CN215120272U - Protection device suitable for navigation double-engine aircraft power supply system - Google Patents

Protection device suitable for navigation double-engine aircraft power supply system Download PDF

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Publication number
CN215120272U
CN215120272U CN202120898473.3U CN202120898473U CN215120272U CN 215120272 U CN215120272 U CN 215120272U CN 202120898473 U CN202120898473 U CN 202120898473U CN 215120272 U CN215120272 U CN 215120272U
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relay
generator
bus bar
power supply
contact
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CN202120898473.3U
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孙樵
邹瑜光
邓静
贾峰
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Jc General Aircraft Design Manufacturing Dalian Co ltd
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Jc General Aircraft Design Manufacturing Dalian Co ltd
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Abstract

The utility model discloses a protection device suitable for a power supply system of a navigation double-engine airplane, which comprises a left starting generator and a right starting generator; the B contact of the left starting generator is connected to a left generator bus bar through a lower contact of a left generator relay, and the left generator bus bar is connected with an important load bus bar; the B contact of the right starting generator is connected to a right generator bus bar through a lower contact of a right generator relay, and the right generator bus bar is connected with an important load bus bar; the important load bus bar is connected with the storage battery through a storage battery relay. The method and the device have the advantages that the airplane power supply system is controlled by the relay switch amount to be simple to realize, high-intensity radiation field protection and indirect lightning effect protection verification are not needed, and airplane cost is saved while reliability of the airplane power supply system is improved.

Description

Protection device suitable for navigation double-engine aircraft power supply system
Technical Field
The utility model relates to an aircraft power supply control field, concretely relates to protection device suitable for two aircraft electrical power generating system of navigation.
Background
Usually, two engines of a navigable dual-generation aircraft are each equipped with a generator (starter generator), and the two generators are connected in parallel to supply power to an aircraft power grid. With the current development of the airplane towards full electricity and multiple electricity, the power supply system plays an increasingly important role in airplane safety, and the airplane power supply system needs to be reasonably controlled and protected, so that the airplane power supply system is safer and more reliable.
In the prior art, the control and protection of a power supply system of a navigation double-engine airplane are mainly realized by the following two schemes:
scheme one (low match): the parallelly connected distribution form of two generations, left and right generator busbar pass through current limiter, silicon controlled rectifier and circuit breaker protection and supply power to the double-fed busbar respectively, if: air king 200 plane; the disadvantages are that: no automatic load shedding and manual one-key load shedding function; when the two generators both fail, if the pilot does not timely perceive the failure at the moment, under the condition that a high-power electricity load (such as electric deicing) works, the storage battery serving as an emergency power supply is quickly exhausted, and the load necessary for the safe operation of the airplane cannot be ensured to have enough power supply time when the double generators fail; even if the pilot timely perceives that the double generators fail, the pilot needs to close unnecessary loads one by one according to the flight working condition to manually reduce the loads because the design has no automatic load reducing function, and the workload of the unit is increased.
Scheme two (high-ratio): the bus bars of the left generator and the right generator realize the power grid control protection of the airplane through a bus bar controller with a microprocessor; the disadvantages are that: because the microprocessor is a sensitive device for electromagnetic radiation and indirect lightning influence, the bus bar controller adopting the microprocessor realizes that the control power supply system equipment can be installed and used only by carrying out high-intensity radiation field protection and indirect lightning effect protection verification, thereby increasing the cost of the airplane.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems, the application provides a protection device suitable for a navigation double-engine aircraft power supply system, which realizes automatic load shedding of an electrical load when the power supply system fails, and improves the safety of the aircraft power supply system on the premise of not obviously increasing the aircraft cost.
In order to achieve the purpose, the technical scheme of the application is as follows: a protection device suitable for a power supply system of a navigation double-generator aircraft comprises a left starting generator and a right starting generator; the B contact of the left starting generator is connected to a left generator bus bar through a lower contact of a left generator relay, and the left generator bus bar is connected with an important load bus bar; the B contact of the right starting generator is connected to a right generator bus bar through a lower contact of a right generator relay, and the right generator bus bar is connected with an important load bus bar; the important load bus bar is connected with the storage battery through a storage battery relay.
