CN115513901A - Overvoltage protection circuit of aviation alternating-current generator - Google Patents

Overvoltage protection circuit of aviation alternating-current generator Download PDF

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Publication number
CN115513901A
CN115513901A CN202211216450.5A CN202211216450A CN115513901A CN 115513901 A CN115513901 A CN 115513901A CN 202211216450 A CN202211216450 A CN 202211216450A CN 115513901 A CN115513901 A CN 115513901A
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capacitor
circuit
resistor
output
operational amplifier
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邵静
梁少盟
徐莉娜
陈复盼
赵欣荣
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Shaanxi Aero Electric Co Ltd
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Shaanxi Aero Electric Co Ltd
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Priority to CN202211216450.5A priority Critical patent/CN115513901A/en
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
    • H02H7/06—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for dynamo-electric generators; for synchronous capacitors
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
    • H02H3/20—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess voltage

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Abstract

The application belongs to the technical field of aviation electrical design, and particularly relates to an overvoltage protection circuit of an aviation alternating-current generator. This overvoltage protection power circuit includes: the peak value sampling circuit is used for rectifying the three-phase alternating current; the following circuit is used for filtering the rectified voltage signal to form an output voltage signal V4 which is the same as the input voltage signal; the integration circuit is used for integrating the output voltage signal of the follower circuit, and the time for the output voltage signal V6 of the integration circuit to be reduced from high to a specified voltage is in a linear relation with the jump amount of the output voltage signal V4 of the follower circuit; and the control protection signal output circuit is used for outputting a low-level signal for controlling the trip protection of the aviation alternating-current generator after the output voltage signal V6 of the integrating circuit is lowered to a specified voltage. According to the method and the device, the overvoltage reverse delay protection can be realized by utilizing a hardware circuit on the premise that the software overvoltage protection fails or the software overvoltage reverse delay cannot effectively trip and protect after exceeding the overvoltage reverse delay specified by relevant standards.

