Aircraft generator power supply system and aircraft

Abstract

The utility model relates to the technical field of aircraft power supply, and provides an aircraft generator power supply system and an aircraft, the aircraft generator power supply system comprises a generator, a voltage regulator and a transformer, the generator is provided with a rotor, and the rotor is used for connecting an aircraft engine; the voltage regulator is electrically connected with the rotor and is used for supplying power to the rotor, so that the generator outputs first power supply voltage to first electric equipment; the transformer is electrically connected with the generator and used for converting the first power supply voltage into second power supply voltage and outputting the second power supply voltage to the second electric equipment. According to the utility model, the multi-voltage-level power supply capability can be realized, so that more types of airborne equipment can be supported, and the diversity of the airborne equipment is enriched.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft power supply, in particular to an aircraft generator power supply system and an aircraft. Background Art

[0002] In the aviation industry, many aircraft use a 14V DC, 250W generator power supply system to power onboard electronic equipment. This voltage level is suitable for powering electronic equipment and systems onboard aircraft, including but not limited to lighting, communication equipment, and navigation systems.

[0003] When an aircraft needs to be equipped with additional equipment, the voltage level and power usage of the existing generator power supply system cannot meet the usage requirements. Utility Model Content

[0004] The utility model provides an aircraft generator power supply system and an aircraft, which are used to solve the defect of a single voltage level power supply of aircraft generators in the prior art. By introducing a transformer, the power supply capability of multiple voltage levels is achieved, thereby supporting more types of onboard equipment.

[0005] The utility model provides an aircraft generator power supply system, comprising:

[0006] a generator having a rotor, wherein the rotor is connected to an aircraft engine;

[0007] a voltage regulator electrically connected to the rotor, and configured to supply power to the rotor so that the generator outputs a first power supply voltage to a first electrical device;

[0008] A transformer is electrically connected to the generator and is used to convert the first supply voltage into a second supply voltage and output the second supply voltage to a second electrical device.

[0009] According to an aircraft generator power supply system provided by the present invention, the generator is provided with a rotor end and a voltage output end, the rotor end is electrically connected to the rotor, and the voltage output end is electrically connected to the first electrical device and the input side of the transformer;

[0010] The voltage regulator is provided with an enabling terminal and an excitation terminal. The enabling terminal is used to input a power supply signal, and the excitation terminal is electrically connected to the rotor terminal for supplying power to the rotor.

[0011] According to an aircraft generator power supply system provided by the utility model, the voltage regulator is further provided with a sensing end, and the sensing end is connected to the enabling end and is used to sense the power supply signal.

[0012] According to an aircraft generator power supply system provided by the present invention, the voltage output end of the generator includes:

[0013] Positive terminal, connected to the first positive power line of the aircraft;

[0014] Negative terminal, connected to the first ground wire of the aircraft;

[0015] The first electrical device and the input side of the transformer are both connected to the first positive power line and the first ground line;

[0016] The enable terminal of the voltage regulator is connected to the first positive power line.

[0017] According to an aircraft generator power supply system provided by the utility model, a circuit breaker is provided between the enabling end of the voltage regulator and the first positive power line;

[0018] And / or, the voltage regulator is further provided with a grounding terminal, and the grounding terminal is connected to the first grounding wire.

[0019] According to an aircraft generator power supply system provided by the utility model, the generator is further provided with a first detection terminal, and the voltage regulator is further provided with a second detection terminal, the second detection terminal being connected to the first detection terminal and being used to detect the operating voltage of the generator;

[0020] The voltage regulator is further provided with a working indication terminal, which is connected to the first positive power line via a working indicator light.

[0021] According to an aircraft generator power supply system provided by the utility model, a fuse is provided between the working indicator light and the first positive power line.

[0022] According to an aircraft generator power supply system provided by the present invention, the output side of the transformer is connected to the second positive power line and the second ground line of the aircraft, and the second electrical equipment is connected to the second positive power line and the second ground line.

[0023] According to an aircraft generator power supply system provided by the present invention, the first power supply voltage is DC 28V, and the second power supply voltage is DC 14V.

[0024] The utility model also provides an aircraft, comprising: the above-mentioned aircraft generator power supply system.