Further, the left generator bus bar is connected with the lower contact of the relay through the left bus bar, and the left current direction sensor is connected to one end of the middle bus bar; the right generator bus bar is connected with a lower contact of the relay through the right bus bar, the right current direction sensor is connected to the other end of the middle bus bar, the right current direction sensor and the middle bus bar are connected with an external power socket through an external power relay, the right current direction sensor, the middle bus bar and the external power relay are divided into two paths to be connected with the electrified storage battery bus bar, one path is provided with a rectifier diode a, the other path is provided with a storage battery connecting relay and a rectifier diode b, one end of an upper contact of the storage battery connecting relay is respectively connected with an upper contact of the left bus connecting relay and an upper contact of the right bus connecting relay, and the other end of the upper contact of the storage battery connecting relay is connected with a storage battery disconnection indicating lamp; the lower contact of the storage battery connecting relay is connected with the storage battery through a current direction sensor; the upper contact of the left confluence connecting relay is connected with a left generator connection control disconnection indicating lamp, and the upper contact of the right confluence connecting relay is connected with a right generator connection control disconnection indicating lamp.
Further, left side generator busbar, right generator busbar, important load busbar all are connected to the power supply busbar through circuit breaker, rectifier diode, the power supply busbar passes through rectifier diode and links to each other with external power socket, the power supply busbar still is connected with two fault indication branches respectively, and one of them branch road is through the last contact of left junction connection relay, the well contact of left generator relay links to each other with left generator fault indication lamp, and another branch road is through the last contact of right junction connection relay, the well contact of right generator relay links to each other with right generator fault indication lamp, the last contact of left junction connection relay with the last contact of right junction connection relay links to each other.
Further, the left generator relay is also connected with a left generator controller, the left generator controller is connected to a right generator controller through lower contacts of a relay K10, a relay K11 and a relay K12 in sequence, and the right generator controller is connected with a right generator relay; the middle contact of the left generator relay is further connected to a relay K11, the middle contact of the right generator relay is further connected to a relay K12, and the upper contact of the left bus connection relay and the upper contact of the right bus connection relay are connected to a relay K10 through rectifier diodes respectively.
Further, the middle contact of the left generator relay is further connected to a relay K4, the middle contact of the right generator relay is further connected to a relay K5, the relay K4 and the relay K5 are connected with a power supply bus bar through rectifier diodes and circuit breakers, the relay K4 and the relay K5 are further connected to a relay K14 through rectifier diodes, and the relay K14 is connected with an external power socket.
Furthermore, the relay K4 and the relay K5 are also connected to the relay K14 through a lower contact of the relay K13 and a rectifier diode; the power supply bus bar is connected to the relay K13 through a circuit breaker and a two-way switch.
Furthermore, the storage battery connecting relay is also connected with one end of an upper contact of the relay K3, and the other end of the upper contact of the relay K3 is connected to the middle bus bar through a storage battery switch, a rectifier diode, a current direction sensor, a lower contact of the storage battery connecting relay and a right current direction sensor in sequence.
Furthermore, the two-way switch is connected to an upper contact of a relay K17 through a left bus bar connecting relay, and an upper contact of the relay K17, the relay K4 and the relay K5 are converged and then sequentially connected back to the relay K17 body through upper contacts of a relay K14 and a relay K16; the relay K4 and the relay K5 are also connected to a bus bar connection indicator lamp through lower contacts of a relay K13 and a relay K17; the left current direction sensor is connected to the landing gear control relay K2 via relay K16.
As a further step, the two-way switch is connected to the lower contact of the relay K3 through the upper contact of the right bus bar connecting relay and the relay K8, the power supply bus bar is also connected to the lower contact of the relay K3 through the breaker, the rectifier diode, the relay K4 and the relay K5 in sequence, and the lower contact of the relay K3 is connected to the bus bar connecting indicator light through the lower contact of the relay K8; the power supply bus bar is also connected to the right current direction sensor sequentially through the circuit breaker, the upper contact of the reset switch, the relay K15, the lower contact of the relay K6 and the relay K17.
As a further step, the charged battery bus bar is connected to the battery relay through a current direction sensor, a rectifier diode, and a battery switch; the battery is connected to the vital load bus bar through the upper contact of the battery relay.
