Propeller device

Abstract

The present invention provides a propeller device that includes both a duct and a pitch angle changing section. [Solution] The propeller device 40A comprises a propeller 100 having a plurality of blades 102 and a pitch angle changing unit 140 that changes the pitch angle of each blade 102. The propeller device 40A further comprises a duct 170 and a support member 180 supported by the aircraft body 12. The duct 170 has a duct hub 174. The support member 180 extends along the rotation axis A1 of the propeller 100 and supports the duct hub 174.

Description

【Technical Field】 【0001】 The present disclosure relates to a propeller device. 【Background Art】 【0002】 U.S. Patent No. 11,420,762 discloses a propeller device capable of changing the pitch angles of a plurality of blades. Specifically, the propeller device includes a control tube that linearly moves by an actuator, and a crosshead provided at one end of the control tube. The plurality of blades are supported by the crosshead. As the control tube and the crosshead move linearly integrally, the pitch angles of the plurality of blades are changed. 【0003】 Japanese Unexamined Patent Application Publication No. 2024-33168 discloses a propeller device including a duct. In this case, the duct has a cylindrical body surrounding the outer periphery of the propeller, and a duct hub and a duct stator located inside the cylindrical body. Air flows inside the cylindrical body. Inside the cylindrical body, the air flow direction is from the flight direction (front) of the aircraft to the opposite direction of the flight direction (rear). In the air flow direction, the duct hub and the duct stator are arranged downstream of the plurality of blades. 【Prior Art Documents】 【Patent Documents】 【0004】 【Patent Document 1】 U.S. Patent No. 11,420,762 【Patent Document 2】 Japanese Unexamined Patent Application Publication No. 2024-33168 【Summary of the Invention】 【Problems to be Solved by the Invention】 【0005】 There is a demand for a propeller device including both a duct and a pitch angle changing section. 【0006】 This disclosure aims to solve the problems described above. [Means for solving the problem] 【0007】 Aspects of the present disclosure are propeller devices provided on an aircraft to generate lift or thrust on the aircraft, comprising: a propeller having a plurality of blades; a rotational driving force applying unit for applying rotational driving force to the propeller; and a pitch angle changing unit for changing the pitch angle of the plurality of blades; a cylindrical body surrounding the outer circumference of the propeller; a duct hub located inside the cylindrical body; and a duct stator connecting the duct hub and the cylindrical body, wherein the duct hub and the duct stator further comprise a duct located downstream of the propeller in the direction of airflow within the cylindrical body; and a support member supported by the aircraft and extending along the rotation axis of the propeller to support the duct hub. [Effects of the Invention] 【0008】 According to this disclosure, a duct can be further provided to a propeller device that includes a pitch angle changing section. [Brief explanation of the drawing] 【0009】 [Figure 1] Figure 1 is a schematic perspective view of a vertical takeoff and landing aircraft. [Figure 2] Figure 2 is a schematic cross-sectional side view of the propeller device according to the first embodiment, viewed from a direction perpendicular to the rotation axis of the propeller. [Figure 3] Figure 3 is a cross-sectional view taken along line III-III in Figure 2. [Figure 4] Figure 4 is a schematic cross-sectional side view of the propeller system with the crosshead moved forward, viewed from a direction perpendicular to the propeller's axis of rotation. [Figure 5] Figure 5 is a schematic diagram of a crosshead in a different embodiment. [Figure 6] Figure 6 is a schematic cross-sectional side view of the propeller device according to the second embodiment, viewed from a direction perpendicular to the rotation axis of the propeller. [Modes for carrying out the invention] 【0010】 The propeller system will be explained below using the propeller system 40A mounted on the vertical take-off and landing (VTOL) aircraft 10 shown in Figure 1 as an example. Although the VTOL aircraft 10 in the illustrated example is a passenger aircraft, the VTOL aircraft 10 may also be an unmanned aerial vehicle such as a drone. Furthermore, the direction in which the VTOL aircraft 10 cruising is defined as "forward," and the opposite direction of "forward" is defined as "rear." 