CN111308383A - Aircraft power supply adaptability test feedback control circuit - Google Patents
Aircraft power supply adaptability test feedback control circuit Download PDFInfo
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- CN111308383A CN111308383A CN201911139543.0A CN201911139543A CN111308383A CN 111308383 A CN111308383 A CN 111308383A CN 201911139543 A CN201911139543 A CN 201911139543A CN 111308383 A CN111308383 A CN 111308383A
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- power supply
- switch
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- throw relay
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/40—Testing power supplies
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R1/00—Details of instruments or arrangements of the types included in groups G01R5/00 - G01R13/00 and G01R31/00
- G01R1/20—Modifications of basic electric elements for use in electric measuring instruments; Structural combinations of such elements with such instruments
Abstract
The invention belongs to the technical field of test and measurement, and relates to a feedback control circuit for an aircraft power supply adaptability test, which comprises a power supply (1), a power supply output safety switch (2), a test bed switch-on switch (3) and a power supply output switch (4); the feedback control circuit provided by the invention realizes automatic adjustment of the power supply output voltage in the aircraft power supply adaptability test by switching the plurality of relays, thereby reducing the configuration requirement of the power supply adaptability test system, shortening the test preparation time and reducing the test risk.
Description
Technical Field
The invention belongs to the technical field of test and measurement, and relates to a feedback control circuit for an aircraft power supply adaptability test, which is used for automatically adjusting output voltage according to voltage values of different feedback points on a power supply line in the aircraft power supply adaptability test process of a program-controlled direct-current power supply so as to meet test requirements.
Background
The aircraft needs to be matched with corresponding carriers, such as an aerial platform and a ground platform, different carriers provide power supply environments for the aircraft with great difference, and in the process of developing the aircraft, the aircraft power supply adaptability test aims at checking the working state and the adaptation condition of the aircraft in different power supply environments.
Fig. 1 is a feedback control circuit for aircraft power supply adaptability test in the prior art. Including power 1, power output safety switch 2, test bench switch-on switch 3, power supply output switch 4, 5 and voltage monitoring equipment 9 of being tried aircraft, wherein, switch-on power output safety switch 2, test bench power supply switch 3 and power supply output switch 4 back in proper order, the aircraft is supplied power, voltage monitoring equipment 9 receives feedback signal, operating personnel adjusts power 1 output voltage according to feedback signal, the voltage that makes power 1 output satisfies experimental requirement.
The drawback of the feedback control circuit shown in fig. 1 is that:
1) the voltage monitoring device 9 needs to be configured.
2) The operating personnel carries out power output voltage regulation according to the voltage signal that voltage monitoring equipment 9 received, and the accommodation process is consuming time longer and easily appears repeatedly, for satisfying the experimental real-time nature requirement of aircraft power adaptability, needs carry out the power supply many times to being tried aircraft 5, brings the risk for aircraft power adaptability is experimental.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a feedback control circuit for an aircraft power supply adaptability test, which utilizes a plurality of relays to switch to realize the automatic adjustment of the output voltage of a power supply in the aircraft power supply adaptability test, thereby reducing the configuration requirement of a power supply adaptability test system, shortening the test preparation time and reducing the test risk.
The technical scheme of the invention is as follows: a voltage feedback control circuit for aircraft power adaptability test comprises a power supply 1, a power output safety switch 2, a test bed switch-on switch 3 and a power supply output switch 4; the positive pole of the power supply 1 is sequentially connected with the power output safety switch 2, the test bed switch-on switch 3 and the power supply output switch 4 to be tested, and the negative pole of the power supply 1 is sequentially connected with the tested aircraft 5 through the power output safety switch 2, the test bed switch-on switch 3 and the power supply output switch 4; the test bench is characterized in that a first double-pole double-throw relay 6 is additionally arranged between a power supply 1 and a power supply output safety switch 2, a second double-pole double-throw relay 7 is additionally arranged between the power supply output safety switch 2 and a test bench switch-on switch 3, and a third double-pole double-throw relay 8 is additionally arranged between the test bench switch-on switch 3 and a power supply output switch 4.
The positive pole of the power supply 1 is connected with the feedback positive pole of the power supply 1 through a first double-pole double-throw relay 6 normally closed point; the positive pole of the power supply 1 is connected with the feedback positive pole of the power supply sequentially through a power supply output safety switch 2, a normally closed point of a second double-pole double-throw relay 7 and a normally open point of a first double-pole double-throw relay 6.
