98 results about "Variable pitch propeller" patented technology

The invention provides a section-operation-power system joint optimization design method for an electric vertical take-off and landing aircraft. The method comprises the following steps: defining a power system design variable, a section design variable and an operation optimization variable of the electric vertical take-off and landing aircraft; a power system quality model, an aircraft profile demand analysis model, a variable pitch propeller operation performance model and a motor operation performance model are established; power system design and operation control plan making of the electric vertical take-off and landing aircraft are combined, section-operation-power system joint optimization design of the electric vertical take-off and landing aircraft is achieved, and the characteristic of great difference between the wide-speed-range operation characteristic of a variable-pitch propeller and the hovering and cruising flight stage of the vertical take-off and landing aircraft is considered to the maximum extent. And compared with the design of firstly carrying out physical system design and then carrying out operation control design, the optimal design of the overall performance of the aircraft is realized.

A propeller controller for a variable-pitch propeller of an aircraft is provided. The controller is configured to determine a requested oil flow for delivery to a hydraulic actuator of the variable-pitch propeller based on a speed error between an actual rotational speed of the variable-pitch propeller and a set point rotational speed for the variable-pitch propeller, determine a requested oil flow for delivery to the hydraulic actuator based on the speed error, determine a trimmed oil leakage rate out of the hydraulic actuator by multiplying an estimated oil leakage rate out of the hydraulic actuator by a leakage trim multiplier based on the speed error, and combine the trimmed oil leakage rate with the requested oil flow to generate a commanded oil flow. The commanded oil flow is delivered to the hydraulic actuator to adjust the pitch of the variable-pitch propeller.

Methods and system are described for operating an aircraft powerplant comprising an engine coupled to a variable-pitch propeller. The method comprises receiving a request to change a propeller rotational speed from a first setting to a second setting, determining a power need for the engine, when the power need corresponds to the second setting, modifying a command for at least one of fuel flow to the engine and oil flow to the propeller to govern the powerplant in accordance with the second setting for the propeller rotational speed, and when the power need does not correspond to the second setting, overriding the request to change the propeller rotational speed from the first setting to the second setting.

The invention provides a variable pitch propeller speed regulator bench test platform and method. The test platform comprises a simulation computer, an electronic controller, a variable pitch power device and a variable pitch execution device. Wherein the simulation computer is used for operating the engine simulation model and the propeller simulation model. Providing real-time data of control parameters such as power and rotating speed based on the simulation model, and participating in a control logic loop of a tested object, namely a speed regulator; the speed regulator and the electronic controller are used for controlling the rack test platform to complete corresponding actions by inputting and outputting actual physical quantities and electronic signals so as to reflect the function and the performance of a tested object; based on the variable-pitch power device and the variable-pitch execution device, power is provided or actions are executed, and the speed regulator is supported to achieve corresponding actual actions. Functional test and performance test of the speed regulator can be realized with low cost and high confidence.

The automatic feathering mechanism comprises a variable-pitch disc, a sliding groove is formed in the side wall of the variable-pitch disc, the sliding groove is in sliding connection with a propeller handle variable-pitch pin, a through hole is formed in the center of the variable-pitch disc, a variable-pitch nut is arranged in the through hole of the variable-pitch disc, and the variable-pitch nut is connected with the variable-pitch disc. The variable-pitch nut is internally in threaded connection with a variable-pitch lead screw, a lower limiting piece is arranged at the lower end of the variable-pitch lead screw, and an upper limiting piece is arranged at the upper end of the variable-pitch lead screw; the variable-pitch disc is connected with the variable-pitch nut in a sliding mode, and a limiting seat is arranged on the outer wall of the variable-pitch nut and located above the variable-pitch disc; the paddle handle variable pitch pin is eccentrically connected with a paddle handle of the paddle, and the axis of the paddle handle of the paddle is not coaxial with the pneumatic center of the paddle. After the power motor fails, unpowered fast feathering can be achieved, fuselage resistance is reduced, and the possibility of safe landing of the aircraft is increased.

