Integrated aircraft power system

Abstract

The utility model relates to the technical field of aircrafts, in particular to an integrated aircraft power system which comprises a motor, and the non-blade mounting side of an output shaft of the motor is in power connection with the first end of a connecting shaft. The driver is mounted on the non-blade mounting side of the output shaft of the motor, and the driver is provided with a through channel; the rotary transformer is arranged on the outer side of the connecting shaft in a sleeving mode, the rotary transformer is located in the channel of the driver, and the rotary transformer is used for being matched with the driver to serve as a motor rotor position sensor. The driver and the motor in the power system are tightly connected, the length of a motor wire is shortened, shielding processing is facilitated, and the EMI problem is solved. The driver cooling fan is powered by the motor, fan blade rotating speed is directly proportional to the motor rotating speed, heating power consumption of a power system is directly proportional to the motor rotating speed, the cooling capacity of the fan blades is directly proportional to heating power consumption of the driver, and good circulation is formed.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft technology field, especially integrated aircraft power system. BACKGROUND

[0002] For the power system used for large aircraft, the driver and the motor are often separated, there is a distance between the driver and the motor, resulting in a certain length of the motor line. Under normal circumstances, high-power power system often adopts 400V-1000V high-voltage power supply platform, the driver adopts SIC MOS tube as power device, the switching speed is fast, and EMI is particularly serious, and the longer motor line makes the EMI problem more serious. At the same time, for various existing aircraft, if the driver is in independent form, the driver itself heat dissipation also needs to be considered, and the installation of the aircraft is not friendly.

[0003] The deficiencies of the prior art mainly exist in the following three aspects:

[0004] 1. When the driver and the motor are installed separately, the longer motor line will make the power system EMI very serious.

[0005] 2. If the driver and the motor are combined as a whole, the heat dissipation problem will be aggravated while solving the EMI problem. After adding an additional heat dissipation device, the system complexity, fault points and failure rate will be increased. INVENTION CONTENTS

[0006] In order to solve the above problems, the utility model provides an integrated aircraft power system, which shortens the distance between the driver and the motor stator base, solves the EMI problem, and can also provide good heat dissipation effect.

[0007] In order to achieve the above purpose, the utility model adopts the technical scheme of:

[0008] The integrated aircraft power system comprises:

[0009] The motor, the first end of the connecting shaft on the non-blade mounting side of the output shaft of the motor is power connected;

[0010] The driver is installed on the non-blade mounting side of the output shaft of the motor, and the driver has a through channel;

[0011] The resolver is sleeved on the outside of the connecting shaft, and the resolver is located in the channel of the driver, and the resolver is used as a motor rotor position sensor in cooperation with the driver.

[0012] As a preferred, the motor and the driver are connected through screws.

[0013] As preferred, the second end of the connecting shaft is provided with a transmission mechanism, the input end of the transmission mechanism is connected with the second end of the connecting shaft, and the output end of the transmission mechanism is connected with the fan.

[0014] When the fan is driven to rotate, air can be driven to flow towards the driver.

[0015] As preferred, the transmission mechanism is a planetary gear transmission.

[0016] As preferred, the lower opening of the channel of the driver is provided with a ring gear, the second end of the connecting shaft is connected with a planetary carrier, three planetary gears are hinged on the planetary carrier, the three planetary gears are meshed with the ring gear, a sun gear is arranged between the three planetary gears and is meshed with the three planetary gears, and the sun gear is coaxially connected with the fan.

[0017] As preferred, the fan is connected with the output shaft of the sun gear through spline transmission.

[0018] The beneficial effects of the utility model are as follows:

[0019] 1. The driver and the motor are closely connected, the length of the motor wire is shortened, the shielding treatment is facilitated, and the EMI problem is solved.

[0020] 2. The driver cooling fan is driven by the motor, the rotating speed of the fan blade is proportional to the rotating speed of the motor, the heat generation power of the power system is proportional to the rotating speed of the motor, the heat dissipation capacity of the fan blade is proportional to the heat generation power of the driver, and good circulation is formed.

[0021] 3. The whole cooling system does not need to increase additional electric equipment, the failure points are reduced, the weight is saved, the system complexity is reduced, and the failure rate is greatly reduced. DRAWINGS

[0022] Figure 1 It is an explosion view of the integrated aircraft power system.

[0023] Figure 2 It is a longitudinal sectional view of the integrated aircraft power system.

[0024] Figure 3 It is a whole schematic view of the integrated aircraft power system.

[0025] Figure 4 It is a schematic view of the planetary gear transmission.

[0026] The reference signs include:

[0027] 1-motor, 2-connecting shaft, 3-rotary transformer, 4-driver, 5-planetary gear, 51-planetary carrier, 52-planet wheel, 53-ring gear, 54-sun gear, 6-fan, 7-propeller, 8-blade mounting base, 9-supporting column, 10-ring gear fixing plate. DETAILED DESCRIPTION

[0028] To make the objectives, technical solutions, and advantages of the present technical solution clearer, the present technical solution will be further described in detail below with specific embodiments. It should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present technical solution.

[0029] To solve the problem of serious EMI in the aircraft power system in the prior art, the embodiment provides an integrated aircraft power system, which can solve the above problems.