[0025] The aircraft generator power supply system and aircraft provided by the present invention utilize a voltage regulator to enable the generator to output a stable first power supply voltage for powering a first electrical device. A transformer, provided in the generator's output circuit, converts the first power supply voltage output by the generator into a second power supply voltage for powering a second electrical device. This allows the aircraft to support the use of both the first and second electrical devices. Therefore, the present invention's generator power supply system solves the problem of existing aircraft generators supplying power at a single voltage level, enabling the use of a variety of different devices and enriching the diversity of onboard equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0027] Figure 1 It is a structural schematic diagram of the aircraft generator power supply system provided by the utility model.

[0028] Reference numerals:

[0029] 1. Generator;

[0030] 101, rotor; 102, rotor end; 103, voltage output end; 1031, positive end;

[0031] 1032, negative terminal; 104, first detection terminal;

[0032] 2. Voltage regulator;

[0033] 201, enable terminal; 202, excitation terminal; 203, induction terminal; 204, ground terminal;

[0034] 205, second detection terminal; 206, work indication terminal;

[0035] 3. Transformer; 4. First electrical equipment; 5. Second electrical equipment;

[0036] 6. First positive power line; 7. First ground line; 8. Circuit breaker; 9. Working indicator light;

[0037] 10. Fuse; 11. Second positive power line; 12. Second ground line. DETAILED DESCRIPTION

[0038] To make the purpose, technical solutions, and advantages of the present invention more clear, the following will be combined with the accompanying drawings to clearly and completely describe the technical solutions of the present invention. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0039] In the description of the embodiments of the present invention, it should be noted that the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0040] In the description of the embodiments of the present invention, it should be noted that, unless otherwise specified or limited, the terms "connected" and "connection" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; direct connections, or indirect connections through an intermediary. Those skilled in the art will understand the specific meanings of the above terms in the embodiments of the present invention based on specific circumstances.

[0041] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiment of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0042] According to the embodiment of the first aspect of the present invention, referring to Figure 1 As shown, the aircraft generator power supply system provided by the present invention primarily comprises: a generator 1, a voltage regulator 2, and a transformer 3. Generator 1 includes a rotor 101, which is connected to the aircraft engine. Voltage regulator 2 is electrically connected to rotor 101 and is configured to supply power to rotor 101, thereby enabling generator 1 to output a first supply voltage to a first electrical device 4. Transformer 3 is electrically connected to generator 1 and is configured to convert the first supply voltage into a second supply voltage, which is then output to a second electrical device 5.

[0043] In this embodiment of the present invention, the problem of a single voltage level power supply system on an aircraft is solved by introducing a transformer 3 to achieve a multi-voltage level power supply capability, thereby supporting more types of onboard equipment. Specifically:

[0044] The core component of the generator 1 is the rotor 101 . The rotor 101 is connected to the engine of the aircraft through a mechanical connection, and the rotor 101 of the generator 1 is driven to rotate by the aircraft engine.

[0045] The voltage regulator 2 is electrically connected to the rotor 101 of the generator 1 and is responsible for providing an excitation current to the rotor 101 to ensure that the generator 1 can stably output a first supply voltage. Furthermore, the voltage regulator 2 can adjust the current supplied to the rotor 101 by monitoring the output voltage of the generator 1, thereby maintaining a stable output voltage.

[0046] The input side of the transformer 3 is connected to the output circuit of the generator 1 and is used to convert the first supply voltage into another voltage level, ie, a second supply voltage (eg, a lower or higher voltage level).

[0047] The output side of the transformer 3 is connected to a second electrical consumer 5 that requires a second supply voltage.

[0048] The working principle of the aircraft generator power supply system of the embodiment of the utility model generally includes:

[0049] When the aircraft engine starts and reaches a certain speed, it drives rotor 101 of generator 1 to rotate. Voltage regulator 2 detects the output voltage of generator 1 and provides an appropriate excitation current to rotor 101 to establish a stable magnetic field. As rotor 101 rotates, generator 1 begins to output a first supply voltage.

[0050] The voltage regulator 2 continuously monitors the output voltage of the generator 1 and adjusts the current supplied to the rotor 101 as needed. If the output voltage of the generator 1 is too high or too low, the voltage regulator 2 increases or decreases the excitation current accordingly to maintain a stable output voltage, thereby outputting a stable first supply voltage to the first electrical device 4.

[0051] When a second power supply voltage, different from the first, is required for a second power consumer 5, transformer 3 comes into play. Transformer 3 converts the first power supply voltage into the required second power supply voltage. This voltage conversion enables the aircraft to power devices requiring different voltages, thereby increasing the diversity of onboard equipment.