As a further step, the deicing system further comprises a left deicing power supply relay and a right deicing power supply relay, wherein the lower contacts of the left deicing power supply relay and the right deicing power supply relay are connected to deicing bus bars, and the deicing bus bars are respectively connected between corresponding heating resistors through the left deicing control relay and the right deicing control relay; the left deicing control relay is connected with an upper contact of the left deicing power supply relay, the right deicing control relay is connected with an upper contact of the right deicing power supply relay, and the left deicing power supply relay is connected with an upper contact of the left generator relay; and the right deicing power supply relay is connected with the upper contact of the right generator relay.
The utility model discloses owing to adopt above technical scheme, can gain following technological effect: according to the power supply system, when a single generator fails, another generator continuously supplies power to the load of the middle bus bar through the relay; when the double generators fail, only the storage battery supplies power to the important load bus bar to realize load shedding; the airplane power supply system controlled by the relay switch is simple to realize, high-intensity radiation field protection and indirect lightning effect protection verification are not needed, reliability of the airplane power supply system is improved, and airplane cost is saved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the technical solutions of the embodiments will be briefly described below.
Fig. 1 is a schematic diagram of a protection device suitable for a power supply system of a navigable dual-generation aircraft.
Detailed Description
The invention will be described in further detail with reference to the following figures and specific embodiments: the present application is further described by taking this as an example.
Example 1
The technical solutions in the embodiments of the present invention will be described clearly and completely below with reference to the drawings in the embodiments of the present invention, so that the objects, technical solutions and advantages of the embodiments of the present invention are more clear, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without any creative work belong to the protection scope of the present invention.
As shown in fig. 1, a protection device suitable for a power supply system of a navigable dual-engine aircraft comprises:
in order to ensure that the batteries of the left and right generators normally supply power, the B contact of the left starting generator is connected to the left generator bus bar through the lower contact of the left generator relay; and the B contact of the right starting generator is connected to the right generator bus bar through the lower contact of the right generator relay.
In order to ensure that the important load bus bar is normally powered, the left generator bus bar is connected with the important load bus bar, and the right generator bus bar is connected with the important load bus bar; the important load bus bar is connected with the storage battery through a storage battery relay.
In order to realize power supply of an external power supply, the left generator bus bar is connected with the lower contact of the relay through the left bus bar, and the left current direction sensor is connected to one end of the middle bus bar; the right side generator bus bar is connected with the lower contact of the relay through the right bus bar, the right current direction sensor is connected to the other end of the middle bus bar, the right current direction sensor and the middle bus bar are connected with an external power socket through an external power relay, the right current direction sensor, the middle bus bar and the external power relay are connected with the electrified storage battery bus bar through the lower contact of the storage battery connection relay and a rectifier diode b, and the storage battery connection relay is connected with the important load bus bar through the current direction sensor.
For realizing the power supply of the middle bus bar, one end of the middle bus bar is connected with the left generator bus bar through the left current direction sensor and the left bus bar connecting relay, the other end of the middle bus bar is connected with the right generator bus bar through the right current direction sensor and the right bus bar connecting relay, and the right current direction sensor is connected with the storage battery through the storage battery connecting relay and the current direction sensor.
The four types are basic power supply forms, and under the normal condition, the left starting generator supplies power to the left generator bus bar through the left generator relay; the power supply mode of the right starting generator is consistent with that of the left starting generator; in an emergency situation, the storage battery supplies power to the important load bus bar and the electrified storage battery bus bar; when ground maintenance is carried out, an external power supply supplies power to all the electric equipment on the machine; when the engine is started, the starter is powered by a ground external power supply or a storage battery.
The load of the important load bus bar is the load necessary for the safe operation of the airplane, and can be directly supplied with power by the redundancy of the storage battery, the left generator and the right generator; the loads of the middle bus bar are unnecessary loads for safe operation of the airplane, and can be respectively supplied with power by the storage battery, the left generator and the right generator under the condition that the storage battery connecting relay, the left bus bar connecting relay and the right bus bar connecting relay are closed; the live battery bus bar supplies power to a load that needs to be supplied with power when the battery switch is off.
When the left generator relay is disconnected, the coil of the left generator relay is disconnected, so that the left generator fault indicator lamp is turned on; when the right generator relay is disconnected, the coil of the right generator relay is disconnected, so that the right generator fault indicating lamp is turned on.