[0030] In combination with Figure 1 and Figure 2 , specifically, in the embodiment, the output end of the motor 1 is connected with the connecting shaft 2, that is, the motor 1 can drive the connecting shaft 2 to rotate through the output end, the rotary transformer 3 is sleeved on the middle part of the connecting shaft 2, that is, the rotary transformer 3 can be driven to rotate synchronously through the connecting shaft 2, that is, the stator of the motor 1 has the same rotating speed as the rotary transformer 3 when the motor 1 rotates. The driver 4 is installed on the side of the motor 1 towards the output end, wherein the middle part of the driver 4 has a column-shaped channel penetrating through the two end faces of the driver 4. After the motor 1 and the driver 4 are connected through detachable screws and nuts, the connecting shaft 2 and the rotary transformer 3 are simultaneously inserted into the channel in the middle part of the driver 4, and the end of the connecting shaft 2 away from the motor 1 is outside the driver 4, that is, the connecting shaft 2 penetrates through the driver 4. In the embodiment, the outer side of the driver 4 has four symmetrical supports, and the supporting columns 9 are arranged on the four supports respectively, and the supporting columns 9 are connected with the screw holes on the shell of the motor 1 through bolts to realize the fixation of the driver 4 and the motor 1.

[0031] The second end of the connecting shaft 2 is provided with a speed change mechanism, the input end of the speed change mechanism is power-connected with the second end of the connecting shaft 2, and the output end of the speed change mechanism is connected with the fan 6. When the fan 6 is driven to rotate, it can drive air to flow towards the driver 4. The connecting shaft 2 and the planetary gear are connected through a pin, and the fan 6 and the planetary gear are connected through threads and splines.

[0032] As shown in Figure 3 , the upper part of the motor 1 is provided with a propeller 7 for providing power to the unmanned aerial vehicle. In the embodiment, the propeller 7 is connected to the output shaft on the top of the motor 1 through the blade mounting base 8, and the motor can directly drive the propeller 7 and the blade mounting base 8 to rotate synchronously.

[0033] In this embodiment, the transmission mechanism needs compact structure and good stability, so the planetary gear 52 transmission 5 is selected.

[0034] The planetary gear 52 transmission 5 is installed at the port of the channel of the driver 4 away from the motor 1, and the planetary gear 52 transmission 5 includes a spider, three planetary gears 52, a sun gear 54 and a ring gear 53. Figure 4 As shown, the ring gear 53 is installed at the lower opening of the channel of the driver 4, the second end of the connecting shaft 2 is connected with the spider 51, the spider 51 is hinged with the three planetary gears 52, the three planetary gears 52 are engaged with the ring gear 53, the three planetary gears 52 have the sun gear 54 in the middle, the sun gear 54 is engaged with the three planetary gears 52, and the sun gear 54 is coaxially connected with the fan 6. In this embodiment, the ring gear 53 is externally provided with a ring gear fixing plate 10, and the ring gear 53 is fixedly installed in the inside of the driver 4 through the ring gear fixing plate 10.

[0035] In the structure of the power system, the driver 4 is connected with the stator base of the motor 1, the distance is very short, the shell of the driver 4 is annular hollow, the rotor main shaft of the motor 1 passes through the shell of the driver 4 and reaches the opposite side of the driver 4, the inside of the driver 4 is installed with the rotary transformer 3, the main shaft is connected in series with the planetary transmission, and finally the fan 6 blades are connected.

[0036] In the function of the power system, when the motor 1 operates, the main shaft drives the planetary transmission, the planetary transmission processes speed multiplication and drives the fan 6 blades to blow air to the driver 4, so that the driver 4 is well cooled, and the motor 1 is also cooled by the airflow. The rotary transformer 3 is used as a rotor position sensor of the motor 1 and is provided for the driver 4.

[0037] The power system solves the EMI problem and the heat dissipation problem of the driver 4 and the motor 1 in the high-power power system without increasing the complexity of the system.

[0038] The above is only a preferred embodiment of the present application, and those skilled in the art can make many changes in the specific implementation and application range according to the technical content of the present application, as long as the changes do not deviate from the concept of the present application, and all belong to the protection scope of the present application.

Claims

1. An integrated aircraft power system, characterized by: The utility model relates to a fan driving device, including Motor, the non-paddle installation side of output shaft of motor is connected with the first end of connecting shaft powerfully; Driver, driver is installed in the non-paddle installation side of motor output shaft, and driver has the passage through; Rotary transformer, rotary transformer is sleeved on the outside of connecting shaft, rotary transformer is located in the passage of driver, and rotary transformer is used to cooperate with driver to serve as motor rotor position sensor.

2. The integrated aircraft power system of claim 1, wherein: The motor and the driver are connected by screws.

3. The integrated aircraft power system of claim 1, wherein: The second end of the connecting shaft is provided with a speed change mechanism, the input end of the speed change mechanism is connected with the second end of the connecting shaft, and the output end of the speed change mechanism is connected with a fan. When the fan is driven to rotate, air can be driven to flow to the direction of the driver.

4. The integrated aircraft power system of claim 3, wherein: The speed change mechanism is a planetary gear transmission.

5. The integrated aircraft power system of claim 4, wherein: A gear ring is installed at the lower opening of the passage of the driver, the second end of the connecting shaft is connected with a planet carrier, three planetary gears are hinged on the planet carrier, the three planetary gears are meshed with the gear ring, a sun gear is arranged between the three planetary gears, the sun gear is meshed with the three planetary gears, and the sun gear is coaxially connected with the fan.

6. The integrated aircraft power system of claim 5, wherein: The fan and the output shaft of the sun gear are connected by spline transmission.

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