【0011】 Figure 1 is a schematic perspective view of the VTOL aircraft 10. The VTOL aircraft 10 comprises a fuselage 12, two propeller units 40A, and eight lift generating units 30. The fuselage 12 has a body 14, a forewing 16, a rear wing 18, and two booms 20L and 20R. The two propeller units 40A are mounted on the rear wing 18. The two propeller units 40A are so-called cruise rotors, which draw in air in front of multiple blades 102 (propellers 100) and expel it behind the propellers 100. Each propeller unit 40A thereby generates thrust for the VTOL aircraft 10. 【0012】 Four of the eight lift-generating units 30 are installed on the boom 20L. The remaining four of the eight lift-generating units 30 are installed on the boom 20R. The eight lift-generating units 30 are so-called VTOL rotors, which draw in air above the multiple blades 32 (propellers 34) and discharge it below the propellers 34. Each lift-generating unit 30 thereby generates lift for the VTOL aircraft 10. The eight lift-generating units 30 may be configured in the same way as the two propeller devices 40A. 【0013】 In the first embodiment, the propeller device 40A will be described in which the rotational driving force application unit 110 shown in Figure 2 is configured with a motor 112A. In this case, the VTOL aircraft 10 is a so-called eVTOL aircraft. However, the rotational driving force application unit 110 is not limited to a motor 112A. The rotational driving force application unit 110 may also be an internal combustion engine. 【0014】 Figure 2 is a schematic cross-sectional side view of the propeller device 40A viewed from a direction perpendicular to the rotation axis A1 of the propeller 100. The propeller device 40A comprises the propeller 100, which has a plurality of blades 102. The propeller device 40A further comprises a motor 112A as a rotational driving force application unit 110 and a pitch angle changing unit 140. 【0015】 Motor 112A has a rotor 114 and a stator 120 surrounding the outer circumference of the rotor 114. That is, in the illustrated example, motor 112A is a so-called inner-rotor type motor in which the rotor 114 is located inside the stator 120. The rotor 114 has a rotating sleeve 116 and a plurality of permanent magnets 118 provided on the outer circumference of the rotating sleeve 116. The stator 120 has an electromagnetic coil 122. 【0016】 The rotating sleeve 116 is rotatable about a rotation axis A1. The direction in which the rotation axis A1 extends coincides with the extension direction of the rotating sleeve 116. The rotating sleeve 116 has two ends in the extension direction. One of the two ends is close to the rear wing 18, which is part of the aircraft body 12, and faces forward. The other end is spaced away from the rear wing 18 and faces rearward. Hereinafter, this end will be referred to as the sleeve rear end 117. 【0017】 The propeller 100 is provided at the rear end 117 of the sleeve. Specifically, the rear end 117 of the sleeve is provided with a plurality of blade support parts 130. The base, which is one end in the longitudinal direction of each of the plurality of blades 102, is inserted into each of the plurality of blade support parts 130 and is supported by each of the plurality of blade support parts 130 so as to be able to swing. The pivot point of each blade 102 is the blade axis A2. When the rotating sleeve 116 rotates, the propeller 100 rotates integrally with the rotating sleeve 116. The pivot point of the propeller 100 is located on the rotation axis A1. The longitudinal direction of each of the plurality of blades 102 is, for example, approximately perpendicular to the rotation axis A1. 【0018】 The pitch angle changing unit 140 includes an actuator 142, a rod 144, and a crosshead 150. The rod 144 has a rod front end 146a, which is one end in the extending direction and faces the actuator 142, and a rod rear end 146b, which is the other end in the extending direction. When the rod front end 146a is connected to the actuator 142, the rod 144 is connected so as to extend rearward. In this state, the actuator 142 moves the rod 144 linearly. The moving direction of the rod 144 is forward or backward (the direction along the rotation axis A1 of the propeller 100). 