Description

Overvoltage protection circuit of aviation alternating-current generator
Technical Field
The application belongs to the technical field of aviation electrical design, and particularly relates to an overvoltage protection circuit of an aviation alternating-current generator.
Background
The overvoltage protection time is an important index of an aviation alternating-current power generation system, and the output overvoltage of the aviation alternating-current power generator is not allowed by electric equipment, so that the safety of a power supply system can be damaged. At present, overvoltage reverse delay protection is mainly carried out by a software fault protection functional module in an aviation alternating-current generator controller.
When the aircraft alternator works under severe environment conditions such as electromagnetism, heat and temperature, the software fault protection function module in the controller of the aircraft alternator may have the phenomena of program runaway, program flow disorder or crash, so that the aircraft alternator continuously outputs overvoltage, cannot output qualified electric energy meeting the requirements of relevant standards such as ISO1540:2006 or GJB 181B-2012 national military standard, and cannot perform trip protection within a specified time, and thus, a disaster-level overvoltage fault is caused, and rear-level electric equipment is damaged.
Disclosure of Invention
In order to solve the problems, the application provides an overvoltage protection circuit of an aviation alternating-current generator, which is a hardware overvoltage reverse delay protection circuit, can realize the backup overvoltage protection function of the aviation alternating-current generator, forms an independent non-similar design with the software overvoltage protection function of an alternating-current generator controller, and avoids the disaster-level failure that the overvoltage failure occurs and the overvoltage protection fails in a power generation system due to the single-point failure in the aviation alternating-current power generation system.
The application provides an aviation alternator overvoltage protection circuit mainly includes:
the peak value sampling circuit is used for rectifying the collected three-phase alternating current;
the following circuit is connected behind the peak value sampling circuit and is used for filtering the rectified voltage signal to form an output voltage signal V4 which is the same as the input voltage signal;
the integrating circuit is connected behind the follower circuit and is used for integrating the output voltage signal of the follower circuit, and the time for the output voltage signal V6 of the integrating circuit to be reduced from high to a specified voltage is in a linear relation with the step-up amount of the output voltage signal V4 of the follower circuit;
and the control protection signal output circuit is connected behind the integrating circuit and used for outputting a low-level signal for controlling the trip protection of the aviation alternating-current generator after the output voltage signal V6 of the integrating circuit is lower than a specified voltage.
Preferably, the peak sampling circuit includes resistors R1 to R7, diodes D1 to D3, and capacitors C1 to C2; one end of each of resistors R1, R2 and R3 is connected with the output phase A, the phase B and the phase C of the voltage regulation point of the aviation alternating current power generation system respectively, the other end of each of the resistors R1, R2 and R3 is connected with the anode of each of diodes D1, D2 and D3 respectively, the cathodes of the diodes D1, D2 and D3 are in short-circuit connection, the short-circuit ends are connected with one end of a capacitor C1 and one end of a resistor R4 respectively, the other end of the capacitor C1 is connected with the ground, the other end of the resistor R4 is connected with a resistor R5, one end of the resistor R5 is connected with one end of a resistor R6, the other end of the resistor R6 is connected with one end of a resistor R7 and one end of a capacitor C2 respectively, the other end of the resistor R7 and the other end of the capacitor C2 are connected with the ground, and the electrical point at which the other end of the resistor R6 is connected with one end of the resistor R7 and one end of the capacitor C2 respectively is the output end of the peak sampling circuit 1;
the peak value sampling circuit is rectified through resistors R1 to R7 and a capacitor C1, the average value of the rectified voltage is V1, and the V1 is subjected to high-frequency filtering through voltage division of resistors R4, R5, R6 and R7 and a capacitor C2 to form a voltage signal V2 input into the following circuit.
Preferably, in the peak sampling circuit, the resistors R1 to R7 and the capacitor C1 are configured such that the relationship between the input three-phase voltages UA, UB, UC and the rectified voltage average value V1 is:
Figure BDA0003876323760000021