The present invention discloses a variable-pitch propeller design verification method and a dedicated simulation test device. The method adopts a variable-pitch propeller design verification method based on blade engineering multi-segment three-dimensional surface elements and PSP surface pressure distribution measurement technology. There is no need to use a large-scale wind tunnel to test the propeller, nor does it require a high-power engine / motor to drive the propeller to rotate. Only the surface pressure distribution of a series of three-dimensional surface elements needs to be measured in the test device proposed by the present invention. The method has the advantages of being applicable to a wide range of propellers, a relatively simple test system, low cost and high efficiency. It has more prominent advantages than full-scale wind tunnel tests and flight tests, is easier to implement, and has higher safety.

The invention provides a composite feedforward cooperative control method and system for propulsion of a controllable-pitch propeller of a ship. The method comprises the following steps: establishing a propulsion composite model comprising a ship load inquiry function model and a controllable-pitch propeller propulsion cooperative control model; identifying ship resistance characteristics in real time through a load inquiry model, predicting main engine power and propeller rotating speed requirements at different navigational speeds, and calculating a main engine power margin; setting a host security threshold based on the maximum persistent power margin; within the allowable range of the safety threshold value, three cooperative control modes are selected and executed in a self-adaptive mode according to the navigation working condition, wherein the three cooperative control modes include the pitch-accelerator joint control mode under the constant rotating speed of a main engine, the main engine rotating speed-accelerator joint control mode under the fixed pitch of a controllable-pitch propeller and the controllable-pitch propeller rotating speed-pitch joint control mode under the constant power of the main engine. According to the invention, through feedforward prediction and multivariable cooperation, navigational speed closed-loop stable control is realized, the problems of host overload, black smoke emission, high exhaust temperature and large control fluctuation are fundamentally avoided, and fuel economy and all-condition navigation safety are improved.

To provide an energy saving navigation method for vessel and an energy saving navigation system for vessel capable of carrying out energy saving navigation by integrally selecting actuation points when control of a governor and a variable pitch propeller are combined.SOLUTION: A plurality of ALC setting curves expressing the relationship between rotational number in ALC (automatic load control) of a variable pitch propeller for propelling a vessel and output of a main engine driving the variable pitch propeller, one of the plurality of ALC setting curves is selected according to load state of the main engine as well as controlling the governor and the variable pitch propeller according to control condition for the governor adjusting fuel supplied to the main engine and the selected ALC setting curve in an energy saving navigation method for vessel.SELECTED DRAWING: Figure 3

The invention relates to the field of unmanned aerial vehicles, and discloses a tilting type composite thrust system of a small fixed-wing aircraft, comprising: a physical bearing and power unit module comprising wings and six groups of tilting thrust units on the wings, each group of unit being composed of a turboprop engine and a variable pitch propeller and generating thrust; the thrust vector adjusting module comprises six sets of electric tilting joints and drives the tilting thrust unit to rotate so as to adjust the thrust direction. The state sensing and feedback module is provided with an angle sensor for monitoring the tilting angle in real time; the cooperation and synchronization control module comprises a synchronization controller which is connected with the angle sensor and the electric tilting joints and controls the six sets of electric tilting joints to be converted in batches according to the monitored angle. According to the invention, the integrated electric tilting joint is arranged, and the joint contains a main tilting shaft for wide-angle mode switching and an auxiliary fine tuning shaft for small-range active compensation, so that two adjusting mechanisms with different functions are integrated in a single structure.

The invention discloses a multi-mode propulsion system of a water-air cross-domain aircraft and a water-air amphibious aircraft. The multi-mode propulsion system of the water-air cross-domain aircraft comprises a brushless motor. The water-air force transmission system comprises a high-speed output transmission set and a low-speed output transmission set, and the input end of the water-air force transmission system is connected with an output shaft of the brushless motor; the output end of the water-air force transfer system is connected with the variable-pitch propeller assembly; when the rotating speed of the brushless motor is lower than or equal to a preset threshold value, a low-speed output transmission set of the water-air force transmission system provides driving force for the variable-pitch propeller assembly. When the rotating speed of the brushless motor is higher than a preset threshold value, a high-speed output transmission set of the water-air force transmission system provides driving force for the variable-pitch propeller assembly. According to the power transmission mechanism, the transmission shaft can be switched to different rotating speed positions, and rotating speed and torque parameter matching of power transmitted to the propeller is achieved.