[0052] Therefore, the aircraft generator power supply system provided by the present embodiment expands its functionality and flexibility by introducing transformer 3. Not only can it power devices requiring a first supply voltage, but it can also convert the voltage level through transformer 3 to power devices requiring a second supply voltage. This solves the problem of single-voltage power supply and improves the flexibility and efficiency of aircraft equipment configuration. Furthermore, the presence of voltage regulator 2 ensures the stability of the generator 1 output voltage, which is crucial for ensuring reliable operation of the aircraft's electrical system.

[0053] According to one embodiment of the present invention, referring to Figure 1 As shown, the generator 1 is provided with a rotor end 102 and a voltage output end 103. The rotor end 102 is electrically connected to the rotor 101, and the voltage output end 103 is electrically connected to the first electrical device 4 and the input side of the transformer 3. The voltage regulator 2 is provided with an enable end 201 and an excitation end 202. The enable end 201 is used to input a power supply signal, and the excitation end 202 is electrically connected to the rotor end 102 for supplying power to the rotor 101.

[0054] In this embodiment of the present invention, the generator 1 is provided with a rotor end 102 and a voltage output end 103. The rotor end 102 is electrically connected to the rotor 101 and is configured to receive excitation current from the voltage regulator 2. The voltage output end 103 is electrically connected to the first electrical device 4 and the input side of the transformer 3 to supply power to these devices.

[0055] The voltage regulator 2 is provided with an enable terminal 201 and an excitation terminal 202. The enable terminal 201 is used to receive a power supply signal to power the voltage regulator 2. The excitation terminal 202 is electrically connected to the rotor terminal 102 of the generator 1 and is used to provide excitation current to the rotor 101 of the generator 1.

[0056] The input side of the transformer 3 is electrically connected to the voltage output terminal 103 of the generator 1, and receives the first supply voltage output by the generator 1. The output side of the transformer 3 is electrically connected to the second power device 5, and is used to convert the first supply voltage into a second supply voltage and supply power to the second power device 5.

[0057] When the aircraft engine starts and drives the rotor 101 of the generator 1 to rotate, the voltage regulator 2 receives a power supply signal through its enable terminal 201 and begins supplying power. The excitation terminal 202 of the voltage regulator 2 provides an excitation current to the rotor terminal 102 of the generator 1, generating a magnetic field in the rotor 101. As the rotor 101 of the generator 1 rotates and interacts with the magnetic field, the generator 1 begins to generate a first supply voltage.

[0058] The first power supply voltage generated by the generator 1 is output from the voltage output terminal 103 , and is used to supply power to the first power consumption device 4 on the one hand, and is input to the transformer 3 on the other hand.

[0059] The transformer 3 converts the first supply voltage into the required second supply voltage and supplies power to the second electrical device 5. In this way, even if the generator 1 can only provide the first supply voltage, the transformer 3 can also supply power to devices requiring other voltages.

[0060] Therefore, the present embodiment effectively manages and expands the output voltage of generator 1 by introducing voltage regulator 2 and transformer 3. Voltage regulator 2 ensures the stability of generator 1's output voltage, while transformer 3 converts between different voltage levels, enabling the aircraft to support a wider range of onboard equipment. This design enhances the flexibility and adaptability of the aircraft's electrical system while also ensuring system stability and reliability.

[0061] According to one embodiment of the present invention, referring to Figure 1 As shown, the voltage regulator 2 is further provided with a sensing terminal 203 , which is connected to the enabling terminal 201 and is used to sense the power supply signal.

[0062] Specifically, when the aircraft engine starts and drives the rotor 101 of the generator 1 to rotate, the voltage regulator 2 receives a power supply signal through its enable terminal 201 and begins supplying power. The sensing terminal 203 senses the power supply signal. When a voltage increase is detected, the voltage regulator 2 provides an excitation current to the rotor terminal 102 of the generator 1 through the excitation terminal 202, generating a magnetic field in the rotor 101 and thus generating electricity.

[0063] According to one embodiment of the present invention, referring to Figure 1 As shown, the voltage output terminal 103 of the generator 1 includes: a positive terminal 1031 and a negative terminal 1032, the positive terminal 1031 is connected to the first positive power line 6 of the aircraft; the negative terminal 1032 is connected to the first ground line 7 of the aircraft; the input sides of the first electrical device 4 and the transformer 3 are both connected to the first positive power line 6 and the first ground line 7; the enable terminal 201 of the voltage regulator 2 is connected to the first positive power line 6.