preferably, the follower circuit comprises a resistor R8, a resistor R9, capacitors C3 to C5 and an operational amplifier N5A; one end of a resistor R8 is connected with the output end of the peak value sampling circuit 1, the other end of the resistor R8 is respectively connected with an input positive end of an operational amplifier N5A, one end of a capacitor C3 and one end of a capacitor C4, one end of the capacitor C3 is connected with one end of the capacitor C4 and is connected with a pin 3 of the input positive end of the operational amplifier N5, the other end of the capacitor C3 is connected with the other end of the capacitor C4 and is connected with one end of a resistor R9, the connection point is the output end of a following circuit 2, the other end of the resistor R9 is connected with a pin 2 of the input negative end of the operational amplifier N5A, a pin 4 of the operational amplifier N5A is respectively connected with +15VDC and one end of the capacitor C5, the other end of the capacitor C5 is connected with the ground, a pin 11 of the operational amplifier N5A is connected with the ground, and the output voltage V4 of the operational amplifier N5A is the same as the output voltage V2 of the peak value sampling circuit.
Preferably, the capacitor C3 and the capacitor C4 are high-frequency filter capacitors, and the capacitor C5 is a decoupling capacitor.
Preferably, the integrating circuit comprises a resistor R10, a resistor R11, a capacitor C6, a capacitor C7, a capacitor C8 and an operational amplifier N5B; one end of a resistor R10 is connected with the output end of the follower circuit, the other end of the resistor R10 is connected with one ends of a capacitor C7 and a capacitor C8, two ends of the capacitor C7 and the capacitor C8 are respectively in short circuit, the point where the other end of the resistor R10 is connected with one end of the capacitor C7 and one end of the capacitor C8 is connected with the input negative terminal 6 pin of the operational amplifier N5B, the other end of the capacitor C7 and the other end of the capacitor C8 in short circuit is connected with the output terminal 7 pin of the operational amplifier N5B, the connection point is the output end of the integrating circuit, one end of a resistor R11 is respectively connected with 5V reference voltage and one end of the capacitor C6, the other end of the capacitor C6 is connected with the ground, and the saturated output voltage of the operational amplifier N5B is set to be 13V.
Preferably, the hardware overvoltage protection delay time can be adjusted by adjusting the values of the parameters of the resistor R10 or the capacitors C7 and C8. The calculation formula of the delay time is as follows:
Figure BDA0003876323760000031
preferably, the control protection signal output circuit comprises resistors R12 to R16, a capacitor C9, a capacitor C10 and an operational amplifier N5C; one end of a resistor R12 is connected with a 5V reference voltage, the other end of the resistor R12 is respectively connected with one end of a capacitor C9 and an input negative terminal 9 of an operational amplifier N5C, the other end of the capacitor C9 is connected with the ground, one end of a resistor R13 is respectively connected with one end of a resistor R14 and an input positive terminal 10 of the operational amplifier N5C, the other end of the resistor R14 is respectively connected with an output terminal 8 of the operational amplifier N5C and one end of a resistor R15, the other end of the resistor R15 is connected with one end of a resistor R16, two ends of the resistor R16 are in short circuit connection with two ends of the capacitor C10, the other end of the short circuit is connected with the ground, and the point where the resistor R15 is connected with the resistor R16 and the capacitor C10 serves as the output end of a control protection signal output circuit.
The application designs an aviation alternating-current generator hardware overvoltage reverse delay protection circuit which is used as backup protection of generator controller software overvoltage protection, can realize overvoltage reverse delay protection by utilizing a hardware circuit on the premise that software overvoltage protection fails or overvoltage reverse delay exceeding relevant standard regulation cannot effectively trip protection, thereby meeting the requirement that the connection between an aviation alternating-current generator and a bus bar is disconnected by reaching trip protection after the reverse delay time specified by the standard, protecting electric equipment and preventing disaster-level overvoltage failure caused by single-point faults.
Drawings
Fig. 1 is a schematic diagram of a peak sampling circuit of a preferred embodiment of the overvoltage protection circuit for an aircraft alternator according to the present application.
Fig. 2 is a schematic view of a follower circuit of a preferred embodiment of the aero alternator overvoltage protection circuit of the present application.
Fig. 3 is a schematic diagram of an integrating circuit and a control protection signal output circuit of a preferred embodiment of the overvoltage protection circuit for an aeronautical alternator according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides an aviation alternating-current generator overvoltage protection circuit, which mainly comprises a peak value sampling circuit, a following circuit, an integrating circuit and a control protection signal output circuit, and is explained in detail below.