In order to realize the power supply of the electrified storage battery bus bar, the electrified storage battery bus bar is connected with the storage battery through a rectifier diode and a current direction sensor.
In order to enable the corresponding indicator light to be turned on when the left generator fails or the right generator fails, the power supply bus bar is respectively connected with two fault indication branches, one branch is connected with the left generator fault indicator light through the upper contact of the left confluence connection relay and the middle contact of the left generator relay, the other branch is connected with the right generator fault indicator light through the upper contact of the right confluence connection relay and the middle contact of the right generator relay, and the upper contact of the left confluence connection relay is connected with the upper contact of the right confluence connection relay.
The intermediate bus bar connection control strategy comprises the following three points:
1) and (3) voltage regulation balance control of the left generator and the right generator: when the left bus bar connecting relay and the right bus bar connecting relay are both attracted, the K10 relay is not attracted at the moment, and the left generator relay and the right generator relay are both attracted, so that the K11 relay and the K12 relay are both attracted, the balanced voltage regulating interfaces of the left generator controller and the right generator controller are communicated, and the voltage of a power supply system is balanced when the left generator and the right generator generate electricity simultaneously. Therefore, the left generator controller is connected to the right generator controller through the lower contacts of the relay K10, the relay K11 and the relay K12 in sequence. In order to realize the control of the relay K10, the power supply bus bar is connected to the relay K10 through two branches, wherein one branch is an upper contact and a rectifier diode of the left bus connection relay; the other branch circuit is an upper contact of the right bus connection relay and a rectifier diode. In order to realize the control of the relay K11 and the relay K12, the power supply bus bar is connected to the upper contact of the relay through the left bus bar, the middle contact of the left generator relay is also connected to the relay K11, and the power supply bus bar is connected to the upper contact of the relay through the right bus bar, and the middle contact of the right generator relay is also connected to the relay K12.
2) Reverse flow protection of the left and right generators: when the left generator controller and the right generator controller detect reverse current, the reverse current protection interface of the generator controller disconnects the left generator relay and the right generator relay, and reverse current protection of the generator is achieved. Therefore, the left generator relay is respectively connected with the B contact of the left starting generator and the left generator controller, and the right generator controller is respectively connected with the B contact of the right starting generator and the right generator relay.
3) Power supply conditions for bus bar connection control: the middle bus bar adopts three-redundancy power supply for connection control, namely, power supply of a left generator and power supply of a right generator; the external power supply supplies power; the storage battery supplies power; therefore, the B contact of the left starting generator is connected to the power supply bus bar sequentially through the left generator relay, the left generator bus bar, the circuit breaker and the rectifier diode, and the B contact of the right starting generator is connected to the power supply bus bar sequentially through the right generator relay, the right generator bus bar, the circuit breaker and the rectifier diode; the power supply bus bar is connected with an external power socket through a rectifier diode; the storage battery is connected to a vital load bus bar through a storage battery relay, and the vital load bus bar is connected to a power supply bus bar through a circuit breaker and a rectifier diode.
The relay K14 can be attracted to supply power to the corresponding circuit after meeting one of the following 3 conditions:
(1) when one of the left generator relay and the right generator relay is attracted, the corresponding K4 or K5 relay is attracted; therefore, the power supply bus bar is connected with the upper contact of the relay through the left bus bar, the middle contact of the left generator relay is connected with the relay K4, the power supply bus bar is connected with the upper contact of the relay through the right bus bar, the middle contact of the right generator relay is connected with the relay K5, and the relay K4 and the relay K5 are connected back to the power supply bus bar through the rectifier diode and the breaker; the relay K4 and the relay K5 are also connected to the relay K14 through rectifier diodes.
(2) Or when the external power supply is connected, the external power supply supplies power; therefore, the relay K14 is connected with an external power socket.
(3) When the power supply bus bar connection two-way switch is opened, the K13 relay is closed. Therefore, the power supply bus bar is connected to the relay K14 through a rectifier diode, the relay K4, the relay K5, the lower contact of the relay K13 and the other rectifier diode; the power supply bus bar is connected to the relay K13 through a circuit breaker and a two-way switch.
