Variable-pitch paddle device

Abstract

The utility model provides a variable pitch blade device, which relates to the technical field of unmanned aerial vehicle engines, and comprises a fixed seat fixedly arranged at an air inlet of a supercharger, a plurality of mounting holes are arranged around the fixed seat perpendicular to the air inlet direction, blades of the supercharger are rotatably mounted in the mounting holes, and a guide groove is arranged on the fixed seat along the air inlet direction. The sliding block is arranged in the guide groove in a sliding mode and moves back and forth along the guide groove under the action of the lead screw, a mounting cavity is formed between the sliding block and the fixing base in a surrounding mode, the paddles penetrate through the mounting holes, an eccentric wheel is arranged in the mounting cavity, the outer edge of the eccentric wheel is pushed when the sliding block moves, the paddles are made to rotate, and then the screw pitch between the adjacent paddles is changed. The continuous power output capacity of the unmanned aerial vehicle engine under the dynamic load change is improved, the reliability of the unmanned aerial vehicle engine in complex tasks is enhanced, and the unmanned aerial vehicle engine system is compact in structure, simple in design and suitable for being used in space-limited and large-height-span unmanned aerial vehicle engine systems.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) engine technology, and in particular to a variable pitch propeller device. Background Technology

[0002] In recent years, unmanned aerial vehicles (UAVs) have been widely used in environmental monitoring, surveying, and disaster early warning, especially in complex environments such as plateaus and high altitudes, where the requirements for power systems are increasingly demanding. Traditional naturally aspirated piston engines suffer from significantly reduced intake efficiency at high altitudes due to the substantial decrease in air density, resulting in a significant drop in engine power output and making it difficult to meet the demands of continuous high-altitude flight. Furthermore, traditional exhaust gas turbocharging systems also have certain technological bottlenecks. Their operation requires complex cooling systems to reduce exhaust gas temperature and the use of highly heat-resistant materials in turbine components, leading to higher manufacturing costs and system size.

[0003] Compared to exhaust gas turbochargers, electric turbochargers are driven by an electric motor, avoiding the high-temperature problems associated with exhaust gas turbines. They offer faster response times and can operate at room temperature. Electric turbochargers can more effectively improve intake efficiency, making them particularly suitable for low-temperature and low-pressure environments. However, current electric turbocharging systems still have certain limitations, including issues with system compactness, intelligent blade angle adjustment capabilities, and dynamic adaptation to flight conditions. These limitations make it difficult for existing technologies to provide stable power output and efficient intake regulation under high-altitude environments, sudden load changes, and multi-condition missions. Utility Model Content

[0004] To overcome the shortcomings of existing technologies, the technical problem to be solved by this utility model is to propose a variable pitch blade device, which adopts the following technical solution:

[0005] A variable pitch propeller device, comprising

[0006] A mounting base is fixed to the air inlet of the turbocharger and has several mounting holes arranged around it perpendicular to the air inlet direction. The turbocharger blades are rotatably mounted in the mounting holes. The mounting base is provided with guide grooves along the air inlet direction.

[0007] The slider is slidably disposed in the guide groove and moves back and forth along the guide groove under the action of the lead screw. A mounting cavity is provided around the slider and the fixed seat. The blade passes through the mounting hole and an eccentric wheel is provided in the mounting cavity.

[0008] When the slider moves, it pushes the outer edge of the eccentric wheel, causing the blades to rotate, thereby changing the pitch between adjacent blades.

[0009] As a further improvement, a sliding groove is provided on the inner side of the fixed base, and the slider moves back and forth in the sliding groove. A receiving groove is provided on the outer side of the slider, and the sliding groove and the receiving groove together form the mounting cavity.

[0010] When the slider slides outward, the inner wall of the receiving groove pushes the outer edge of the eccentric wheel outward, increasing the rotation angle of the blade and the pitch; when the slider slides inward, the outer wall of the receiving groove pushes the outer edge of the eccentric wheel inward, decreasing the rotation angle of the blade and the pitch.

[0011] As a further improvement, the blade is provided with a limiting platform, a fixed shaft and an eccentric wheel. The fixed shaft passes through the mounting hole, and the limiting platform and the eccentric wheel abut against the inner and outer sides of the mounting hole, respectively.

[0012] As a further improvement, the inner sidewall of the sliding groove is provided with a plurality of contact surfaces, and a plurality of the mounting holes are respectively provided on the contact surfaces, and the eccentric wheel abuts against the contact surfaces.