The peak value sampling circuit is used for rectifying the collected three-phase alternating current. Referring to fig. 1, the peak sampling circuit includes resistors R1 to R7, diodes D1 to D3, and capacitors C1 to C2; one end of each of resistors R1, R2 and R3 is connected with the output phase A, the phase B and the phase C of the voltage regulation point of the aviation alternating current power generation system respectively, the other end of each of the resistors R1, R2 and R3 is connected with the anode of each of diodes D1, D2 and D3 respectively, the cathodes of the diodes D1, D2 and D3 are in short-circuit connection, the short-circuit ends are connected with one end of a capacitor C1 and one end of a resistor R4 respectively, the other end of the capacitor C1 is connected with the ground, the other end of the resistor R4 is connected with a resistor R5, one end of the resistor R5 is connected with one end of a resistor R6, the other end of the resistor R6 is connected with one end of a resistor R7 and one end of a capacitor C2 respectively, the other end of the resistor R7 and the other end of the capacitor C2 are connected with the ground, and the electrical point at which the other end of the resistor R6 is connected with one end of the resistor R7 and one end of the capacitor C2 respectively is the output end of the peak sampling circuit 1; the peak value sampling circuit is rectified through resistors R1 to R7 and a capacitor C1, the average value of the rectified voltage is V1, and the V1 is subjected to high-frequency filtering through voltage division of resistors R4, R5, R6 and R7 and a capacitor C2 to form a voltage signal V2 input into the following circuit.
Referring to fig. 1, in the peak sampling circuit,
resistors R1 to R3 and diodes D1 to D3 form a half-wave rectification circuit, the peak values of three-phase voltages of an A phase, a B phase and a C phase are output through a voltage regulation point of a sensitive aviation alternating current power generation system, half-wave rectification is carried out on the voltages (the peak values are UA, UB and UC respectively), a capacitor C1 is a high-frequency filter capacitor, the average value of the rectified voltages is V1, and the V1 is used as an input signal V2 of a following circuit 2 after being subjected to voltage division by R4, R5, R6 and R7 and a C2 high-frequency filter capacitor; v1 and UA, UB and UC satisfy the following formula:
Figure BDA0003876323760000051
v1 and V2 satisfy the following formula:
Figure BDA0003876323760000052
the following circuit is connected behind the peak value sampling circuit and is used for filtering the rectified voltage signal and then forming an output voltage signal V4 which is the same as the input voltage signal.
Referring to fig. 2, the follower circuit includes a resistor R8, a resistor R9, capacitors C3 to C5, and an operational amplifier N5A; one end of a resistor R8 is connected with the output end of the peak value sampling circuit 1, the other end of the resistor R8 is respectively connected with the input positive end of an operational amplifier N5A, one end of a capacitor C3 and one end of a capacitor C4, one end of the capacitor C3 is connected with one end of the capacitor C4 and is connected with the input positive end 3 pin of the operational amplifier N5, the other end of the capacitor C3 is connected with the other end of the capacitor C4 and is connected with one end of a resistor R9, the connection point is the output end of a following circuit 2, the other end of the resistor R9 is connected with the input negative end 2 pin of the operational amplifier N5A, the 4 pins of the operational amplifier N5A are respectively connected with +15VDC and one end of the capacitor C5, the other end of the capacitor C5 is connected with the ground, the 11 pins of the operational amplifier N5A are connected with the ground, and the output voltage V4 of the operational amplifier N5A is the same as the output voltage V2 of the peak value sampling circuit.
In some optional embodiments, the capacitors C3 and C4 are high-frequency filter capacitors, and the capacitor C5 is a decoupling capacitor. In the follower circuit, an output voltage V2 is sent to the positive end of an operational amplifier N5A through a current limiting resistor R8, the voltage of the output end of the operational amplifier N5A is V4, V4= V2, wherein C3 and C4 are high-frequency filter capacitors, C5 is a decoupling capacitor to improve the anti-interference performance of a power supply, and the follower circuit can improve the output load carrying capacity and the anti-interference performance.
The integrating circuit is connected behind the follower circuit and is used for integrating the output voltage signal of the follower circuit, and the time for the output voltage signal V6 of the integrating circuit to be reduced from high to a specified voltage is in a linear relation with the step-up amount of the output voltage signal V4 of the follower circuit.
Referring to fig. 3, the integrating circuit includes a resistor R10, a resistor R11, a capacitor C6, a capacitor C7, a capacitor C8, and an operational amplifier N5B; one end of a resistor R10 is connected with the output end of the follower circuit, the other end of the resistor R10 is connected with one ends of a capacitor C7 and a capacitor C8, two ends of the capacitor C7 and the capacitor C8 are respectively in short circuit, the point where the other end of the resistor R10 is connected with one end of the capacitor C7 and one end of the capacitor C8 is connected with the input negative terminal 6 pin of the operational amplifier N5B, the other end of the capacitor C7 and the other end of the capacitor C8 in short circuit is connected with the output terminal 7 pin of the operational amplifier N5B, the connection point is the output end of the integrating circuit, one end of a resistor R11 is respectively connected with 5V reference voltage and one end of the capacitor C6, the other end of the capacitor C6 is connected with the ground, and the saturated output voltage of the operational amplifier N5B is set to be 13V.
