CN112511121A - Airplane power grid differential pressure connection operation circuit - Google Patents
Airplane power grid differential pressure connection operation circuit Download PDFInfo
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- CN112511121A CN112511121A CN202011462686.8A CN202011462686A CN112511121A CN 112511121 A CN112511121 A CN 112511121A CN 202011462686 A CN202011462686 A CN 202011462686A CN 112511121 A CN112511121 A CN 112511121A
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- 238000000034 method Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 3
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- 230000000694 effects Effects 0.000 description 2
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- H—ELECTRICITY
- H03—ELECTRONIC CIRCUITRY
- H03F—AMPLIFIERS
- H03F3/00—Amplifiers with only discharge tubes or only semiconductor devices as amplifying elements
- H03F3/45—Differential amplifiers
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
- G01R19/10—Measuring sum, difference or ratio
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J3/00—Circuit arrangements for ac mains or ac distribution networks
- H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
- H02J3/388—Islanding, i.e. disconnection of local power supply from the network
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Eletrric Generators (AREA)
Abstract
The invention discloses an aircraft power grid differential pressure connection operational circuit.A first operational amplifier, a second operational amplifier, a first triode and a second triode are added between a generator and a junction voltage, and the operational circuit controls the main contactor of the generator to be connected when the differential pressure connection condition is met by comparing the junction voltage with the voltage at the output end of the generator, and the generator is connected into a power grid; when the voltage value output by the generator cannot meet the power supply requirement, the main contactor of the generator is disconnected, the operation circuit controls the contactor of the generator to be disconnected, and the generator exits from the power grid. The aircraft power grid differential pressure switch-on operation circuit in this application selects to be incorporated into the power networks and moves back the net according to the actual behavior of generator, realizes that the generator is incorporated into the power networks and moves back the automatic switch-over of net, does not need the pilot to judge the selection, avoids influencing the flight because of artificial maloperation or other reasons, promotes the stability of aircraft.
Description
Technical Field
The invention relates to the technical field of airplane electrical systems, in particular to an airplane power grid differential pressure connection operation circuit.
Background
The aircraft power supply system is generally designed with a main power supply, a secondary power supply, an auxiliary power supply, a backup power supply and an emergency power supply according to the power source of the aircraft power supply system. The main power system is an engine-driven generator system that provides all of the electrical power during normal flight conditions of the aircraft. The time for the generator, which is the core device in the main power supply system, to be incorporated into the power grid and to be withdrawn from the power grid during normal operation is very important, and the stability of the main power supply system is directly influenced too early or too late. The old airplane is designed with a low-voltage generator alarm, when the output voltage value of the generator cannot meet the requirement, a pilot can judge the airplane state according to the alarm, and choose to cut off the power supply line of the generator and supply power by other power supplies (such as an auxiliary power supply, a backup power supply and an emergency power supply), but the design mode has certain defects, and the alarm line fault and the manual misoperation can cause unsatisfactory treatment effect, thereby influencing the flight stability.
Disclosure of Invention
The invention aims to solve the technical problem of unsatisfactory effect caused by manual operation of launching and exiting a network of the existing airplane, and provides an airplane power grid differential pressure connection operation circuit, which enables a generator to be merged into a power grid when the output voltage of the generator meets the requirement; when the output voltage of the generator is too low, the generator is enabled to exit from the power grid, grid connection and grid disconnection are selected according to the actual working condition of the generator, automatic switching of grid connection and grid disconnection of the generator is achieved, a pilot does not need to judge selection, flying is prevented from being influenced due to manual misoperation or other reasons, and the stability of the airplane is improved.
In order to solve the technical problem, the invention provides an aircraft power grid differential pressure connection operational circuit, which comprises a first operational amplifier, a second operational amplifier, a first triode and a second triode, wherein power supply ends of the first operational amplifier and the second operational amplifier are connected with the positive end voltage of a generator, and grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the pivot voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with a diode A400 and a resistor R106 in series and is connected with the reverse end of the second operational amplifier, the homodromous end of the second operational amplifier is connected with a resistor R105 in series and is grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitting electrode of the first triode is grounded, the collector electrode series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector electrode of the second triode is connected with the main contactor, and the emitting electrode of the second triode is in signal connection with the generator switch.
In an alternative embodiment of the present application, the generator positive terminal voltage is connected in series with the ground terminal resistor R102 and the zener diode V200.
In an optional embodiment of the present application, a voltage stabilizing circuit is disposed between the voltage regulator V200 and the resistor R101.
In an optional embodiment of the present application, the voltage stabilizing circuit includes a rectifying tube V201 and a resistor R103 connected in parallel.
In an optional embodiment of the present application, an adjustable resistor R104 is provided between the voltage of the positive terminal of the generator and the resistor R100.