In order to realize the indication of the bus bar connection state, namely when the left bus bar connection relay is disconnected, the left bus bar connection relay is disconnected through a coil, so that an amber indicating lamp for 'left generator connection open circuit' is lightened, and a unit left generator is prompted not to be connected with the middle bus bar; when the right bus bar connection relay is disconnected, the through coil of the right bus bar connection relay is disconnected, so that the amber indicator lamp for connecting the right generator to be open-circuited is lightened, and the middle bus bar is not accessed by the right generator of the unit. Therefore, the power supply bus bar is connected with the left generator connection control disconnection indicating lamp through the upper contact of the left bus connection relay, and the power supply bus bar is connected with the right generator connection control disconnection indicating lamp through the upper contact of the right bus connection relay.
When the left engine and the right engine are not in a starting state, the contacts of the K15 relay and the K6 relay are not attracted, and under the condition, the following 4 bus bars are connected with control logic:
(1) when the undercarriage acts, the storage battery is always connected with the relay, so that the power supply reliability of the undercarriage is improved. The battery connection relay is also connected with one end of an upper contact of the relay K3, and the other end of the upper contact of the relay K3 is connected to the middle bus bar through a battery switch, a rectifier diode, a current direction sensor, a lower contact of the battery connection relay and a right current direction sensor in sequence.
(2) As long as the reverse flow does not occur in the left current direction sensor, the relay K16 is not attracted, at the moment, the relay K14 attracts the relay K17, the relay K17 attracts the left bus bar connecting relay, so that the left generator is connected to the middle bus bar, and the relay K17 lights the bus bar connecting indicator lamp to indicate that the bus bar connection is in a working state; this allows the left generator to be disconnected from the intermediate bus bar when the left generator fails, and the right generator continues to supply power to the intermediate bus bar. Therefore, the two-way switch is connected to the upper contact of the relay K17 through the left bus bar connecting relay, and the upper contact of the relay K17 is converged with the relay K4 and the relay K5 and then is connected back to the relay K17 body through the upper contacts of the relay K14 and the relay K16 in sequence; the relay K4 and the relay K5 are also connected to a bus bar connection indicator lamp through lower contacts of a relay K13 and a relay K17; the left current direction sensor is connected to the landing gear control relay K2 via relay K16. The B contact of the left starting generator is connected to one end of the middle bus bar through a lower contact of the left generator relay, the left generator bus bar, the left bus bar connecting relay and the left current direction sensor.
(3) As long as the right current direction sensor does not generate reverse flow, the K7 relay does not attract, the K14 relay attracts the K8 relay, the K8 relay attracts the right bus bar connecting relay, so that the right generator is connected with the middle bus bar, and the K8 relay lights the bus bar connecting indicator lamp to indicate that the bus bar connection is in a working state; therefore, when the right generator fails, the right generator is disconnected from the middle bus bar, and the left generator continuously supplies power to the middle bus bar. Therefore, the two-way switch is connected with the upper contact of the relay K8 through the right bus bar, the upper contact of the relay K8 is connected with the lower contact of the relay K3, the power supply bus bar is also connected with the lower contact of the relay K3 through the breaker, the rectifier diode, the relay K4 and the relay K5 in sequence, and the lower contact of the relay K3 is connected with the bus bar connection indicator lamp through the lower contact of the relay K8; the power supply bus bar is also connected to the right current direction sensor sequentially through the circuit breaker, the upper contact of the reset switch, the relay K15, the lower contact of the relay K6 and the relay K17. The B contact of the right starting generator is connected to the other end of the middle bus bar through a lower contact of the right generator relay, the right generator bus bar, the right bus bar connecting relay and the right current direction sensor.
(4) When both generators fail, only the critical load bus bar and the live battery bus bar are powered by the battery. Therefore, the electrified storage battery bus bar is connected to the storage battery relay through the current direction sensor, the rectifier diode and the storage battery switch; the battery is connected to the vital load bus bar through the upper contact of the battery relay. The B contact of the left starting generator is connected with the lower contact of the left generator relay; the B contact of the right starting generator is connected with the lower contact of the right generator relay.