The positive electrode of the power supply 1 is also connected with the positive electrode of a coil of a first double-pole double-throw relay 6 through a power supply output safety switch 2; the positive pole of the power supply 1 is connected with the feedback positive pole of the power supply 1 through a power output safety switch 2, a test bed switch-on switch 3, a third double-pole double-throw relay 8 normally-closed point, a second double-pole double-throw relay 7 normally-open point and a first double-pole double-throw relay 6 normally-open point in sequence.
The positive pole of the power supply 1 is connected with the positive pole of a coil of a second double-pole double-throw relay 7 through a power supply output safety switch 2 and a test bed switch-on switch 3 in sequence.
The positive pole of the power supply 1 is connected with the positive pole of a coil of a third double-pole double-throw relay 8 sequentially through a power supply output safety switch 2, a test bed switch-on switch 3 and a power supply output switch 4.
The negative pole of the power supply 1 is also connected with the feedback negative pole of the power supply 1 through a first double-pole double-throw relay 6 normally closed point.
The negative pole of the power supply 1 is connected with the feedback negative pole of the power supply 1 sequentially through a power supply output safety switch 2, a normally closed point of a second double-pole double-throw relay 7 and a normally open point of a first double-pole double-throw relay 6.
The negative pole of the power supply 1 is also connected with the negative pole of a coil of a first double-pole double-throw relay 6 through a power supply voltage safety switch 2.
The negative pole of the power supply 1 is connected with the feedback negative pole of the power supply 1 through a power output safety switch 2, a test bed switch-on switch 3, a normally closed point of a third double-pole double-throw relay 8, a normally open point of a second double-pole double-throw relay 7 and a normally open point of a first double-pole double-throw relay 6 in sequence.
And the negative electrode of the power supply 1 is also connected with the negative electrode of a coil of a second double-pole double-throw relay 7 through a power supply output safety switch 2 and a test bed switch-on switch 3 in sequence.
The positive pole of the power supply 1 is connected with the negative pole of a coil of a third double-pole double-throw relay 8 sequentially through a power output safety switch 2, a test bed switch-on switch 3 and a power supply output switch 4.
The feedback control circuit has the advantages that the feedback control circuit realizes automatic adjustment of the output voltage of the power supply in the aircraft power supply adaptability test by switching the plurality of relays, so that the configuration requirement of the power supply adaptability test system is reduced, the test preparation time is shortened, and the test risk is reduced.
Drawings
FIG. 1 is a schematic diagram of a prior art aircraft power supply suitability test circuit connection,
fig. 2 is a schematic diagram of a feedback control circuit according to the present invention.
1: power supply, 2: power output safety switch, 3: test stand on switch, 4: power supply output switch, 5: test aircraft, 6: first double pole double throw relay, 7: second double pole double throw relay, 8: third double-pole double-throw relay, 9: voltage monitoring device
Detailed Description
Reference will now be made in detail to the embodiments of the present invention, examples of which are illustrated in fig. 2, wherein like or similar reference numerals refer to like or similar elements or elements having similar functions. The embodiments described below with reference to the drawings are illustrative only and should not be construed as limiting the invention.
The aircraft power supply adaptability test feedback control circuit comprises a power supply 1, a power supply output safety switch 2, a test bed switch-on switch 3, a power supply output switch 4, a tested aircraft 5, a first double-pole double-throw relay 6, a second double-pole double-throw relay 7 and a third double-pole double-throw relay 8. Wherein the power supply 1 is a power supply required by the test; the power output safety switch 2 is a double-pole double-throw switch, so that the output voltage of the power supply 1 can meet the working requirement of a test bed, the on-off state of the power output safety switch determines whether a coil of the first double-pole double-throw relay 6 is driven by a power supply or not, and also determines whether a feedback voltage acquisition point sent to the power supply 1 is at the front end or the rear end of the power output safety switch 2; the test bed switch-on switch 3 is a double-pole double-throw switch, the test bed is ready after being switched on, the switching state of the test bed switch-on switch determines whether a coil of the second double-pole double-throw relay 7 is driven by a power supply or not, and also determines whether a feedback voltage acquisition point sent to the power supply 1 is at the front end or the rear end of the test bed switch-on switch 3; the power supply output switch 4 is a double-pole double-throw switch, supplies power to the tested aircraft according to a test process, and the on-off state of the power supply output switch determines whether a coil of the third double-pole double-throw relay 8 is driven by a power supply or not and also determines whether a feedback voltage acquisition point sent to the power supply 1 is at the front end or the rear end of the power supply output switch 4; the test flying device 5 is a test object of the test.