[0013] As a further improvement, the top plate and bottom plate of the fixed base along the air intake direction are provided with the above-mentioned guide groove, and the top and bottom of the slider are respectively provided with guide members matching the above-mentioned guide groove, and the cross-section of the above-mentioned guide groove and guide member is rectangular.

[0014] As a further improvement, the aforementioned fixing seat is formed by a base and a top cover fitting together. The base is provided with a first notch, the fixing shaft is installed in the first notch, and the eccentric wheel and the limiting platform respectively abut against the inner and outer sides of the first notch.

[0015] As a further improvement, the top cover is provided with a second notch, which fits together with the first notch to form the mounting hole.

[0016] Further improvements include a turbine motor and a rotary motor, wherein the rotary motor is fixed to the turbocharger, the stator of the turbine motor is fixed to the base of the rotary motor, and the rotor is fixedly connected to the fixed base; the stator and rotor are provided with a clearance channel, and the lead screw passes through the clearance channel to connect to the output end of the rotary motor.

[0017] Further improvements include a housing, which is fixed to the air inlet of the engine body and has a mounting bracket inside, on which the rotary motor is fixed.

[0018] Compared with the prior art, the beneficial effects of this utility model are:

[0019] Firstly, this invention utilizes a drive adjustment mechanism comprised of a fixed base, a slider, a lead screw, and an eccentric wheel. This mechanism creates a structural link where the slider drives the eccentric wheel, which in turn rotates the propeller blades, thereby altering the pitch. This design is compact, has a short motion path, and provides rapid response. The cooperation between the slider, sliding groove, and receiving groove effectively limits the axial displacement of the eccentric wheel, ensuring the stability and consistency of the propeller blade rotation. This enables rapid and precise propeller angle adjustment, dynamically optimizing the air intake, making it suitable for UAV engine booster systems with limited space and high responsiveness requirements.

[0020] Secondly, in this utility model, the fixing base consists of a base and a top cover. The base is provided with a first notch, and the fixing shaft of the blade is installed in the first notch to realize the pre-installation of the blade. After the top cover is closed, the second notch and the first notch form an installation hole to limit the blade. At the same time, the blade limiting platform and the eccentric wheel abut against the inner and outer sides of the installation hole. The contact surface on the inner side of the fixing base makes the eccentric wheel rotate more smoothly. The overall structure is simple and reasonable, and the installation is convenient and reliable.

[0021] Secondly, in this utility model, the rotary motor is fixed to the booster, the stator of the turbine motor is fixed to the base of the rotary motor, and the rotor is fixedly connected to the fixed base; the stator and rotor are provided with a clearance channel, and the lead screw passes through the clearance channel to connect to the output end of the rotary motor. The combined assembly design of the turbine motor and the rotary motor not only realizes independent control of the blade speed and pitch, but also effectively improves the compactness of the system. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0024] Figure 2 This is a schematic diagram of the assembly of the turbocharger in this utility model;

[0025] Figure 3 A schematic diagram of the system framework for driving the device of this utility model;

[0026] Figure 4 This is an exploded view of the structure of this utility model;

[0027] Figure 5 This is a schematic diagram of the assembly structure of the fixed base in this utility model;

[0028] Figure 6 This is a schematic diagram of the blade structure in this utility model.

[0029] Figure label:

[0030] 1-Drive adjustment mechanism; 2-Sensor module; 3-Control module; 4-Turbine motor; 5-Housing;

[0031] 11-Fixed base; 11a-Top cover; 11b-Base; 12-Slider; 13-Lead screw; 14-Paddle; 15-Rotary motor;

[0032] 11a-Top cover; 11b-Base; 11a1-Second notch; 11b1-First notch; 111-Mounting hole; 112-Sliding groove; 113-Guide groove; 114-Mating surface; 121-Accommodating groove; 122-Guide component; 141-Fixed shaft; 142-Eccentric wheel; 143-Limiting platform;

[0033] 21-Speed ​​sensor; 22-Pressure sensor; 23-Temperature sensor;

[0034] 41-Stator; 42-Rotor;

[0035] 51-Mounting bracket;

[0036] 100-Booster. Detailed Implementation

[0037] To facilitate understanding by those skilled in the art, the structure of this utility model will now be described in further detail with reference to the accompanying drawings:

[0038] In the description of this utility model, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. The terms "part," "side," "end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation; therefore, they should not be construed as limitations on this utility model.