In the integration circuit, referring to fig. 3, the initial voltage at V6 is 13V, if the voltage at V4 or V5 jumps, the voltage at V6 starts to drop, and when the voltage drops to 5V, the subsequent control protection signal output circuit will be triggered, and the time consumed by the drop is approximately linear with the voltage jump at V4 or V5, and the time consumed by the drop is shorter as the jump is larger. The output voltage signal V4 of the specific follower circuit enters an integrating circuit composed of R10, C7, C8, and N5B, and as can be seen from the virtual short and the virtual break of the operational amplifier, the current flowing through R10 = the current flowing through C7 + the current flowing through C8, that is, the current flowing through C8
Figure BDA0003876323760000061
The output voltage V6 of the integrating circuit is
Figure BDA0003876323760000062
When the capacitors C7 and C8 are charged in an approximately constant current mode, the initial voltage of the capacitors C7 and C8 is the saturated output voltage of the operational amplifier N5B, and is 13V, and at the moment, the output voltage V6 of the integrating circuit is approximately linear in time, namely
Figure BDA0003876323760000063
Therefore, the hardware overvoltage protection delay time can be adjusted by adjusting the values of the resistor R10 or the capacitors C7 and C8. The delay time is calculated by the following formula:
Figure BDA0003876323760000064
and the control protection signal output circuit is connected behind the integrating circuit and is used for outputting a low-level signal for controlling the trip protection of the aviation alternating-current generator after the output voltage signal V6 of the integrating circuit is lowered to a specified voltage.
Referring to fig. 3, the control protection signal output circuit includes resistors R12 to R16, a capacitor C9, a capacitor C10, and an operational amplifier N5C; one end of a resistor R12 is connected with a 5V reference voltage, the other end of the resistor R12 is respectively connected with one end of a capacitor C9 and an input negative terminal 9 of an operational amplifier N5C, the other end of the capacitor C9 is connected with the ground, one end of a resistor R13 is respectively connected with one end of a resistor R14 and an input positive terminal 10 of the operational amplifier N5C, the other end of the resistor R14 is respectively connected with an output terminal 8 of the operational amplifier N5C and one end of a resistor R15, the other end of the resistor R15 is connected with one end of a resistor R16, two ends of the resistor R16 are in short circuit connection with two ends of the capacitor C10, the other end of the short circuit is connected with the ground, and the point where the resistor R15 is connected with the resistor R16 and the capacitor C10 serves as the output end of a control protection signal output circuit.
In the control protection signal output circuit, a voltage signal V6 output by an integrating circuit passes through a hysteresis comparator consisting of an operational amplifier N5C, resistors R12 to R16, a capacitor C9, a capacitor C10 and reference voltage, a control protection signal V8 is output, and the final overvoltage control protection signal is output after the voltage of the V8 is divided by resistors R15 and R16 and filtered by the C10.
For example, when the output voltage of the aviation alternator is over-voltage, assuming that the input voltage effective value is changed from 115V to 162V, the over-voltage protection process is as follows:
when the output of the alternator is normal, V1=0.827u =134.5V is output after passing through the half-wave rectification circuit, the rectified voltage is divided by R4, R5, R6, and R7, and the forward input voltage of the operational amplifier N5 is obtained
Figure BDA0003876323760000071
When the output of the alternator is overvoltage, the output V1=0.827u =190v after passing through the half-wave rectification circuit, the rectified voltage is divided by R4, R5, R6, and R7, and the forward input voltage of the operational amplifier N5 is obtained as:
Figure BDA0003876323760000072
in summary, V3 is a voltage signal that steps from 3.75V to 5.30V.
The output signal V4 of the follower circuit enters an integrating circuit composed of R10, C7, C8 and N5B, and the output voltage V6 of the integrating circuit is approximately linear in relation to time, namely
Figure BDA0003876323760000073
Substituting V6=5V, V4=5.30V, V6| t1=13V, VREF1_ +5v =5v, and the resistance and capacitance parameters, the delay time Δ t =250.4ms is obtained. Therefore, after the time delay of 250.4ms, the voltage V6 is reduced to 5V, and then the output voltage VAC _ Hard-OV of the operational amplifier N5C of the protection signal output circuit is controlled to change from high level to low level by controlling the protection signal output circuit, so as to trigger the pull-off protection. In conclusion, the requirement of an overvoltage reverse delay curve in the GJB 181B-2012 aircraft power supply characteristic is met.
Although the present application has been described in detail with respect to the general description and specific embodiments, it will be apparent to those skilled in the art that certain modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.