The aircraft power supply adaptability test voltage feedback control circuit is specifically linked as follows: the positive pole of the power supply 1 is connected with the tested aircraft 5 sequentially through the first knife 21 of the power output safety switch 2, the first knife 31 of the test bed switch-on switch 3 and the first knife 41 of the power supply output switch.
The positive pole of the power supply 1 is also connected to the feedback positive pole of the power supply via a first double pole double throw relay 6 normally closed point 61.
The positive pole of the power supply 1 is connected with the feedback positive pole of the power supply sequentially through the first knife 21 of the power supply output safety switch 2, the normally closed point 71 of the second double-pole double-throw relay 7 and the normally open point 62 of the first double-pole double-throw relay 6.
The positive pole of the power supply 1 is also connected with the positive pole of the coil of the first double-pole double-throw relay 6 through the first pole 21 of the power output safety switch 2.
The positive pole of the power supply 1 is connected with the power supply feedback positive pole through the first knife 21 of the power supply output safety switch 2, the first knife 31 of the test bed switch-on switch, the normally closed point 81 of the third double-pole double-throw relay 8, the normally open point 72 of the second double-pole double-throw relay 7 and the normally open point 62 of the first double-pole double-throw relay 6 in sequence.
The positive pole of the power supply 1 is connected with the coil positive pole of the second relay 7 through the first knife 21 of the power output safety switch 2 and the first knife 31 of the test bed switch-on switch 3 in sequence.
The positive pole of the power supply 1 is connected with the coil positive pole of the third double-pole double-throw relay 8 through the first knife 21 of the power supply output safety switch 2, the first knife 31 of the test bed switch-on switch 3 and the first knife 41 of the power supply output switch 4 in sequence.
The negative pole of the power supply 1 is connected with the tested aircraft 5 sequentially through the second knife 22 of the power output safety switch 2, the second knife 32 of the test bed switch-on switch 3 and the second knife 42 of the power supply output switch.
The negative pole of the power supply 1 is also connected with the feedback negative pole of the power supply through a normally closed point 63 of the first double-pole double-throw relay 6.
The negative pole of the power supply 1 is connected with the feedback negative pole of the power supply sequentially through the second pole 22 of the power supply output safety switch 2, the normally closed point 73 of the second double-pole double-throw relay 7 and the normally open point 64 of the first double-pole double-throw relay 6.
The negative pole of the power supply 1 is also connected with the negative pole of the coil of the first double-pole double-throw relay 6 through the second pole 22 of the power output safety switch 2.
The negative pole of the power supply 1 is connected with the negative pole of the power supply feedback through the second pole 22 of the power supply output safety switch 2, the second pole 32 of the test bed switch-on switch, the normally closed point 83 of the third double-pole double-throw relay 8, the normally open point 74 of the second double-pole double-throw relay 7 and the normally open point 64 of the first double-pole double-throw relay 6 in sequence.
The negative pole of the power supply 1 is connected with the coil negative pole of the second relay 7 through the second knife 22 of the power output safety switch 2 and the second knife 32 of the test bed switch-on switch 3 in sequence.
The negative pole of the power supply 1 is connected with the coil negative pole of the third double-pole double-throw relay 8 through the second pole 22 of the power output safety switch 2, the second pole 32 of the test bed switch-on switch 3 and the second pole 42 of the power supply output switch 4 in sequence.
The power output safety switch 2, the test bed switch-on switch 3 and the power supply output switch 4 are double-pole double-throw switches.
Claims (10)
1. A voltage feedback control circuit for aircraft power adaptability test comprises a power supply (1), a power output safety switch (2), a test bed switch-on switch (3) and a power supply output switch (4); the positive electrode of a power supply (1) is sequentially connected with a power output safety switch (2), a test bed switch-on switch (3) and a power supply output switch (4) and a tested aircraft (5), and the negative electrode of the power supply (1) is sequentially connected with the tested aircraft (5) through the power output safety switch (2), the test bed switch-on switch (3) and the power supply output switch (4); the test bench is characterized in that a first double-pole double-throw relay (6) is additionally arranged between a power supply (1) and a power supply output safety switch (2), a second double-pole double-throw relay (7) is additionally arranged between the power supply output safety switch (2) and a test bench switch-on switch (3), and a third double-pole double-throw relay (8) is additionally arranged between the test bench switch-on switch (3) and a power supply output switch (4).