【0019】 The crosshead 150 has a cylindrical portion 152 and a rod holding portion 154. In the illustrated example, a connecting hole 155 is formed in the rod holding portion 154. By fixing the rod rear end 146b to the connecting hole 155, the rod 144 is connected to the rod holding portion 154. Alternatively, a threaded portion may be provided on the side surface of the rod rear end 146b. In this case, after passing the threaded portion through the connecting hole 155, a nut is screwed onto the threaded portion. Thereby, the rod 144 is connected to the rod holding portion 154. Based on the connection of the rod 144 (rod rear end 146b) to the rod holding portion 154 as described above, the crosshead 150 moves integrally with the rod 144. 【0020】 A pin groove 156 is formed on the side surface of the crosshead 150. The pin groove 156 extends in a circular shape along the circumferential direction of the side surface. A bearing 160 is inserted into the pin groove 156. The bearing 160 supports one end of each of a plurality of operating pins 162. The other end of each operating pin 162 is connected to the base of each blade 102. As each operating pin 162 moves integrally with the crosshead 150, each blade 102 swings about the blade axis A2. 【0021】 The propeller device 40A further comprises a duct 170 and a support member 180 for supporting the duct 170 on the aircraft body 12. The support member 180 is a hollow cylindrical body located inside the rotor 114 and extending along the axis of rotation A1. The support member 180 has a large-diameter section 182 and a guide section 184. The guide section 184 is located behind the large-diameter section 182 and has a smaller diameter than the large-diameter section 182. One longitudinal end of the large-diameter section 182 (the front end of the support member 180) is supported on the aircraft body 12 (fuselage 14 or rear wing 18, etc.). One longitudinal end of the guide section 184 (the rear end of the support member 180) supports the duct hub 174 that constitutes the duct 170. In this state, the large-diameter section 182 supports the rotor 114 via a bearing 179. 【0022】 The support member 180 has an insertion hole 186 that extends along the rotation axis A1. The position of the insertion hole 186 coincides with the rotation axis A1. The actuator 142 and the rod 144 are inserted into the insertion hole 186. The actuator 142 may be positioned outside the insertion hole 186. 【0023】 Figure 3 is a cross-sectional view taken along line III-III in Figure 2. As shown in Figure 3, the guide portion 184 has a slit 188. The slit 188 extends along the axis of rotation A1. The cylindrical portion 152 of the crosshead 150 slidably covers the outer circumference of the guide portion 184. The rod holding portion 154 of the crosshead 150 protrudes from the cylindrical portion 152 toward the rod 144 and passes through the slit 188. The direction of extension of the rod holding portion 154 is perpendicular to the axis of rotation A1 and coincides with the diametrical direction of the support member 180. The rod holding portion 154 has a connecting hole 155 at a position through which the axis of rotation A1 passes. As described above, the rear end 146b of the rod is fixed to this connecting hole 155. 【0024】 In the radial direction of the crosshead 150, a roughly semicircular opening 158 is formed between the cylindrical portion 152 and the rod holding portion 154. As shown in Figure 2, one longitudinal end of the guide portion 184 (the rear end of the support member 180) is exposed so as to face rearward from the opening 158. 【0025】 The duct 170 comprises a cylindrical body 172, a duct hub 174, and a plurality of duct stators 176. The cylindrical body 172 is substantially cylindrical in shape and surrounds the outer circumference of the propeller 100. The duct hub 174 and the plurality of duct stators 176 are located inside the cylindrical body 172. 【0026】 In the duct hub 174, the forward-facing front end is connected to one end of the guide portion 184 in the longitudinal direction (the rear end of the support member 180). The connection is made by joining, for example, by welding. Alternatively, the shape of the front end may be made to correspond to the shape of the slit 188, and the front end may be press-fitted into the slit 188. 【0027】 Multiple duct stators 176 extend radially from the duct hub 174 toward the inner surface of the cylindrical body 172, connecting the duct hub 174 and the cylindrical body 172. As described above, the duct hub 174 is supported by the support member 180, so the multiple duct stators 176 are supported by the support member 180 via the duct hub 174, and the cylindrical body 172 is supported by the support member 180 via the multiple duct stators 176 and the duct hub 174. 