Integrated single-motor cross-medium propelling device

Abstract

The utility model is suitable for the technical field of aircraft propulsion system design, and provides an integrated single-motor cross-medium propulsion device. Comprising a nacelle, a pneumatic paddle, a pneumatic propeller hub, a pneumatic shaft sleeve, a pneumatic shaft sleeve connecting rod, a pneumatic thrust bearing, a pneumatic one-way bearing, a motor, a motor fixing frame, an electric lead screw, an optical axis, a hydraulic one-way bearing, a hydraulic thrust bearing, a hydraulic shaft sleeve connecting rod, a hydraulic shaft sleeve, a hydraulic propeller hub, a hydraulic paddle and a reduction gear set. The whole motor can move on the lead screw in the nacelle in the axial direction of the nacelle, then the relative position between the engine and the paddle disc is changed so as to adjust the angle between the paddle and the nacelle in the axial direction, and the folded paddle is stored through the opening in the outer wall of the nacelle of the engine so as to achieve more excellent pneumatic and hydrodynamic resistance characteristics. The cross-medium unmanned aerial vehicle can actively select the most suitable propeller under different working conditions, and the fluid resistance under the two main working conditions is reduced to the maximum extent.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft propulsion system design, and in particular relates to an integrated single-motor cross-medium propulsion device. Background Art

[0002] Unmanned aerial vehicles that can achieve air flight and underwater cruising and seamless transition between the two media are gaining increasing attention. Some commonly used existing solutions include multi-rotor solutions, which use the large lift characteristics of multi-rotors to achieve vertical take-off and landing and buoyancy in water, but their load capacity, flight efficiency and speed are not as good as those of fixed-wing aircraft. Fixed-wing cross-medium aircraft have the potential advantages of longer range, greater payload and higher flight speed.

[0003] In the process of research on fixed-wing cross-medium aircraft systems, the design of its propulsion system has a very significant impact on the overall efficiency of the aircraft. Under different medium conditions, the propulsion system designed and installed for a single medium cannot always maintain high propulsion efficiency. Generally, small and medium-sized cross-medium aircraft are generally equipped with at least two propulsion systems to meet the propulsion needs of both underwater and airborne media. However, due to the heavy weight and complex system of the dual-power system, the two propulsion systems can only work under single medium conditions. Summary of the invention

[0004] The purpose of the present invention is to provide an integrated single-motor cross-medium propulsion device, aiming to solve the technical problems existing in the prior art identified in the background technology.

[0005] The present invention is implemented as follows: an integrated single-motor cross-medium propulsion device, the integrated single-motor cross-medium propulsion device comprising:

[0006] A nacelle, on which a hydraulic sleeve is mounted via a pneumatic thrust bearing;

[0007] One side of the nacelle is connected to an aerodynamic hub, on which aerodynamic blades are hinged via a hinge, and one side of the aerodynamic hub is provided with an aerodynamic output shaft, the aerodynamic output shaft is connected to the aerodynamic hub via a pneumatic one-way bearing and is inserted into a pneumatic sleeve;

[0008] A pneumatic sleeve connecting rod is hinged on the ear piece of the pneumatic sleeve, and the other end of the pneumatic sleeve connecting rod is connected to the hinge on the pneumatic blade;

[0009] As a further solution of the present invention, the integrated single-motor cross-medium propulsion device further includes:

[0010] The hydraulic output shaft and the hydraulic propeller hub are connected by a hydraulic one-way bearing and inserted into a hydraulic sleeve. The hydraulic propeller hub is hinged with a hydraulic blade. The hydraulic sleeve connecting rod is hinged on the ear of the hydraulic sleeve. One end of the hydraulic sleeve connecting rod is connected to the hinge on the hydraulic blade.

[0011] The front and rear sides of the nacelle are respectively fixed with screws through screw motors and screw bearings;

[0012] The hydraulic sleeve is installed at the rear of the nacelle through a hydraulic thrust bearing.

[0013] As a further solution of the present invention, a motor fixing ring is arranged inside the nacelle, a disc motor is arranged on the motor fixing ring, and front and rear output shafts of the disc motor are connected to the pneumatic output shaft and the reduction gear set through a first coupling and a second coupling respectively;

[0014] A hydraulic output shaft is provided at the output end of the reduction gear set;

[0015] The motor fixing ring is provided with two sliding grooves and an optical axis, and the disc motor and the motor fixing ring slide upward along the nacelle on the optical axis;

[0016] The motor fixing ring is fixedly connected to a screw slider, and is used to enable the motor fixing ring to move upward in the nacelle along the screw.

[0017] As a further solution of the present invention, both ends of the screw are fixed to the front and rear sides of the nacelle through a screw motor and a screw bearing respectively.