The aircraft power grid differential pressure connection operational circuit comprises a first operational amplifier, a second operational amplifier, a first triode and a second triode, wherein power supply ends of the first operational amplifier and the second operational amplifier are connected with the positive end voltage of a generator, and grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the pivot voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with a diode A400 and a resistor R106 in series and is connected with the reverse end of the second operational amplifier, the homodromous end of the second operational amplifier is connected with a resistor R105 in series and is grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitting electrode of the first triode is grounded, the collector electrode series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector electrode of the second triode is connected with the main contactor, and the emitting electrode of the second triode is in signal connection with the generator switch.
According to the airplane power grid differential pressure connection operation circuit, the operation circuit is added between a generator and a junction voltage, the junction voltage is compared with the voltage of the output end of the generator, when the differential pressure connection condition is met, the operation circuit controls the main contactor of the generator to be connected, and the generator is connected to a power grid; when the voltage value output by the generator cannot meet the power supply requirement, the main contactor of the generator is disconnected, the operation circuit controls the contactor of the generator to be disconnected, and the generator exits from the power grid. The normal operation of the aircraft power supply system is ensured through the control of the operational circuit, the grid connection and grid disconnection can be selected according to the actual working condition of the generator by the circuit design, the judgment and selection of a pilot are not needed, the influence on the flight caused by manual misoperation or other reasons is avoided, the stability of the aircraft power supply system can be greatly improved, and the flight safety is ensured.
Drawings
In order to more clearly illustrate the embodiments or technical solutions of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
Fig. 1 is a schematic diagram of a principle of an aircraft power grid differential pressure connection operation circuit provided in an embodiment of the present application.
Detailed Description
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
As shown in fig. 1, fig. 1 is a schematic diagram of a principle of an aircraft power grid differential voltage connection operation circuit provided in an embodiment of the present application, where the aircraft power grid differential voltage connection operation circuit includes: the aircraft power grid differential pressure connection operational circuit comprises a first operational amplifier, a second operational amplifier, a first triode and a second triode, wherein power ends of the first operational amplifier and the second operational amplifier are connected with the positive end voltage of a generator, and grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the pivot voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with a diode A400 and a resistor R106 in series and is connected with the reverse end of the second operational amplifier, the homodromous end of the second operational amplifier is connected with a resistor R105 in series and is grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitting electrode of the first triode is grounded, the collector electrode series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector electrode of the second triode is connected with the main contactor, and the emitting electrode of the second triode is in signal connection with the generator switch.
In the embodiment, the operational circuit is additionally arranged between the generator and the junction voltage, and the operational circuit comprises an operational amplifier, a resistor, a voltage regulator tube, a rectifier tube, a triode and the like. By comparing the voltage of the pivot with the voltage of the output end of the generator, when the condition of differential pressure connection is met, the operation circuit controls the main contactor of the generator to be connected, and the generator is connected to a power grid; when the voltage value output by the generator cannot meet the power supply requirement, the main contactor of the generator is disconnected, the operation circuit controls the contactor of the generator to be disconnected, and the generator exits from the power grid. The circuit design can select grid connection and grid disconnection according to the actual working condition of the generator, does not need a pilot to judge selection, and avoids influencing flight due to manual misoperation or other reasons.
Further, in an embodiment of the present application, the generator positive terminal voltage is regulated by a resistor R102 and a zener diode V200 connected in series with the ground terminal to obtain a predetermined reference voltage.
Furthermore, the junction voltage is limited by the resistor R101 and then connected to the + end of the N300, so that the (+) voltage of the equidirectional end of the N300 is relatively stable in order to eliminate the influence of junction voltage change, and a voltage stabilizing circuit is arranged between the voltage stabilizing tube V200 and the resistor R101 to stabilize the voltage value within a certain range.
It should be noted that the voltage regulator circuit is not limited in particular, and may be a rectifier tube V201 and a resistor R103 connected in parallel, where the resistor R103 and the rectifier tube V201 stabilize the voltage value within a certain range, so as to divide the influence of the junction voltage variation.
In another embodiment of the present application, the output voltage of the generator is limited by a resistor R100 and then connected to the reverse end of the first operational amplifier, an adjustable resistor R104 is disposed between the positive end voltage of the generator and the resistor R100, the adjustable resistor R104 is a shunt circuit, and the reverse end voltage of the first operational amplifier can be adjusted in advance, so that even if the normal voltage value output by the generator is 0.2-0.5V lower than the normal value of the junction voltage, the reverse end voltage is still higher than the voltage of the same direction end, the output of the first operational amplifier is inverted, and the output high potential is changed into the low potential (the differential voltage signal is effective).
Specifically, as shown in fig. 1, the operational amplifier N300 outputs a high potential when the reverse terminal (-) voltage is lower than the common terminal (+) voltage, and outputs a low potential (signal active) when the reverse terminal (-) voltage is higher than the common terminal (+) voltage. Working power supplies of the operational amplifiers N300 and N301 are both from the voltage C at the positive end of the generator, are grounded after passing through holes 1 and 2 of the operational amplifiers N300 and N301, and are divided by a resistor R102 and stabilized by a voltage stabilizing tube V200. The main contactor connection control circuit consists of an operational amplifier N301 and switching circuits of triodes B500 and B501.