【0028】 In the duct 170, the direction of airflow is from front to back. Therefore, the front of the duct 170 is upstream in the direction of airflow, and the rear of the duct 170 is downstream in the direction of airflow. As can be seen from Figure 2, the duct hub 174 and the multiple duct stators 176 are located downstream of the propeller 100 in the direction of airflow. When the eight lift generating units 30 (see Figure 1) are configured similarly to the propeller device 40A, each of the eight lift generating units 30 has a duct 170 configured as described above. 【0029】 Next, we will explain the operation of the propeller device 40A. 【0030】 When operating the VTOL aircraft 10, first the propeller 34 of the lift generating unit 30 (VTOL rotor) is rotated. This generates lift for the VTOL aircraft 10, causing it to take off. When the VTOL aircraft 10 reaches a predetermined altitude, the propeller 100 of the propeller device 40A (cruise rotor) is then rotated. Specifically, the motor 112A, which is the rotational drive force applying unit 110, is energized. As a result, the rotating sleeve 116 and the propeller 100 rotate together. The rotation of the propeller 100 generates thrust for the VTOL aircraft 10, causing it to move forward. 【0031】 In the propeller device 40A, air is drawn into the cylindrical body 172 from the front opening as the propeller 100 rotates. The air drawn into the cylindrical body 172 is discharged from the rear opening. As described above, within the cylindrical body 172, the duct hub 174 and the duct stator 176 are located downstream of the propeller 100 in the direction of air flow. For this reason, noise in the propeller device 40A is suppressed, as shown in Japanese Patent Application Publication No. 2024-33168. 【0032】 As the propeller 100 rotates, multiple actuation pins 162 rotate along the pin grooves 156. Since the multiple actuation pins 162 are supported by the bearing 160, wear on the multiple actuation pins 162 is avoided. Note that the rod 144 and the crosshead 150 do not rotate when the propeller 100 rotates. 【0033】 To change the pitch angle of multiple blades 102, the operator remotely activates the actuator 142. This causes the rod 144 and the crosshead 150 to move forward as a single unit, as shown in Figure 4. Consequently, the multiple actuation pins 162 held by the crosshead 150 move forward in an arc. As described above, each actuation pin 162 is connected to the base of each blade 102 held by the blade support 130. This causes each blade 102 to oscillate. As a result, the pitch angle of each blade 102 is changed. 【0034】 To rotate each blade 102 back to its original direction, the operator remotely activates the actuator 142, causing the rod 144 and crosshead 150 to move together backward, as shown in Figure 2. As a result, each blade 102 swings back to its original direction, thereby changing the pitch angle of each blade 102 again. 【0035】 As described above, the propeller device 40A includes a pitch angle changing unit 140 for changing the pitch angle of each blade 102, as well as a duct 170. In other words, according to the first embodiment, a propeller device 40A can be configured that includes both the pitch angle changing unit 140 and the duct 170. 【0036】 The first embodiment provides the following effects. 【0037】 As shown in Figure 2, the propeller device 40A includes a pitch angle changing unit 140 for changing the pitch angle of the multiple blades 102. The propeller device 40A further includes a duct 170 having a cylindrical body 172, a duct hub 174, and a duct stator 176. The duct hub 174 and duct stator 176 are located inside the cylindrical body 172, downstream of the multiple blades 102 (propeller 100) in the direction of airflow. 【0038】 Thus, according to the first embodiment, a duct 170 can be provided in a propeller device 40A equipped with a pitch angle changing section 140. 【0039】 The pitch angle changing section 140 has a crosshead 150. When changing the pitch angle of each blade 102, the crosshead 150 can move while being guided by a guide portion 184 of a support member 180 that supports the duct hub 174. This movement allows the crosshead 150 to change the pitch angle of multiple blades 102 via an operating pin 162. 【0040】 Since the crosshead 150 is guided by the guide portion 184 (support member 180) in this way, movement of the crosshead 150 with a misalignment with respect to the rotation axis A1 is avoided. Therefore, each blade 102 can be swung to a desired pitch angle. 【0041】 The pitch angle changing section 140 has a rod 144 to which the crosshead 150 is connected. Meanwhile, the support member 180 has an insertion hole 186 that extends along the rotation axis A1 of the propeller 100. The rod 144 is inserted into the insertion hole 186 so as to be movable relative to the support member 180. 