[0039] This utility model provides a variable pitch propeller device, such as Figure 3 The schematic diagram of the system framework for driving this device shows a drive adjustment mechanism 1, a sensor module 2, and a control module 3. Figure 2 The piston-type turbocharged engine shown has a turbocharger 100 installed at the air intake. The drive adjustment mechanism 1 includes the variable pitch blade device of this technical solution, such as... Figures 2-5 As shown, it specifically includes a mounting base 11 disposed at the air inlet of the booster 100, such as... Figure 1As shown, a slider 12 is provided inside the fixed base 11, and a lead screw 13 drives the slider 12 to move back and forth along the axial direction of the fixed base 11. An installation cavity is provided around the fixed base 11 and the slider 12, and the fixed base 11 is provided with a plurality of installation holes 111 at corresponding positions in the installation cavity. The fixed shaft 141 of the blade 14 is rotatably disposed in the installation hole 111, and an eccentric wheel 142 is provided in the installation cavity. When the slider 12 moves, it pushes the outer edge of the eccentric wheel 142, causing the blade 14 to rotate, thereby changing the pitch between adjacent blades 14.

[0040] The above design enables precise adjustment of the propeller blade pitch 14, enhancing the adaptability of the supercharger 100 to varying flight altitudes and loads. Especially at high altitudes, increasing air intake and optimizing engine power output effectively reduces power loss and improves the sustained flight capability and stability of the UAV.

[0041] In one specific embodiment, such as Figures 1-3 As shown, the drive adjustment mechanism 1 is located at the air inlet of the booster 100. The fixed base 11 is used to fix the blades, and its outer contour is cylindrical. The blades are arranged around the side of the cylinder. The fixed base 11 is hollow inside and the aforementioned slider 12 is sleeved thereon. A sliding groove 112 is provided on the inner side of the fixed base 11. The slider 12 moves back and forth in the sliding groove 112. For ease of understanding, the air inlet direction is defined as from the outside to the inside. The slider 12 can slide inward or outward inside the fixed base 11, and the sliding area is limited to the sliding groove 112.

[0042] In the above embodiments, such as Figure 1 and Figure 4 As shown, it also includes a housing 5, which is fixed to the engine body. Inside the housing 5 is a mounting bracket 51, on which a rotary motor 15 and a turbine motor 4 are fixed. The output end of the rotary motor 15 is connected to the aforementioned lead screw 13, and the output end of the turbine motor 4 is connected to the aforementioned fixed base 11, for driving the fixed base 11 to rotate, that is, driving the blades 14 to rotate and intake air. Preferably, as... Figure 3 As shown, a mounting bracket 51 is provided on the lower side inside the aforementioned housing 5. A rotary motor 15 and a turbine motor 4 are sequentially fixedly mounted on the mounting bracket 51. More specifically, the turbine motor 4 is a brushless motor, including a stator 41 and a rotor 42. The stator 41 is fixedly mounted on the upper surface of the rotary motor 15 body, driving the rotor 42 to rotate. Furthermore, the stator 41 and rotor 42 are hollowed out in the middle, forming a clearance channel allowing the lead screw 13 to pass through. The lead screw 13 passes through the hollowed-out area in the middle of the rotor 42 and stator 41, connecting to the output end of the rotary motor 15. The aforementioned mounting base 11 is fixedly mounted on the rotor 42. This structure enables the combined assembly of the rotary motor 15 and the turbine motor 4, achieving separate control of the speed adjustment and pitch adjustment of the blade 14, and significantly reducing the internal space of the turbocharger 100.

[0043] like Figure 1 and Figure 4 As shown, a receiving groove 121 is provided on the outer side of the slider 12, and the sliding groove 112 and the receiving groove 121 together form the aforementioned mounting cavity. When the slider 12 slides outward, the inner sidewall of the receiving groove 121 pushes the outer edge of the eccentric wheel 142 outward, increasing the rotation angle of the blade 14 and the pitch. When the slider 12 slides inward, the outer sidewall of the receiving groove 121 pushes the outer edge of the eccentric wheel 142 inward, decreasing the rotation angle of the blade 14 and the pitch. Preferably, the inner and outer sides of the outer edge of the eccentric wheel 142 abut against the inner and outer side plates of the receiving groove 121, respectively.