[0018] As a further solution of the present invention, the reduction gear set includes a planetary gear set, the screw motor outputs to the sun gear of the planetary gear set, the hydraulic output shaft is connected to the planetary carrier, and the ring gear is fixed as the reduction set housing.

[0019] The beneficial effects of the present invention are:

[0020] The present invention proposes a compact and efficient integrated single-motor trans-medium propulsion device, which takes into account both propulsion efficiency and rectification shape, and can be used for small and medium-sized trans-medium aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 An internal structural diagram of an integrated single-motor cross-medium propulsion device provided by an embodiment of the present invention;

[0022] Figure 2 This is the side view of the aerial mode;

[0023] Figure 3 This is an aerial mode diagram;

[0024] Figure 4It is a side view of the aerodynamic propeller structure in the air mode;

[0025] Figure 5 This is the structure diagram of the aerodynamic propeller in the air mode;

[0026] Figure 6 It is an internal side view of the aerodynamic propeller structure in the air mode;

[0027] Figure 7 This is a three-dimensional diagram of the interior of the aerodynamic propeller structure in the air mode;

[0028] Figure 8 This is a side view of the water propellers folded in air mode;

[0029] Fig. 9 This is the folding diagram of the liquid propeller in the air mode;

[0030] Fig.10 This is a side view of the interior of the folded propeller in air mode.

[0031] Fig.11 A three-dimensional diagram of the interior of the liquid propeller folded in the air mode;

[0032] Fig.12 Side view of the pneumatic propeller folded for underwater mode;

[0033] Fig.13 This is the folding diagram of the pneumatic propeller in underwater mode;

[0034] Fig.14 Internal side view of the pneumatic propeller folded for underwater mode;

[0035] Fig.15 A three-dimensional view of the interior of the pneumatic propeller folded for underwater mode;

[0036] Fig.16 Open side view for underwater mode hydraulic propeller;

[0037] Fig.17 Open the diagram for the underwater mode hydraulic propeller;

[0038] Fig.18 Open interior side view for underwater mode hydraulic propeller;

[0039] Fig.19 Open interior stereogram for the underwater mode hydraulic propeller;

[0040] Fig. 20 It is a side view of the disc motor moving mechanism;

[0041] Fig.21 It is a three-dimensional diagram of the disc motor moving mechanism;

[0042] Fig. 22 This is the nacelle structure diagram.

[0043] In the attached drawings, 101, pneumatic hub; 102, pneumatic one-way bearing; 103, pneumatic sleeve; 104, pneumatic sleeve connecting rod; 105, pneumatic thrust bearing; 106, pneumatic blade; 107, nacelle; 108, pneumatic output shaft; 109, screw motor; 110, screw; 111, screw bearing; 112, first coupling; 113, disc motor; 114, second coupling; 115, reduction gear set; 116, optical axis; 117, thrust bearing; 118, hydraulic hub; 119, hydraulic sleeve; 120, hydraulic sleeve connecting rod; 121, hydraulic blade; 122, hydraulic one-way bearing; 123, hydraulic output shaft; 124, motor fixing ring. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0045] It is understood that the terms "first", "second", etc. used in this application may be used herein to describe various elements, but unless otherwise specified, these elements are not limited by these terms. These terms are only used to distinguish a first element from another element. For example, without departing from the scope of this application, a first xx script may be referred to as a second xx script, and similarly, a second xx script may be referred to as a first xx script.

[0046] like Figures 1 to 3 As shown, the pneumatic blade 106 is hinged to the pneumatic hub 101 through a hinge of its own design, the pneumatic output shaft 108 is connected to the pneumatic hub 101 through a pneumatic one-way bearing 102 and inserted into the pneumatic sleeve 103, the pneumatic sleeve connecting rod 104 is hinged to the ear of the pneumatic sleeve 103, and the other end of the pneumatic sleeve connecting rod 104 is connected to the hinge on the pneumatic blade 106, and the pneumatic sleeve 103 is installed at the front of the nacelle 107 through a pneumatic thrust bearing 105.

[0047] Similarly, the hydraulic blade 121 is hinged on the hydraulic hub 118 through a hinge designed by itself, the hydraulic output shaft 123 is connected to the hydraulic hub 118 through a hydraulic one-way bearing 122 and inserted into the hydraulic sleeve 119, the hydraulic sleeve connecting rod 120 is hinged on the ear piece of the hydraulic sleeve 119, and the other end of the hydraulic sleeve connecting rod 120 is connected to the hinge on the hydraulic blade 121, and the hydraulic sleeve 119 is installed at the rear of the nacelle 107 through a hydraulic thrust bearing 117. The actuation directions allowed by the two one-way bearings at the front and rear are opposite.