【0042】 By housing the rod 144 in the insertion hole 186 in this manner, the propeller device 40A can be made smaller compared to the case where the rod 144 is positioned outside the support member 180. 【0043】 As shown in Figure 3, the support member 180 has a slit 188 extending along the axis of rotation A1. On the other hand, the crosshead 150 has a rod holder portion 154 that passes through the slit 188 and is located in the insertion hole 186. The rod 144 is connected to this rod holder portion 154. 【0044】 This configuration allows for easy connection between the rod 144 inserted into the insertion hole 186 and the crosshead 150. 【0045】 As shown in Figure 2, the crosshead 150 has a cylindrical portion 152. The cylindrical portion 152 extends along the axis of rotation A1 outside the insertion hole 186. The rod holder portion 154 protrudes from the cylindrical portion 152 toward the rod 144. 【0046】 In this case, the inner surface of the cylindrical portion 152 contacts the outer surface of the guide portion 184 on the support member 180. Therefore, the posture of the crosshead 150 is stabilized. As a result, the rod 144 does not become misaligned with respect to the rotation axis A1. 【0047】 Motor 112A is an inner-rotor type motor in which the rotor 114 is located inside the stator 120. The support member 180 supports the rotor 114 inside the rotor 114 via the bearing 179. 【0048】 With this configuration, when an inner rotor type motor (motor 112A) is used as the rotational driving force application unit 110, the rotor 114 can be reliably rotated. In addition, the support member 180 can support the duct 170. 【0049】 Instead of the crosshead 150, the crosshead 200 shown in Figure 5 may be used. This embodiment will be explained. 【0050】 The crosshead 200 has an inner member 202 and an outer member 204. The inner member 202 is positioned and fixed to the outer circumferential surface of the rear end 146b of the rod 144. The outer member 204 is located on the outer circumferential surface of the inner member 202 in the radial direction of the rod 144 and overlaps the inner member 202 via a crosshead bearing 210. The crosshead bearing 210 interposed between the inner member 202 and the outer member 204 is, for example, a self-aligning bearing. 【0051】 Multiple operating pins 162 are connected to multiple blades 102, for example, via a linkage mechanism 212. However, the linkage mechanism 212 is not mandatory. 【0052】 As the rotating sleeve 116 rotates, the propeller 100 rotates, and the operating pin 162 and outer member 204 rotate together with the rotating sleeve 116. On the other hand, because the crosshead bearing 210 is interposed between the inner member 202 and the outer member 204, the inner member 202 does not rotate. Also, the rod 144 does not rotate. 【0053】 When changing the pitch angle of each blade 102, the rod 144 and inner member 202 move together as described above. Consequently, the crosshead bearing 210 and outer member 204 move in the same direction as the inner member 202. As a result, the operating pin 162 moves in an arc shape. This causes each blade 102 to oscillate. Based on this oscillation, the pitch angle of each blade 102 is changed. 【0054】 A modified example of a different embodiment will be outlined below. In this modified example, the rod 144 is hollow, and the support member 180 is passed through the hollow interior of the rod 144. That is, contrary to Figure 2, the support member 180 is located on the inner circumference side of the rod 144. In this case, the rear end of the support member 180 is exposed from the rear end 146b of the rod, and the duct hub 174 is supported by the rear end of the support member 180. 【0055】 Furthermore, if the actuator 142 interferes with the support member 180 when placed on the rotation axis A1, the actuator 142 is placed at a position off the rotation axis A1. In addition, the actuator 142 and the rod 144 are connected, for example, via a gear train. This allows the rod 144 to be moved by the actuator 142 while avoiding interference between the support member 180 and the actuator 142. 【0056】 In this modified example, as described above, each blade 102 swings as the rod 144 and crosshead 150 move integrally forward or backward. As a result, the pitch angle of each blade 102 is changed. In this embodiment, the crosshead 150 is not guided by the support member 180. 