Claims (8)

1. An aircraft alternator overvoltage protection circuit, comprising:
the peak value sampling circuit is used for rectifying the collected three-phase alternating current;
the following circuit is connected behind the peak value sampling circuit and is used for filtering the rectified voltage signal to form an output voltage signal V4 which is the same as the input voltage signal;
the integration circuit is connected behind the follower circuit and is used for integrating the output voltage signal of the follower circuit, and the time for the output voltage signal V6 of the integration circuit to be reduced from high to a specified voltage is in a linear relation with the jump amount of the output voltage signal V4 of the follower circuit;
and the control protection signal output circuit is connected behind the integrating circuit and used for outputting a low-level signal for controlling the trip protection of the aviation alternating-current generator after the output voltage signal V6 of the integrating circuit is lowered to a specified voltage.
2. The aircraft alternator overvoltage protection circuit of claim 1, wherein said peak sampling circuit comprises resistors R1 through R7, diodes D1 through D3, capacitors C1 through C2; one end of each of resistors R1, R2 and R3 is connected with an A phase, a B phase and a C phase of the voltage regulation point output of the aviation alternating current power generation system respectively, the other end of each of resistors R1, R2 and R3 is connected with the anode of each of diodes D1, D2 and D3 respectively, the cathodes of the diodes D1, D2 and D3 are connected in a short circuit mode, the short-circuit ends are connected with one end of a capacitor C1 and one end of a resistor R4 respectively, the other end of the capacitor C1 is connected with the ground, the other end of the resistor R4 is connected with a resistor R5, one end of the resistor R5 is connected with one end of a resistor R6, the other end of the resistor R6 is connected with one end of a resistor R7 and one end of a capacitor C2 respectively, the other end of the resistor R7 and the other end of the capacitor C2 are connected with the ground, and the other end of the resistor R6 is connected with an electrical point of one end of the resistor R7 and one end of the capacitor C2 respectively, which is the output end of the peak sampling circuit 1;
the peak value sampling circuit is rectified through resistors R1 to R7 and a capacitor C1, the average value of the rectified voltage is V1, and the V1 is subjected to high-frequency filtering through voltage division of resistors R4, R5, R6 and R7 and a capacitor C2 to form a voltage signal V2 input into the following circuit.
3. The aircraft alternator overvoltage protection circuit as claimed in claim 2, wherein in said peak sampling circuit, said resistors R1 to R7, capacitor C1 are configured such that the input three phase voltage U is A 、U B 、U C The relationship with the rectified voltage average value V1 is:
Figure FDA0003876323750000011
4. the aircraft alternator overvoltage protection circuit as claimed in claim 1, wherein said follower circuit comprises resistor R8, resistor R9, capacitors C3 to C5, and operational amplifier N5A; one end of a resistor R8 is connected with the output end of the peak value sampling circuit 1, the other end of the resistor R8 is respectively connected with an input positive end of an operational amplifier N5A, one end of a capacitor C3 and one end of a capacitor C4, one end of the capacitor C3 is connected with one end of the capacitor C4 and is connected with a pin 3 of the input positive end of the operational amplifier N5, the other end of the capacitor C3 is connected with the other end of the capacitor C4 and is connected with one end of a resistor R9, the connection point is the output end of a following circuit 2, the other end of the resistor R9 is connected with a pin 2 of the input negative end of the operational amplifier N5A, a pin 4 of the operational amplifier N5A is respectively connected with +15VDC and one end of the capacitor C5, the other end of the capacitor C5 is connected with the ground, a pin 11 of the operational amplifier N5A is connected with the ground, and the output voltage V4 of the operational amplifier N5A is the same as the output voltage V2 of the peak value sampling circuit.
5. The aircraft alternator overvoltage protection circuit as claimed in claim 4, wherein said capacitors C3 and C4 are high frequency filter capacitors and said capacitor C5 is a decoupling capacitor.
6. The aircraft alternator overvoltage protection circuit of claim 1, wherein said integration circuit comprises a resistor R10, a resistor R11, a capacitor C6, a capacitor C7, a capacitor C8, and an operational amplifier N5B; one end of a resistor R10 is connected with the output end of the follower circuit, the other end of the resistor R10 is connected with one ends of a capacitor C7 and a capacitor C8, two ends of the capacitor C7 and the capacitor C8 are in short circuit respectively, the point where the other end of the resistor R10 is connected with one end of the capacitor C7 and one end of the capacitor C8 is connected with the input negative terminal 6 pin of the operational amplifier N5B, the other short circuit end of the capacitor C7 and the other short circuit end of the capacitor C8 are connected with the output end 7 pin of the operational amplifier N5B, the connection point is the output end of the integrating circuit, one end of a resistor R11 is connected with a 5V reference voltage and one end of the capacitor C6 respectively, the other end of the capacitor C6 is connected with the ground, and the saturated output voltage of the operational amplifier N5B is set to be 13V.
7. The aircraft alternator overvoltage protection circuit as in claim 6, wherein hardware overvoltage protection delay time is adjustable by adjusting values of resistor R10 or capacitors C7 and C8 parameters. The calculation formula of the delay time is as follows:
Figure FDA0003876323750000021
8. the aircraft alternator overvoltage protection circuit according to claim 1, wherein said control protection signal output circuit includes resistors R12 to R16, a capacitor C9, a capacitor C10, and an operational amplifier N5C; one end of a resistor R12 is connected with a 5V reference voltage, the other end of the resistor R12 is respectively connected with one end of a capacitor C9 and an input negative terminal 9 of an operational amplifier N5C, the other end of the capacitor C9 is connected with the ground, one end of a resistor R13 is respectively connected with one end of a resistor R14 and an input positive terminal 10 of the operational amplifier N5C, the other end of the resistor R14 is respectively connected with an output terminal 8 of the operational amplifier N5C and one end of a resistor R15, the other end of the resistor R15 is connected with one end of a resistor R16, two ends of the resistor R16 are in short circuit connection with two ends of the capacitor C10, the other end of the short circuit is connected with the ground, and the point where the resistor R15 is connected with the resistor R16 and the capacitor C10 serves as the output end of a control protection signal output circuit.
CN202211216450.5A 2022-09-30 2022-09-30 Overvoltage protection circuit of aviation alternating-current generator Pending CN115513901A (en)

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CN202211216450.5A CN115513901A (en) 2022-09-30 2022-09-30 Overvoltage protection circuit of aviation alternating-current generator

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Application Number Priority Date Filing Date Title
CN202211216450.5A CN115513901A (en) 2022-09-30 2022-09-30 Overvoltage protection circuit of aviation alternating-current generator

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CN115513901A true CN115513901A (en) 2022-12-23

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