[0048] In order to avoid damage to the disc motor 113 due to excessive damping in water, the front and rear output shafts of the disc motor 113 are connected to the pneumatic output shaft 108 and the reduction gear set 115 through the first coupling 112 and the second coupling 114 respectively. The output shaft of the reduction gear set is the hydraulic output shaft 123. The disc motor 113 is fixed on the motor fixing ring 124. The two slide grooves on the motor fixing ring 124 allow the disc motor 113 and the motor fixing ring 124 to slide upward along the nacelle axis on the optical axis 116. The motor fixing ring 124 is also fixed to a screw slider to allow it to move along the screw 110 in the nacelle axis. The two ends of the screw 110 are fixed to the front and rear sides of the nacelle 107 through the screw motor 109 and the screw bearing 111 respectively. The reduction gear set 115 includes a set of planetary gear sets. The screw motor 109 outputs to the sun gear of the planetary gear set. The hydraulic output shaft is connected to the planet carrier, and the ring gear is fixed as the reduction set housing.

[0049] When the pneumatic propeller is folded, the pneumatic blades 106 are folded around the hinge axis toward the nacelle 107 and are limited in the folded position by the screw 110. Similarly, when the hydraulic propeller is folded, the hydraulic blades 121 are folded back toward the nacelle and are also limited in the folded position by the screw 110.

[0050] like Figures 1 to 22 As shown, when the trans-medium aircraft needs to use the pneumatic blades 106 to fly in the air, the screw motor 109 controls the motor fixing ring 124 to move toward the front of the nacelle 107 through the screw 110, so that the motor fixing ring 124 and the disc motor 113 drive the pneumatic output shaft 108 and the pneumatic hub 101 to slide forward axially. Because the pneumatic hub 101, the pneumatic blades 106, the pneumatic sleeve 103 and the pneumatic sleeve connecting rod 104 are all connected by hinges, and one end of the pneumatic sleeve connecting rod 104 is installed on the pneumatic sleeve 103, and the pneumatic sleeve 103 is installed on the nacelle 107 through the pneumatic thrust bearing 105 and cannot slide along the nacelle axial direction, under the action of the screw motor 109, the distance between the connecting hinges of the pneumatic sleeve connecting rod 104 and the pneumatic hub 101 and the connecting hinges of the pneumatic sleeve connecting rod 104 and the pneumatic sleeve 103 becomes smaller, so the pneumatic sleeve connecting rod 104 can only be unfolded through the hinge on the pneumatic blade 106, so that the angle between the radial direction of the pneumatic blade 106 and the axial direction of the nacelle 107 increases, and the pneumatic blade 106 is unfolded.

[0051] At the same time, the gear reduction group 115 and the hydraulic output shaft 123 also slide forward axially under the drive of the screw motor 109, because the hydraulic hub 118, the hydraulic blade 121, the hydraulic sleeve 119 and the hydraulic sleeve connecting rod 120 are all connected by hinges, and one end of the hydraulic sleeve connecting rod 120 is installed on the hydraulic sleeve 119, and the hydraulic sleeve 119 is installed on the nacelle 107 through the hydraulic thrust bearing 117 and cannot slide axially along the nacelle. Therefore, under the action of the screw motor 109, the distance between the connecting hinges of the hydraulic sleeve connecting rod 120 and the hydraulic hub 118 and the connecting hinges of the hydraulic sleeve connecting rod 120 and the hydraulic sleeve 119 is reduced. Therefore, the hydraulic sleeve connecting rod 120 can only be unfolded through the hinge on the hydraulic blade 121, so that the angle between the radial direction of the hydraulic blade 121 and the axial direction of the nacelle 107 is reduced, and the hydraulic blade 121 is retracted to the tail of the nacelle.

[0052] At this time, the disc motor 113 is started, and the pneumatic output shaft 108 and the hydraulic output shaft 123 respectively drive the two one-way bearings 102 / 122 installed in opposite directions to rotate, so that the tail hydraulic blade 121 stops and only the pneumatic blade 106 is driven to rotate.

[0053] When the pneumatic blades 106 are folded, the screw motor 109 actuates in the opposite direction, driving the motor fixing ring 124, the disc motor 113 and the pneumatic hub 101 to slide backward along the axial direction, compressing the pneumatic sleeve connecting rod 104. The other end of the pneumatic sleeve connecting rod 104 is mounted on the pneumatic sleeve 103, and the pneumatic sleeve 103 is mounted on the nacelle 107 through the pneumatic system thrust bearing 105, and cannot slide along the fuselage direction. Therefore, the pneumatic sleeve connecting rod 104 shrinks inward, and the pneumatic blades 106 also shrink inward through the hinge. At this time, the pneumatic blades 106 are folded to the corresponding position of the nacelle 107. At the same time, the hydraulic hub 118 slides backward along the nacelle axial direction under the drive of the screw motor 109, shrinking the hydraulic sleeve connecting rod 120, so that the angle between the radial direction of the hydraulic blades 121 and the axial direction of the nacelle 107 increases, and the hydraulic blades 121 are opened.