[0044] like Figure 1 and Figure 4 As shown, the lead screw 13 is located at the center of the fixed base 11 and the slider 12. The slider 12 is threadedly connected to the lead screw 13. The fixed base 11 is provided with a guide groove 113, and the slider 12 is provided with a guide member 122. The guide member 122 passes through the guide groove 113. This structure is also used to prevent the slider 12 from rotating. Preferably, the top plate and bottom plate of the fixed base 11 along the air intake direction are provided with the above-mentioned guide groove 113. Correspondingly, the top and bottom of the slider 12 are provided with corresponding guide members 122. The guide groove 113 and the guide member 122 are rectangular or other polygonal in shape, which allows the slider 12 to slide along the guide groove 113 and also restricts its rotation around the lead screw 13.

[0045] like Figure 4 and Figure 5 As shown, the inner sidewall of the fixed base 11 is provided with several contact surfaces 114, and the eccentric wheel 142 of the blade 14 contacts or abuts the contact surfaces 114 so that it can rotate more smoothly.

[0046] like Figure 4 and Figure 5 As shown, in one embodiment, the fixing seat 11 consists of a base 11b and a top cover 11a. The base 11b is provided with a first notch 11b1, and the top cover 11a is provided with a corresponding second notch 11a1. When the top cover 11a is placed on the base 11b, the first notch 11b1 and the second notch 11a1 fit together to form the aforementioned mounting hole 111. During installation, the slider 12 is placed inside the base 11b, and the blade 14 is placed sequentially along the first notch 11b1 of the base 11b. Then, the top cover 11a is placed on top to complete the assembly of the fixing seat 11, the slider 12, and the blade 14.

[0047] like Figure 4 and Figure 5As shown, in one embodiment, the inner sidewall of the sliding groove 112 is provided with ten mating surfaces 114 of equal length. Preferably, the mating surfaces 114 are planes, that is, the inner contour of the fixed base 11 from the top view is a regular decagon. Each mating surface 114 is provided with a corresponding mounting hole 111. More specifically, both the base 11b and the top cover 11a are provided with ten mating surfaces 114. The base 11b is provided with a first notch 11b1 corresponding to each mating surface 114. Similarly, the top cover 11a is provided with a second notch 11a1 corresponding to each mating surface 114. In this embodiment, a total of ten blades 14 are installed. During installation, the eccentric wheel 142 is mated to the mating surfaces 114 of the base 11b and the top cover 11a.

[0048] Furthermore, such as Figure 6 As shown, a limiting platform 143 is provided on the side of the fixed shaft 141 away from the eccentric wheel 142. The limiting platform 143 and the eccentric wheel 142 respectively abut against the inner and outer sides of the mounting hole 111. Figures 4-6 As shown in the above embodiment, the fixed shaft 141 of the blade 14 is placed in the first notch 11b1 of the base 11b, and the limiting platform 143 and the eccentric wheel 142 abut against the inner and outer sides of the first notch 11b1 respectively, forming a pre-installation. Preferably, the outer side of the fixed base 11 is provided with a contact surface 114 corresponding to the inner side. The outer contact surface 114 is used to contact the limiting platform 143, and its function is also to make the blade 14 rotate more smoothly.

[0049] like Figure 3 As shown, this system further includes a sensor module 2, specifically including a speed sensor 21, a pressure sensor 22, and a temperature sensor 23, used to monitor engine speed R, ambient air pressure P, and engine intake air temperature T, respectively. It also includes a control module 3, electrically connected to the sensor module 2, which generates the target pitch L. tgt and target turbine speed n tgt The system outputs control signals to control the rotation of the lead screw 13 via the rotary motor 15, adjusting the pitch between adjacent blades 14, and adjusting the turbine speed via the turbine motor 4. It should be noted, and understood uniformly, that the parallel distance between adjacent blades 14 is the aforementioned pitch. When the deflection angle of the blades 14 increases, the pitch increases; when the deflection angle of the blades 14 decreases, the pitch decreases; and when the blades 14 (under permissible conditions) are perpendicular to the air intake direction, the pitch is zero.

[0050] Furthermore, the target pitch L tgt and target turbine speed n tgt The following condition must be met:

[0051] n tgt ·L tgt =f·T·R / P;

[0052] Where f is a preset proportional constant, R is the engine speed, T is the intake air temperature, and P is the ambient air pressure.