【0057】 Next, with reference to Figure 6, the propeller device 40B according to the second embodiment will be described. Components identical to those shown in Figures 1 to 4 are given the same reference numerals, and detailed explanations are omitted. 【0058】 In the propeller device 40B, the motor 112B has a stator 120 and a rotor 114 surrounding the outer circumference of the stator 120. That is, the motor 112B shown in Figure 6 is a so-called outer rotor type motor in which the stator 120 is located inside the rotor 114. The rotor 114 has a rotating sleeve 116 and a plurality of permanent magnets 118 provided on the inner circumference of the rotating sleeve 116. The stator 120 has an electromagnetic coil 122. A bearing 179a is interposed between the aircraft body 12 (fuselage 14 or rear wing 18) and the forward-facing end of the rotor 114. 【0059】 In the second embodiment, the support member 180 is located inside the stator 120 and extends along the axis of rotation A1. The large-diameter portion 182 of the support member 180 supports the rotor 114 via the bearing 179b. 【0060】 In the second embodiment, as in the first embodiment, each blade 102 swings as the rod 144 and crosshead 150 move integrally forward or backward. As a result, the pitch angle of each blade 102 is changed. 【0061】 Therefore, according to the second embodiment, the same effects as the first embodiment can be obtained. 【0062】 Furthermore, the motor 112B in the second embodiment is an outer rotor type motor in which the stator 120 is located inside the rotor 114. In other words, according to the second embodiment, when the outer rotor type motor (motor 112B) is used as the rotational driving force application unit 110, the rotor 114 can be reliably rotated. In addition, the support member 180 can support the duct 170. 【0063】 In the second embodiment, the crosshead 200 shown in Figure 5 may be used. Also in the second embodiment, following the modifications described above, the rod 144 may be made hollow, and the support member 180 may be passed through the hollow interior of the rod 144. 【0064】 The following additional information is disclosed regarding the above embodiments. 【0065】 (Note 1) The propeller devices (40A, 40B) of the present disclosure are propeller devices provided on an aircraft body (12) for generating lift or thrust on the aircraft body, and include a propeller (100) having a plurality of blades (102), a rotational driving force applying unit (110) for applying rotational driving force to the propeller, and a pitch angle changing unit (140) for changing the pitch angle of the plurality of blades, and further include a cylindrical body (172) surrounding the outer circumference of the propeller, a duct hub (174) located inside the cylindrical body, and a duct stator (176) connecting the duct hub and the cylindrical body, and further include a duct (170) located downstream of the propeller in the direction of air flow within the cylindrical body, and a support member (180) supported by the aircraft body and extending along the rotation axis (A1) of the propeller to support the duct hub. 【0066】 With this configuration, a duct can be further provided to the propeller device that has a pitch angle changing section. 【0067】 (Note 2) In the propeller device described in Appendix 1, the pitch angle changing section has a crosshead (150, 200) that changes the pitch angle by oscillating a plurality of blades, and when changing the pitch angle of the plurality of blades, the crosshead may move while being guided by the support member. 【0068】 In this case, the crosshead is guided by the support member as it moves. Therefore, since the crosshead moves along the axis of rotation, the pitch angle of multiple blades can be changed to a desired pitch angle. 【0069】 (Note 3) In the propeller device described in Appendix 1 or 2, the pitch angle changing section includes a crosshead (150, 200) that changes the pitch angle by oscillating a plurality of blades, and a rod (144) connected to the crosshead, the support member has an insertion hole (186) extending along the axis of rotation, and the rod may be inserted into the insertion hole so as to be movable relative to the support member. 【0070】 In this case, it is easier to miniaturize the propeller device compared to when the rod is positioned outside the support member. 【0071】 (Note 4) In the propeller device described in Appendix 3, the support member has a slit (188) extending along the axis of rotation, the crosshead has a rod holding portion (154) that passes through the slit and is located in the insertion hole, and the rod may be connected to the rod holding portion. 