The invention provides a fault identification method of a variable pitch propeller and a related device, and relates to the technical field of aircrafts. The method comprises the steps that a blade of the variable pitch propeller is controlled to conduct reciprocating variable pitch motion according to a self-inspection waveform, a motion waveform is obtained, self-inspection data corresponding to multiple self-inspection indexes are determined according to the self-inspection waveform and the motion waveform, the multiple self-inspection indexes comprise indexes of multiple dimensions related to input instruction response, and the self-inspection data correspond to the multiple self-inspection indexes. And further determining whether the variable pitch propeller has a fault or not according to the self-inspection data corresponding to the plurality of self-inspection indexes. According to the method, the blades of the variable-pitch propeller are controlled to perform reciprocating variable-pitch motion according to the self-inspection waveform, the self-inspection data corresponding to the multiple self-inspection indexes are determined, the operation state of the variable-pitch propeller is accurately monitored, the operation state of the propeller is comprehensively evaluated from multiple dimensions according to the self-inspection data, and the accuracy of the operation state of the propeller is improved. Whether the variable pitch propeller has a fault or not is accurately identified, the possibility of misjudgment or missed judgment is reduced, and thus the accuracy of fault identification is improved.

Variable pitch propeller, comprising at least two blades and a rotor with a hub, the hub comprising a blade support for each blade of the propeller, each blade comprising a blade foot designed to cooperate with one of said blade supports in order to maintain the blade in position in the rotor while allowing the pitch to be changed, comprising: - a blade foot comprising a composite core (11), disposed in an outer sleeve (13) of the blade support resting on it by means of an elastomer buffer (12), - a blade support (4) having an upper bearing (2) and a lower bearing (3) in contact with the outer sleeve (13), the blade support (4) also comprising at least two half-jaws (14) cooperating with the composite core (11) in order to prevent the blade foot from moving in a radial direction relative to the blade support (4). Figure for the abridged version: Fig 8

The present invention discloses a variable pitch propeller, a thrust assembly and an aircraft, and relates to the technical field of aircraft. The variable pitch propeller includes a hub and blades; the fixed end of the linear drive assembly is arranged in the hub, and the output end of the linear drive assembly extends to the outside of the hub in a direction away from the electric engine; the variable pitch push plate is located on the side of the hub away from the electric engine and is connected to the variable pitch push plate, so as to reciprocate along the axial direction of the hub under the drive of the linear drive assembly; at least two variable pitch transmission assemblies correspond to at least two blades one by one, the variable pitch transmission assembly is located on the radial outer side of the hub, and the variable pitch transmission assembly is respectively connected to the variable pitch push plate and the blade, so that the variable pitch push plate drives the blade to swing through the variable pitch transmission assembly. The present invention places the variable pitch push plate directly above the hub, so that the structural size of the variable pitch motor is not restricted and the structural strength is improved.

The utility model discloses an aerial variable pitch propeller variable pitch mechanism stability augmentation structure and a propeller, the stability augmentation structure comprises a variable pitch disc, the variable pitch disc is provided with at least two axial through limiting guide holes, and guide columns are arranged in the limiting guide holes in a sliding mode. The propeller comprises the stability augmentation structure. According to the utility model, the guide post is arranged, so that the variable-pitch disc does not rotate and does not shake, the planeness of the variable-pitch disc in the variable-pitch movement process is improved, and the variable-pitch precision is improved; the resistance of up-down movement of the variable-pitch disc is reduced by arranging the linear bearing, the service life is prolonged, and the mechanical transmission efficiency is improved.

A method of performing health monitoring for an aircraft having a variable pitch propeller system. The method includes: receiving aircraft flight information; performing a virtual pitch calculation to determine a virtual propeller pitch or virtual blade angle from the aircraft flight information; receiving a measured propeller pitch or blade angle from at least one physical sensor associated with the propeller; and using the virtual propeller pitch or virtual blade angle and the measured propeller pitch or blade angle to perform a health monitoring process to determine a health condition of at least one component of the aircraft, wherein the at least one component is distinct from the blades.