[0064] Specifically, the enable terminal 201 of the voltage regulator 2 is connected to the first positive power line 6 of the aircraft, and is used to receive a power supply signal and supply power to the voltage regulator 2 .

[0065] The input sides of the first electrical device 4 and the transformer 3 are both connected to the first positive power line 6 and the first ground line 7 of the aircraft. The first electrical device 4 can directly obtain the first power supply voltage from the generator 1, and the transformer 3 converts the first power supply voltage into a second power supply voltage.

[0066] This embodiment of the utility model ensures efficient utilization of the output voltage of generator 1 through electrical connections. Voltage regulator 2 receives a power supply signal via connection to first positive power line 6 and controls the output voltage of generator 1 by adjusting the excitation current. Simultaneously, first power consumer 4 and transformer 3 draw their required voltage directly from generator 1 via connections to first positive power line 6 and first ground line 7. This design enhances the flexibility and adaptability of the aircraft electrical system while also ensuring system stability and reliability.

[0067] According to one embodiment of the present invention, referring to Figure 1 As shown, a circuit breaker 8 is provided between the enable terminal 201 of the voltage regulator 2 and the first positive power line 6 .

[0068] For example, the circuit breaker 8 may be a 5A circuit breaker, that is, it may be disconnected when the current in the circuit exceeds 5A to prevent damage caused by overload or short circuit, thereby achieving circuit protection.

[0069] This embodiment of the present invention enhances system safety by adding a circuit breaker 8 between the enable terminal 201 of the voltage regulator 2 and the first positive power line 6. Circuit breaker 8 automatically disconnects the circuit when current flow is abnormal, protecting the voltage regulator 2 and related circuits from damage caused by overload or short circuit. This design improves the safety and reliability of the aircraft's electrical system.

[0070] According to one embodiment of the present invention, referring to Figure 1 As shown, the voltage regulator 2 is further provided with a grounding terminal 204 , which is connected to the first grounding line 7 .

[0071] The embodiment of the present invention ensures safe grounding of the voltage regulator 2 by adding a ground terminal 204 to the voltage regulator 2, helping to prevent the danger of current passing through the human body during an electrical fault. This design improves the safety and reliability of the aircraft electrical system.

[0072] According to one embodiment of the present invention, referring to Figure 1 As shown, the generator 1 is further provided with a first detection terminal 104, and the voltage regulator 2 is further provided with a second detection terminal 205, which is connected to the first detection terminal 104 and is used to detect the operating voltage of the generator 1; the voltage regulator 2 is further provided with a working indication terminal 206, which is connected to the first positive power line 6 via the working indicator light 9.

[0073] Specifically, the second detection terminal 205 of the voltage regulator 2 is connected to the first detection terminal 104 of the generator 1 for detecting the operating voltage of the generator 1 .

[0074] When a voltage anomaly is detected (such as being continuously too high or too low), the voltage regulator 2 will trigger the working indication terminal 206 to light up the working indicator light 9 to alert the operator to the voltage fault.

[0075] The working indicator light 9 is powered by the first positive power line 6. When the voltage is normal, the working indicator light 9 is off; when a voltage fault is detected, the working indicator light 9 lights up and issues an alarm.

[0076] By adding first detection terminal 104 and second detection terminal 205, this embodiment of the utility model effectively detects the operating voltage of generator 1. When a voltage anomaly is detected, an alarm is issued via operating indicator light 9, improving system safety and reliability. This design facilitates timely detection of electrical faults and the implementation of appropriate measures, thereby ensuring the stable operation of the aircraft's electrical system.

[0077] According to one embodiment of the present invention, referring to Figure 1 As shown, a fuse 10 is provided between the working indicator light 9 and the first positive power line 6 .

[0078] For example, the fuse 10 may be a 1A fuse, that is, it may melt when the current in the circuit exceeds 1A, thereby preventing damage caused by overload or short circuit and achieving circuit protection.

[0079] This embodiment of the present invention enhances system safety by adding a fuse 10 between the operating indicator light 9 and the first positive power line 6. Fuse 10 can blow when current flow is abnormal, protecting the operating indicator light 9 and related circuits from damage caused by overload or short circuit. This design improves the safety and reliability of the aircraft's electrical system.

[0080] According to one embodiment of the present invention, referring to Figure 1 As shown, the output side of the transformer 3 is connected to the second positive power line 11 and the second ground line 12 of the aircraft, and the second electrical device 5 is connected to the second positive power line 11 and the second ground line 12.

