remotely is state ON switching signal output point A1, second electricity
The one end of resistance (R2) remotely is connected to the collector of first triode (Q1), and the emitter-base bandgap grading of first triode (Q1) connects
It is connected to the collector of second triode (Q2), the emitter grounding of second triode (Q2), first triode
(Q1) base stage inputs B20 signal, and B20 signal is that fueling state signal is connected in simulation, and virtual value is+27V, the two or three pole
Manage (Q2) base stage input A20 signal, A20 signal be simulation by beam hanger stretch out status signal, virtual value be+27V, the A20,
B20 signal is controlled by individual electric switch and carries out analog signal access.
8. a kind of teleputer air refuelling state control rate detection method according to claim 1, it is characterised in that:
Angular speed is rate of pitch in the step c), and obtaining for rate of pitch includes being repaired using antihunt circuit, rate of pitch
Positive circuit, antihunt circuit include damping resistance circuit and state ON switch (SW).
9. a kind of teleputer air refuelling state control rate detection method according to claim 8, it is characterised in that:
The switch state of the state ON switch (SW) is controlled by the signal of state ON switching signal output point A1, and low level is led
Logical, high level is closed, and the rate of pitch signal is inputted by B1 endpoint, is bowed after damping resistance circuit from the output of B2 endpoint
Face upward operation limitation signal, B2 endpoint continues to connect be connected to the state ON switch (SW) after one layer of damping resistance circuit after,
Rate of pitch revise signal is exported by B3 point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810827315.1A CN109292111B (en) | 2018-07-25 | 2018-07-25 | Method for detecting air refueling state control rate of telex computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810827315.1A CN109292111B (en) | 2018-07-25 | 2018-07-25 | Method for detecting air refueling state control rate of telex computer |
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| CN109292111A true CN109292111A (en) | 2019-02-01 |
| CN109292111B CN109292111B (en) | 2021-10-26 |
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| US20130168499A1 (en) * | 2011-10-11 | 2013-07-04 | Victor A. Grossman | Rapid store load system for aircraft and method of operation thereof |
| CN105083586A (en) * | 2015-08-12 | 2015-11-25 | 中国航空工业集团公司西安飞机设计研究所 | Device for testing aerial refueling adapter equipment |
| CN106043718A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Airplane boom type air refueling automatic control butt joint method |
| CN106184814A (en) * | 2016-08-18 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | Calculation of pressure method and device at a kind of back pressure regulating valve inlet |
| CN206074235U (en) * | 2016-08-09 | 2017-04-05 | 中国人民解放军第五七二一工厂 | A kind of aircraft is in the air by oily plug special detection device |
-
2018
- 2018-07-25 CN CN201810827315.1A patent/CN109292111B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130168499A1 (en) * | 2011-10-11 | 2013-07-04 | Victor A. Grossman | Rapid store load system for aircraft and method of operation thereof |
| CN105083586A (en) * | 2015-08-12 | 2015-11-25 | 中国航空工业集团公司西安飞机设计研究所 | Device for testing aerial refueling adapter equipment |
| CN106043718A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Airplane boom type air refueling automatic control butt joint method |
| CN206074235U (en) * | 2016-08-09 | 2017-04-05 | 中国人民解放军第五七二一工厂 | A kind of aircraft is in the air by oily plug special detection device |
| CN106184814A (en) * | 2016-08-18 | 2016-12-07 | 中国航空工业集团公司西安飞机设计研究所 | Calculation of pressure method and device at a kind of back pressure regulating valve inlet |
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| CN109292111B (en) | 2021-10-26 |
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