Control logic of the electrical de-icing busbar: and the working state of the deicing bus bar is controlled by contacts on the left generator relay and the right generator relay. When the left generator and the right generator work normally, power is supplied to the deicing bus bar, and the electric deicing equipment can work at high and low gear heating; when only one of the left generator and the right generator works, the power is supplied to the deicing bus bar, but the electric deicing equipment only works at a low gear by considering that only one generator works and the load power needs to be limited; when the left generator and the right generator are invalid, the power supply of the electric deicing equipment is automatically cut off, and the danger of electric quantity exhaustion of the storage battery is avoided. Therefore, the lower contacts of the left deicing power supply relay and the right deicing power supply relay are connected to deicing bus bars, and the deicing bus bars are connected between corresponding heating resistors through the left deicing control relay and the right deicing control relay respectively; the left deicing control relay is connected with an upper contact of the left deicing power supply relay, the right deicing control relay is connected with an upper contact of the right deicing power supply relay, and the left deicing power supply relay is connected with an upper contact of the left generator relay; and the right deicing power supply relay is connected with the upper contact of the right generator relay.
The above-mentioned devices are explained functionally:
the left and right generator controllers have the functions of controlling generator excitation, overload protection, reverse flow protection, overvoltage protection, undervoltage protection and the like;
starting the generator from left to right: the motor mode is used for starting an aircraft engine, and after the engine is started, the engine is switched to the generator mode to supply power to a load;
k10 Relay: the left generator controller and the right generator controller are connected to play a role in balancing the voltage of the left generator and the voltage of the right generator;
each connection relay: connecting a left generator, a right generator and a storage battery into the middle bus bar;
when the current flowing through the current direction sensor is in the direction of the arrow in the figure 1, the signal end provided by the sensor is grounded;
left and right generator relays: controlling the generators to access the corresponding generator bus bars;
important load bus bar: the load of this bus bar is the load necessary for the safe operation of the aircraft;
an intermediate bus bar: the load of the bus bar is unnecessary for the safe operation of the airplane;
electrical de-icing bus bar: the load of this busbar is a powerful electrical deicing device.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the above embodiments, it should be understood by those skilled in the art that: the technical solutions described in the embodiments above can be modified or some technical features can be equivalently replaced, and the modifications or the replacements do not enable the corresponding technical solutions to exceed the scope of the technical solutions of the embodiments of the present invention.

Claims (10)

1. A protection device suitable for a power supply system of a navigation double-generator aircraft is characterized by comprising a left starting generator and a right starting generator; the B contact of the left starting generator is connected to a left generator bus bar through a lower contact of a left generator relay, and the left generator bus bar is connected with an important load bus bar; the B contact of the right starting generator is connected to a right generator bus bar through a lower contact of a right generator relay, and the right generator bus bar is connected with an important load bus bar; the important load bus bar is connected with the storage battery through a storage battery relay.
2. The protection device for the power supply system of the navigable dual-generation aircraft according to claim 1, wherein the left generator bus bar is connected to one end of the middle bus bar through a left bus bar connecting relay lower contact and a left current direction sensor; the right generator bus bar is connected with a lower contact of the relay through the right bus bar, the right current direction sensor is connected to the other end of the middle bus bar, the right current direction sensor and the middle bus bar are connected with an external power socket through an external power relay, the right current direction sensor, the middle bus bar and the external power relay are divided into two paths to be connected with the electrified storage battery bus bar, one path is provided with a rectifier diode a, the other path is provided with a storage battery connecting relay and a rectifier diode b, one end of an upper contact of the storage battery connecting relay is respectively connected with an upper contact of the left bus connecting relay and an upper contact of the right bus connecting relay, and the other end of the upper contact of the storage battery connecting relay is connected with a storage battery disconnection indicating lamp; the lower contact of the storage battery connecting relay is connected with the storage battery through a current direction sensor; the upper contact of the left confluence connecting relay is connected with a left generator connection control disconnection indicating lamp, and the upper contact of the right confluence connecting relay is connected with a right generator connection control disconnection indicating lamp;
the electrified storage battery bus bar is connected to the storage battery relay through the current direction sensor, the rectifier diode and the storage battery switch; the battery is connected to the vital load bus bar through the upper contact of the battery relay.