[0053] Based on conditional n tgt ·L tgt =f·T·R / P, generating multiple sets of parameter combinations that meet the conditions, and selecting the target parameter combination from the multiple sets of parameter combinations. The selection methods include:

[0054] In energy-saving mode, the pre-stored power consumption database is called, and the target pitch L with the lowest power consumption is selected by looking up the table. tgt With the target turbine speed n tgt Parameter combinations;

[0055] Maintain the target turbine speed n during sudden load changes. tgt Constant, and adjust the target pitch L tgt To achieve rapid response.

[0056] The specific derivation of the above conditional expression is as follows:

[0057] Calculate the intake air volume Q of turbocharger 100 IN :

[0058] Q IN =η M ·k·n·L·ρ·f(Re,…);

[0059] Where, η M The mechanical efficiency is dimensionless and ranges from 0 to 1; k is the proportionality constant of the geometry of the reaction fan or pump; n is the turbine speed; L is the pitch of the blade 14; ρ is the intake air density; f(Re,…) represents a function related to fluid dynamics, including but not limited to Reynolds number Re, density, viscosity, and other relevant fluid properties. The aforementioned mechanical efficiency η… M The proportionality constant k and the function f(Re,…) are constant values ​​that can be measured from time-based experimental data. To simplify calculations, a combined fixed value a=η is introduced. M ·k·f(Re,…) reflects the efficiency and mechanical structure parameters of the intake system, then the intake volume Q of the turbocharger 100 is... IN =a·n·L·ρ;

[0060] Calculate the gas consumption Q of an internal combustion engine EXP :

[0061] Q EXP =η V ·ρ·V·R / 2;

[0062] Where, η VThe volumetric efficiency is dimensionless and ranges from 0 to 1; ρ is the intake air density; V is the engine displacement; and R is the engine speed. The volumetric efficiency η mentioned above... V And the engine displacement V is a constant that can be measured from time-based experimental data. We introduce a combined fixed value b=η V V / 2 reflects the engine's displacement volumetric efficiency, while the gas consumption Q is... EXP =b·ρ·R.

[0063] To enable a drone to achieve the same air intake volume at high altitudes as it would at zero altitude, normal temperature (20℃), and air density ρ0, i.e.

[0064] a·n·L·ρ=Q IN =Q EXP0 =b·ρ0·R;

[0065] After simplification, we get: n·L=b·ρ0·R / a·ρ;

[0066] Where ρ0=P0 / (S·T0) and ρ=P / (S·T), S is the gas constant of air (unit: J / (kg·K), approximately 287J / (kg·K)), P is atmospheric pressure, and T is the intake temperature.

[0067] That is, n·L=b·P0·T·R / (a·P·T0), and a preset proportionality constant is introduced.

[0068] f = P0·b / (T0·a;

[0069] Where T0 is 20℃ and P0 is the atmospheric pressure at 20℃;

[0070] We obtain n·L=f·T·R / P, which is the target pitch L. tgt With the target turbine speed n tgt Satisfy: n tgt ·L tgt =f·T·R / P.

[0071] As one example, the target turbine speed n tgt The adjustment range is 1000rps~6000rps. Sampling points are selected at 500rps intervals to calculate the pitch at the corresponding speed and record the lowest power point of each sampling point to generate a power consumption database.

[0072] As one embodiment, the rotation angle range of the blade 14 is 0~60°, and the target pitch L tgt The rotation angle of the propeller blade 14 is mapped through the function L=g(α), and the control module 3 determines the target pitch L based on this mapping. tgt Calculate the rotation angle.

[0073] This utility model further provides a control method for a drone engine booster system, applied to the aforementioned drone engine booster system, comprising the following steps:

[0074] S1: Real-time engine speed, ambient air pressure and intake air temperature are obtained through speed sensor 21, air pressure sensor 22 and temperature sensor 23;

[0075] S2: Obtain the target pitch L that satisfies the condition based on the conditional expression n·L=f·T·R / P. tgt and target turbine speed n tgt Multiple parameter combinations;

[0076] S3: Call the pre-stored power consumption database and select the target pitch L with the lowest power consumption. tgt With the target turbine speed n tgt Parameter combinations;

[0077] S4: Control module 3 drives rotary motor 15 to move slider 12, adjusts the rotation angle of blade 14 through function L=g(α), and thus adjusts the pitch between adjacent blades 14; drives turbine motor 4 to adjust turbine speed;

[0078] S5: Control module 3 dynamically calculates the target value V based on real-time collected engine speed, ambient air pressure, and intake air temperature. target =f·T·R / P, and compare the real-time n·L with the target value V. target Comparison, if the error is |n·LV target | If the set tolerance is exceeded, the target pitch L will be corrected. tgt and target turbine speed n tgt .