[0054] At this time, the disc motor is started in the opposite direction, and the pneumatic output shaft 108 and the hydraulic output shaft 123 respectively drive the two one-way bearings 102 / 122 installed in opposite directions to rotate, so that the front pneumatic blade 106 stops and only drives the hydraulic blade 121 to rotate.

[0055] It should be understood that, although each step in the flow chart of each embodiment of the present invention is shown in sequence according to the indication of the arrow, these steps are not necessarily performed in sequence according to the order indicated by the arrow. Unless there is a clear explanation in this article, the execution of these steps does not have a strict order restriction, and these steps can be performed in other orders. Moreover, at least a portion of the steps in each embodiment may include a plurality of sub-steps or a plurality of stages, and these sub-steps or stages are not necessarily performed at the same time, but can be performed at different times, and the execution order of these sub-steps or stages is not necessarily performed in sequence, but can be performed in turn or alternately with at least a portion of other steps or sub-steps or stages of other steps.

[0056] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the program can be stored in a non-volatile computer-readable storage medium. When the program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory may include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM) or flash memory. Volatile memory may include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM is available in many forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), memory bus (Rambus) direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).

[0057] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0058] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent of the present invention. It should be pointed out that, for ordinary technicians in this field, several variations and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be subject to the attached claims.

[0059] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An integrated single-motor cross-medium propulsion device, characterized in that: The integrated single-motor cross-medium propulsion device comprises: A nacelle (107), wherein a hydraulic sleeve (119) is mounted on the nacelle (107) via a pneumatic thrust bearing (105); One side of the nacelle (107) is connected to an aerodynamic hub (101), and an aerodynamic blade (106) is hingedly connected to the aerodynamic hub (101) via a hinge. A pneumatic output shaft (108) is provided on one side of the aerodynamic hub (101), and the pneumatic output shaft (108) is connected to the aerodynamic hub (101) via a pneumatic one-way bearing (102) and is inserted into a pneumatic shaft sleeve (103); A pneumatic sleeve connecting rod (104) is hinged on the ear piece of the pneumatic sleeve (103), and the other end of the pneumatic sleeve connecting rod (104) is connected to a hinge on the pneumatic blade (106).

2. The integrated single-motor cross-medium propulsion device according to claim 1, characterized in that: The integrated single-motor cross-medium propulsion device also includes: A hydraulic output shaft (123) and a hydraulic impeller hub (118) are connected via a hydraulic one-way bearing (122) and inserted into a hydraulic shaft sleeve (119); a hydraulic impeller blade (121) is hingedly connected to the hydraulic impeller hub (118); a hydraulic shaft sleeve connecting rod (120) is hingedly connected to an ear piece of the hydraulic shaft sleeve (119); one end of the hydraulic shaft sleeve connecting rod (120) is connected to a hinge on the hydraulic impeller blade (121); The front and rear sides of the nacelle (107) are respectively fixed with screws (110) via screw motors (109) and screw bearings (111); The hydraulic sleeve (119) is installed at the rear of the nacelle (107) via a hydraulic thrust bearing (117).

3. The integrated single-motor cross-medium propulsion device according to claim 2, characterized in that: A motor fixing ring (124) is arranged inside the nacelle (107), a disc motor (113) is arranged on the motor fixing ring (124), and front and rear output shafts of the disc motor (113) are connected to the pneumatic output shaft (108) and the reduction gear set (115) through a first coupling (112) and a second coupling (114) respectively; The output end of the reduction gear set (115) is provided with a hydraulic output shaft (123); The motor fixing ring (124) is provided with two sliding grooves and an optical axis (116), and the disc motor (113) and the motor fixing ring (124) slide upward along the nacelle (107) on the optical axis (116); The motor fixing ring (124) is fixedly connected to a screw slider, and is used to enable the motor fixing ring (124) to move axially upward in the nacelle (107) along the screw (110).

4. The integrated single-motor cross-medium propulsion device according to claim 3 is characterized in that: The two ends of the screw rod (110) are respectively fixed to the front and rear sides of the nacelle (107) through a screw rod motor (109) and a screw rod bearing (111).

5. The integrated single-motor cross-medium propulsion device according to claim 3, characterized in that: The reduction gear set (115) includes a planetary gear set, the screw motor (109) outputs to the sun gear of the planetary gear set, the hydraulic output shaft (123) is connected to the planet carrier, and the ring gear is fixed as the reduction set housing.

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