3. The protection device for the power system of the navigable dual-generation aircraft according to claim 1, wherein the left generator bus bar, the right generator bus bar and the important load bus bar are all connected to the power supply bus bar through a circuit breaker and a rectifier diode, the power supply bus bar is connected to an external power socket through the rectifier diode, the power supply bus bar is further connected with two fault indication branches, one branch is connected to the left generator fault indication lamp through an upper contact of the left bus connection relay and a middle contact of the left generator relay, the other branch is connected to the right generator fault indication lamp through an upper contact of the right bus connection relay and a middle contact of the right generator relay, and an upper contact of the left bus connection relay is connected to an upper contact of the right bus connection relay.
4. The protection device suitable for the power system of the navigable dual-generator aircraft as defined in claim 2, wherein the left generator relay is further connected with a left generator controller, the left generator controller is connected with a right generator controller through the lower contacts of a relay K10, a relay K11 and a relay K12 in sequence, and the right generator controller is connected with a right generator relay; the middle contact of the left generator relay is further connected to a relay K11, the middle contact of the right generator relay is further connected to a relay K12, and the upper contact of the left bus connection relay and the upper contact of the right bus connection relay are connected to a relay K10 through rectifier diodes respectively.
5. The protection device suitable for the power system of the navigable dual-generator aircraft as defined in claim 1, wherein the middle contact of the left generator relay is further connected to a relay K4, the middle contact of the right generator relay is further connected to a relay K5, the relay K4 and the relay K5 are connected to the power supply bus bar through rectifier diodes and circuit breakers, the relay K4 and the relay K5 are further connected to a relay K14 through rectifier diodes, and the relay K14 is connected to an external power socket.
6. The protection device suitable for the power supply system of the navigable dual-engine aircraft according to claim 5, characterized in that the relay K4 and the relay K5 are further connected to a relay K14 through a lower contact of a relay K13 and a rectifier diode; the power supply bus bar is connected to the relay K13 through a circuit breaker and a two-way switch.
7. The protection device for the power supply system of the navigable dual-aircraft as defined in claim 2, wherein the battery connection relay is further connected with one end of an upper contact of a relay K3, and the other end of the upper contact of the relay K3 is connected to the intermediate bus bar through a battery switch, a rectifier diode, a current direction sensor, a lower contact of the battery connection relay, and a right current direction sensor in sequence.
8. The protection device suitable for the power supply system of the navigable dual-engine aircraft as claimed in claim 6, wherein the two-way switch is connected to the upper contact of the relay K17 through a left bus bar connecting relay, the upper contact of the relay K17 is connected to the body of the relay K17 after being merged with the relay K4 and the relay K5 and then sequentially connected back to the body of the relay K14 and the upper contact of the relay K16; the relay K4 and the relay K5 are also connected to a bus bar connection indicator lamp through lower contacts of a relay K13 and a relay K17; the left current direction sensor is connected to the landing gear control relay K2 via relay K16.
9. The protection device suitable for the power supply system of the navigable dual-engine aircraft as defined in claim 6, wherein the two-way switch is connected to the lower contact of the relay K3 through a right bus bar connecting relay, the upper contact of the relay K8, the power supply bus bar is also connected to the lower contact of the relay K3 through a breaker, a rectifier diode, the relay K4 and the relay K5 in turn, and the lower contact of the relay K3 is connected to a bus bar connecting indicator lamp through the lower contact of the relay K8; the power supply bus bar is also connected to the right current direction sensor sequentially through the circuit breaker, the upper contact of the reset switch, the relay K15, the lower contact of the relay K6 and the relay K17.
10. The protection device suitable for the power supply system of the navigable dual-generation aircraft according to claim 1, further comprising a left deicing power supply relay and a right deicing power supply relay, wherein the lower contacts of the left deicing power supply relay and the right deicing power supply relay are both connected to deicing busbars which are respectively connected between corresponding heating resistors through the left deicing control relay and the right deicing control relay; the left deicing control relay is connected with an upper contact of the left deicing power supply relay, the right deicing control relay is connected with an upper contact of the right deicing power supply relay, and the left deicing power supply relay is connected with an upper contact of the left generator relay; and the right deicing power supply relay is connected with the upper contact of the right generator relay.
CN202120898473.3U 2021-04-28 2021-04-28 Protection device suitable for navigation double-engine aircraft power supply system Active CN215120272U (en)

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