[0079] In step S3, if a sudden load change occurs, maintain the target turbine speed n. tgt Keep it unchanged, adjust the target pitch L tgt satisfying condition n tgt ·L tgt =f·T·R / P.

[0080] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A variable pitch propeller device, characterized in that, include: The fixed base (11) is fixed to the air inlet of the booster (100) and has a number of mounting holes (111) arranged around it perpendicular to the air inlet direction. The blades (14) of the booster (100) are rotatably installed in the mounting holes (111). The fixed base (11) is provided with guide grooves (113) along the air inlet direction. The slider (12) is slidably disposed in the guide groove (113) and moves back and forth along the guide groove (113) under the action of the lead screw (13). An installation cavity is provided around the slider (12) and the fixed seat (11). The blade (14) passes through the installation hole (111) and an eccentric wheel (142) is provided in the installation cavity. When the slider (12) moves, it pushes the outer edge of the eccentric wheel (142), causing the blade (14) to rotate, thereby changing the pitch between adjacent blades (14).

2. The variable pitch propeller device as described in claim 1, characterized in that, The inner side of the fixed base (11) is provided with a sliding groove (112), the slider (12) moves back and forth in the sliding groove (112), and the outer side of the slider (12) is provided with a receiving groove (121). The sliding groove (112) and the receiving groove (121) together form the mounting cavity. When the slider (12) slides outward, the inner wall of the receiving groove (121) pushes the outer edge of the eccentric wheel (142) outward, increasing the rotation angle of the blade (14) and the pitch. When the slider (12) slides inward, the outer wall of the receiving groove (121) pushes the outer edge of the eccentric wheel (142) inward, decreasing the rotation angle of the blade (14) and the pitch.

3. A variable pitch propeller device as described in claim 2, characterized in that, The blade (14) is provided with a limiting platform (143), a fixed shaft (141) and an eccentric wheel (142). The fixed shaft (141) passes through the mounting hole (111). The limiting platform (143) and the eccentric wheel (142) abut against the inner and outer sides of the mounting hole (111) respectively.

4. A variable pitch blade device as described in claim 3, characterized in that, The inner sidewall of the sliding groove (112) is provided with a plurality of mating surfaces (114), and a plurality of mounting holes (111) are respectively provided on the mating surfaces. The eccentric wheel (142) abuts against the mating surfaces (114).

5. A variable pitch blade device as described in claim 1, characterized in that, The top and bottom plates of the fixed base (11) along the air intake direction are provided with the guide groove (113), and the top and bottom of the slider (12) are respectively provided with guide members (122) matching the guide groove (113). The cross-section of the guide groove (113) and the guide member (122) is rectangular.

6. A variable pitch blade device as described in claim 3, characterized in that, The fixed seat (11) is formed by the base (11b) and the top cover (11a) covering each other. The base (11b) is provided with a first notch (11b1). The fixed shaft (141) is installed in the first notch (11b1), and the eccentric wheel (142) and the limiting platform (143) respectively abut against the inner and outer sides of the first notch (11b1).

7. A variable pitch blade device as described in claim 6, characterized in that, The upper cover (11a) is provided with a second notch (11a1), and the second notch (11a1) and the first notch (11b1) fit together to form the mounting hole (111).

8. A variable pitch blade device as described in claim 1, characterized in that, It also includes a turbine motor (4) and a rotary motor (15), the rotary motor (15) being fixed to the booster (100), the stator (41) of the turbine motor (4) being fixed to the base of the rotary motor (15), and the rotor (42) being fixedly connected to the fixed base (11); the stator (41) and the rotor (42) are provided with a clearance channel, and the lead screw (13) passes through the clearance channel and connects to the output end of the rotary motor (15).

9. A variable pitch blade device as described in claim 8, characterized in that, It also includes a housing (5), which is fixed to the air inlet of the engine body and has a mounting bracket (51) inside it. The rotary motor (15) is fixed to the mounting bracket (51).

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