The junction voltage is input from B, and is connected to the + end of N300 after being limited by the resistor R101, and the resistor R103 and the rectifying tube V201 stabilize the voltage value within a certain range so as to eliminate the influence of the junction voltage change and relatively stabilize the (+) voltage of the equidirectional end of N300. The output voltage of the generator is input from A, is limited by the resistor R100 and then is connected to the reverse end (-) of the operational amplifier N300, the adjustable resistor R104 is a shunt circuit and can adjust the reverse end (-) voltage of the N300 in advance, so that even if the normal voltage value output by the generator is 0.2-0.5V lower than the normal value of the junction voltage, the reverse end (-) voltage is still higher than the voltage of the same-direction end (+) and the output of the operational amplifier N300 is inverted and is changed from high output potential to low potential (a differential voltage signal is effective).
The differential voltage signal outputted from the operational amplifier N300 is connected to the inverting terminal (-) of the operational amplifier N301 through the diode A400 and the resistor R106, and the non-inverting terminal (+) of the operational amplifier N301 is connected to the preset reference voltage regulated by the resistor R105. When the voltage difference signal is compared with the reference voltage, when the voltage of the reverse end (-) of the N301 is lower than the voltage of the same-direction end (+), the operational amplifier outputs high potential, the triode B500 works through the rectifier tube V202 and the resistor R107, at the moment, if the generator switching signal is switched on (E input), the collector current of the B500 passes through the resistor R108, the base electrode of the B501 has current, the B501 works, the voltage input at the point E outputs a working signal of the main contactor through the B501 and the K, the main contactor works, and the generator is connected to a power grid.
When the differential pressure signal is invalid (namely the operational amplifier N300 outputs high potential), the voltage of the reverse end (-) of the operational amplifier N301 is higher than the preset voltage value of the homodromous end (+), at the moment, the low potential is output, the triode B500 is cut off, the B501 is cut off, the voltage input at the point E cannot reach K through the B501 and outputs a working signal of the main contactor, the main contactor does not work, and the generator exits the power grid.
According to the airplane power grid differential pressure switch-on operation circuit, when the output voltage of the generator is higher than the hub voltage and lower than the preset voltage value, the generator can be incorporated into the power grid to work, and otherwise, the generator exits from the power grid. The circuit design greatly improves the stability of the aircraft power supply system, and avoids the influence on the normal operation of the aircraft power supply system due to human misoperation, line faults and the like.
It should be noted that, in this specification, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that the products of the present invention are conventionally placed in when used, and are used only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
It should also be noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are intended to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Furthermore, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include elements inherent in the list. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element. In addition, parts of the above technical solutions provided in the embodiments of the present application, which are consistent with the implementation principles of corresponding technical solutions in the prior art, are not described in detail so as to avoid redundant description.
The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (5)
1. The utility model provides an aircraft electric wire netting pressure differential switch-on arithmetic circuit which characterized in that: the power supply system comprises a first operational amplifier, a second operational amplifier, a first triode and a second triode, wherein the power supply ends of the first operational amplifier and the second operational amplifier are connected with the positive end voltage of a generator, and the grounding ends of the first operational amplifier and the second operational amplifier are grounded; the generator output voltage series resistor R100 is connected with the reverse end of the first operational amplifier, and the pivot voltage series resistor R101 is connected with the same-direction end of the first operational amplifier; the output end of the first operational amplifier is connected with a diode A400 and a resistor R106 in series and is connected with the reverse end of the second operational amplifier, the homodromous end of the second operational amplifier is connected with a resistor R105 in series and is grounded, and the output end of the second operational amplifier is connected with a diode V202 and a resistor R107 in series and is connected with the base electrode of the first triode; the emitting electrode of the first triode is grounded, the collector electrode series resistor R108 of the first triode is connected with the base electrode of the second triode, the collector electrode of the second triode is connected with the main contactor, and the emitting electrode of the second triode is in signal connection with the generator switch.
2. An aircraft grid voltage difference switch-on operational circuit as claimed in claim 1, wherein the generator positive terminal voltage is connected in series with a ground terminal resistor R102 and a zener diode V200.
3. An aircraft power grid voltage difference connection operation circuit as claimed in claim 2, wherein a voltage stabilizing circuit is arranged between the voltage stabilizing tube V200 and the resistor R101.
4. An aircraft power grid voltage difference switch-on operational circuit as claimed in claim 3, wherein said voltage regulation circuit comprises a rectifier tube V201 and a resistor R103 connected in parallel.
5. An aircraft power grid voltage difference switch-on operation circuit as claimed in claim 1, wherein an adjustable resistor R104 is arranged between the voltage of the positive terminal of the generator and the resistor R100.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011462686.8A CN112511121B (en) | 2020-12-12 | 2020-12-12 | Airplane power grid differential pressure switching-on operation circuit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011462686.8A CN112511121B (en) | 2020-12-12 | 2020-12-12 | Airplane power grid differential pressure switching-on operation circuit |
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| CN112511121A true CN112511121A (en) | 2021-03-16 |
| CN112511121B CN112511121B (en) | 2024-04-02 |
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