[0081] Specifically, the input side of transformer 3 is connected to the aircraft's first positive power line 6 and first ground line 7, receiving a first supply voltage. Transformer 3 converts the first supply voltage into a required second supply voltage, and its output side is connected to the aircraft's second positive power line 11 and second ground line 12. Second powered device 5 is connected to second positive power line 11 and second ground line 12, directly receiving the required second supply voltage from transformer 3.

[0082] This embodiment of the present invention supports different voltage levels by connecting the output side of transformer 3 to the aircraft's second positive power line 11 and second ground line 12. This design allows the aircraft to power a first electrical device 4 requiring a first supply voltage and a second electrical device 5 requiring a second supply voltage.

[0083] According to an embodiment of the present invention, the first supply voltage is DC 28V, and the second supply voltage is DC 14V.

[0084] Specifically, the first power supply voltage is DC 28V, and the corresponding power may be 480W; the second power supply voltage is DC 14V, and the corresponding power may be 250W.

[0085] This embodiment of the utility model supports different voltage level requirements by adjusting the voltage level output by the generator 1. In this configuration, the first power device 4 can use a DC voltage of 28V, corresponding to a power of 480W; the second power device 5 can use a DC voltage of 14V, corresponding to a power of 250W.

[0086] Of course, the first power supply voltage and the second power supply voltage can also be designed and adjusted according to actual requirements of electrical equipment.

[0087] According to an embodiment of the second aspect of the present invention, the present invention further provides an aircraft, comprising: the aircraft generator power supply system of the above embodiment.

[0088] Since the aircraft provided by the embodiment of the present invention includes the aircraft generator power supply system of the above embodiment, it has all the technical effects of the aircraft generator power supply system of the above embodiment, which will not be described in detail here.

[0089] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An aircraft generator power supply system, characterized in that: include: a generator having a rotor, wherein the rotor is connected to an aircraft engine; a voltage regulator electrically connected to the rotor, and configured to supply power to the rotor so that the generator outputs a first power supply voltage to a first electrical device; A transformer is electrically connected to the generator and is used to convert the first supply voltage into a second supply voltage and output the second supply voltage to a second electrical device.

2. The aircraft generator power supply system according to claim 1, characterized in that: The generator is provided with a rotor end and a voltage output end, the rotor end is electrically connected to the rotor, and the voltage output end is electrically connected to the first electrical device and the input side of the transformer; The voltage regulator is provided with an enabling terminal and an excitation terminal. The enabling terminal is used to input a power supply signal, and the excitation terminal is electrically connected to the rotor terminal for supplying power to the rotor.

3. The aircraft generator power supply system according to claim 2, characterized in that: The voltage regulator is further provided with a sensing end, which is connected to the enabling end and is used to sense the power supply signal.

4. The aircraft generator power supply system according to claim 2, characterized in that: The voltage output terminal of the generator includes: Positive terminal, connected to the first positive power line of the aircraft; The negative terminal is connected to the first ground wire of the aircraft; The first electrical device and the input side of the transformer are both connected to the first positive power line and the first ground line; The enable terminal of the voltage regulator is connected to the first positive power line.

5. The aircraft generator power supply system according to claim 4, characterized in that: A circuit breaker is provided between the enabling terminal of the voltage regulator and the first positive power line; And / or, the voltage regulator is further provided with a grounding terminal, and the grounding terminal is connected to the first grounding wire.

6. The aircraft generator power supply system according to claim 4, characterized in that: The generator is further provided with a first detection terminal, and the voltage regulator is further provided with a second detection terminal, the second detection terminal being connected to the first detection terminal and being used to detect the operating voltage of the generator; The voltage regulator is further provided with a working indication terminal, which is connected to the first positive power line via a working indicator light.

7. The aircraft generator power supply system according to claim 6, characterized in that: A fuse is provided between the working indicator light and the first positive power line.

8. The aircraft generator power supply system according to claim 1, characterized in that: The output side of the transformer is connected to a second positive power line and a second ground line of the aircraft, and the second electrical device is connected to the second positive power line and the second ground line.

9. The aircraft generator power supply system according to any one of claims 1 to 8, characterized in that: The first power supply voltage is DC 28V, and the second power supply voltage is DC 14V.

10. An aircraft, characterized in that: include: The aircraft generator power supply system according to any one of claims 1 to 9.

Images