【0072】 This configuration makes it easy to connect the rod inserted into the insertion hole with the crosshead. 【0073】 (Note 5) In the propeller device described in Appendix 4, the crosshead has a cylindrical portion (152) extending along the axis of rotation outside the insertion hole, and the rod holding portion may protrude from the cylindrical portion toward the rod. 【0074】 In this case, the inner surface of the cylindrical part contacts the outer surface of the support member, thus stabilizing the crosshead's position. This prevents the rod from becoming misaligned with the axis of rotation. 【0075】 (Note 6) In the propeller device described in any one of the appendices 1 to 5, the rotational driving force application unit is a motor (112A, 112B) having a stator (120) and a rotor (114), and the support member may rotatably support the rotor via bearings (179, 179b). 【0076】 When a motor is used as the rotational driving force application unit, the rotor and propeller can be reliably rotated. At the same time, the duct can be supported by the support member. 【0077】 While this disclosure has been described in detail, it is not limited to the individual embodiments described above. These embodiments can be added, replaced, modified, partially deleted, etc., in any way that does not depart from the gist of this disclosure or from the intent of this disclosure derived from the claims and their equivalents. These embodiments can also be implemented in combination. For example, the order of operations and processes in the embodiments described above are given as examples only and are not limited thereto. The same applies when numerical values ​​or mathematical formulas are used in the description of the embodiments described above. [Explanation of symbols] 【0078】 10…Vertical Take-Off and Landing (VTOL) aircraft 12…Aircraft 40A, 40B... Propeller device; 100... Propeller 102...Blade 110...Rotational drive force application unit 112A, 112B...Motor 140...Pitch angle changing section 142... Actuator 144... Rod 150, 200... Crosshead 162... Actuator pin 170...Duct 172...Cylinder 174... Duct hub 176... Duct stator 179, 179a, 179b... Bearings 180... Support members 184... Guide section 186... Insertion hole 188... Slit

Claims

[Claim 1] A propeller device provided on an aircraft to generate lift or thrust on the aircraft, A propeller with multiple blades, A rotational driving force application unit that applies rotational driving force to the propeller, A pitch angle changing unit for changing the pitch angle of multiple blades, Equipped with, The propeller has a cylindrical body surrounding its outer circumference, a duct hub located inside the cylindrical body, and a duct stator connecting the duct hub and the cylindrical body, wherein the duct hub and the duct stator are connected to a duct located downstream of the propeller in the direction of airflow within the cylindrical body. A support member supported by the aircraft body and extending along the rotation axis of the propeller to support the duct hub, A propeller device that further enhances this feature. [Claim 2] In the propeller device according to claim 1, the pitch angle changing unit has a crosshead that changes the pitch angle by oscillating a plurality of blades, A propeller device in which, when changing the pitch angle of multiple blades, the crosshead moves while being guided by the support member. [Claim 3] In the propeller device according to claim 1, the pitch angle changing unit includes a crosshead that changes the pitch angle by oscillating a plurality of blades, and a rod connected to the crosshead. The support member has an insertion hole extending along the axis of rotation, A propeller device in which the rod is inserted into the insertion hole so as to be movable relative to the support member. [Claim 4] In the propeller device according to claim 3, the support member has a slit extending along the axis of rotation, The crosshead has a rod holding portion that passes through the slit and is located in the insertion hole, The rod is connected to the rod holder, forming a propeller device. [Claim 5] A propeller device according to claim 4, wherein the crosshead has a cylindrical portion extending along the axis of rotation outside the insertion hole, and the rod holding portion protrudes from the cylindrical portion toward the rod. [Claim 6] In the propeller device according to claim 1, the rotational driving force application unit is a motor having a stator and a rotor, The support member is a propeller device that rotatably supports the rotor via a bearing.

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