2. The aircraft power supply adaptability test voltage feedback control circuit of claim 1, wherein the positive pole of the power supply (1) is connected with the feedback positive pole of the power supply (1) through a first double-pole double-throw relay (6) normally closed point; the positive pole of the power supply (1) is connected with the feedback positive pole of the power supply sequentially through a power supply output safety switch (2), a normally closed point of a second double-pole double-throw relay (7) and a normally open point of a first double-pole double-throw relay (6).
3. The aircraft power supply adaptability test voltage feedback control circuit according to claim 1, wherein the positive electrode of the power supply (1) is further connected with the positive electrode of the coil of the first double-pole double-throw relay (6) through the power supply output safety switch (2); the positive pole of the power supply (1) is connected with the feedback positive pole of the power supply (1) sequentially through a power supply output safety switch (2), a test bed switch-on switch (3), a third double-pole double-throw relay (8) normally-closed point, a second double-pole double-throw relay (7) normally-open point and a first double-pole double-throw relay (6) normally-open point.
4. The aircraft power supply adaptability test voltage feedback control circuit as claimed in claim 1, wherein the positive pole of the power supply (1) is connected with the positive pole of the coil of the second double-pole double-throw relay (7) through a power supply output safety switch (2) and a test bed switch-on switch (3) in sequence.
5. The aircraft power supply adaptability test voltage feedback control circuit according to claim 1, wherein the positive electrode of the power supply (1) is connected with the positive electrode of the coil of the third double-pole double-throw relay (8) through a power supply output safety switch (2), a test bed switch-on switch (3) and a power supply output switch (4) in sequence.
6. The aircraft power supply adaptability test voltage feedback control circuit according to claim 1, characterized in that the negative pole of the power supply (1) is further connected with the feedback negative pole of the power supply (1) through a first double-pole double-throw relay (6) normally closed point.
7. The aircraft power supply adaptability test voltage feedback control circuit of claim 1, characterized in that the negative pole of the power supply (1) is further connected with the feedback negative pole of the power supply (1) sequentially through a power supply output safety switch (2), a normally closed point of a second double-pole double-throw relay (7), and a normally open point of a first double-pole double-throw relay (6).
8. The aircraft power supply adaptability test voltage feedback control circuit according to claim 1, wherein the negative electrode of the power supply (1) is further connected with the negative electrode of the coil of the first double-pole double-throw relay (6) through a power supply voltage safety switch (2); the negative pole of the power supply (1) is connected with the feedback negative pole of the power supply (1) sequentially through a power supply output safety switch (2), a test bed switch-on switch (3), a third double-pole double-throw relay (8) normally-closed point, a second double-pole double-throw relay (7) normally-open point and a first double-pole double-throw relay (6) normally-open point.
9. The aircraft power supply adaptability test voltage feedback control circuit according to claim 1, wherein the negative electrode of the power supply (1) is further connected with the negative electrode of the coil of the second double-pole double-throw relay (7) through the power supply output safety switch (2) and the test bed switch-on switch (3) in sequence.
10. The aircraft power supply adaptability test voltage feedback control circuit according to claim 1, wherein the positive pole of the power supply (1) is connected with the negative pole of the coil of the third double-pole double-throw relay (8) through a power supply output safety switch (2), a test bed switch-on switch (3) and a power supply output switch (4) in sequence.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911139543.0A CN111308383B (en) | 2019-11-19 | 2019-11-19 | Aircraft power supply adaptability test feedback control circuit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911139543.0A CN111308383B (en) | 2019-11-19 | 2019-11-19 | Aircraft power supply adaptability test feedback control circuit |
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| CN111308383A true CN111308383A (en) | 2020-06-19 |
| CN111308383B CN111308383B (en) | 2022-02-15 |
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2019
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| US20160091556A1 (en) * | 2013-01-28 | 2016-03-31 | China University Of Mining And Technology | Fault diagnosis method for freewheeling diodes of dual-switch power converter of switched reluctance motor |
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