The utility model discloses a variable pitch propeller structure of an unmanned aerial vehicle, which relates to the field of unmanned aerial vehicle structures and comprises a propeller mounting seat, the bottom end of the propeller mounting seat is connected with a telescopic propeller shaft structure, and propeller blades are arranged on the periphery of the propeller mounting seat; the ends, close to the propeller mounting base, of the propeller blades are connected with propeller blade adjusting shafts, the ends, close to the propeller mounting base, of the propeller blade adjusting shafts are connected with the propeller mounting base, and the propeller blade adjusting shafts are further connected with limiting clamping rings. The outer wall of the limiting clamping ring is connected with an upper limiting clamp and a lower limiting clamp through bolts, and the lower limiting clamp is used for being connected with a propeller mounting base. According to the propeller structure, the included angle (pitch) between the rotating plane of the propeller blades of the propeller structure and airflow can be adjusted according to needs, so that the propeller system optimizes thrust and efficiency in different flight states, and the unmanned aerial vehicle can adapt to different environments.

The invention relates to an assembly comprising a propeller blade (10) and a pitch adjustment system (34) for setting the pitch of the blade (10), wherein the root (14) of the blade (10) has a bulb (32) and the pitch adjustment system (34) for setting the pitch of the blade (10) comprises: - a cup (58) having an upper opening (58c); - a retaining ring (82) extending around the bulb (32), the retaining ring being at least limited in axial movement relative to the cup (58) towards the opening (58c) and having a bearing face (84) to hinder axial movement of the root (14) towards the opening (58c); the pitch adjustment system (34) being characterized in that it further comprises a lower seat (88) by which the root (14) is engaged with the cup (58), the seat (88) and / or the retaining ring (82) being mounted so as to be axially translatable relative to the cup (58) by at least one clamping mechanism (90).

The invention relates to a static hydraulic fluid transfer terminal (42) for a hollow propeller shaft (30) that rotates during operation. The hydraulic fluid transfer terminal (42) has a main body (42.1) with an inner wall enclosing a cylindrical free space (42.3). The cylindrical free space (42.3) is configured for receiving the propeller shaft (30). The inner wall of the main body (42.1) is annularly recessed to provide an annular hydraulic fluid transfer groove (42.4). At least one hydraulic fluid port (42.7) is fluidly connected to the hydraulic fluid transfer groove (42.4) for feeding a hydraulic fluid such as oil in the annular hydraulic fluid transfer groove (42.4). The main body (42.1) is composed of at least two separate body parts (42.11, 42.1.2) that are detachably fastened to each other and that are separated along a plane that extends through a longitudinal axis of the cylindrical free space (42.3).

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.

1. The name of the product of this design: twin-blade geared variable pitch propeller. 2. Purpose of this design product: This design is used for a variable pitch propeller on a helicopter. 3. The design key point of this appearance design product lies in the combination of shape and pattern. 4. The picture or photo that best illustrates the key points of the design: main view.

A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.

The propulsion system is a propulsion system for a hybrid propulsion ship having a variable pitch propeller, an engine for controlling the rotational speed in accordance with a rotational speed command value, a motor generator, a power converter, and a controller for controlling the power converter, the controller including a processing circuit that acquires blade angle data of the variable pitch propeller and transmits the acquired blade angle data to the variable pitch propeller. When the rate of change in the blade angle of the variable pitch propeller is equal to or greater than a predetermined threshold value, a command value for adjusting the power received by the power converter from the motor generator or the power supplied from the power converter to the motor generator is generated, and the command value is output to the power converter.

A system (34) for controlling the pitch of a propeller blade (10) of a turboprop engine of an aircraft is disclosed, characterized in that it comprises a cup (58) comprising an annular wall (58a) extending around an axis (A) serving as an axis of pitch setting of the blade, and a bottom wall (58b) configured to cooperate in a shape-matched manner with a free end (28) of said root (14), so as to prevent the cup (58) from rotating with respect to the root (14) around the axis (A), and a fixing ring (52, 52') configured to be mounted inside the cup (58) and to cooperate with the root (14) and with the annular wall (58a) of the cup (58), respectively, so as to ensure the axial retention of the root (14) in the cup (58).

The utility model belongs to aerospace equipment technical field, concretely relates to a variable pitch propeller. The utility model discloses variable pitch propeller includes a plurality of blades, hub assembly and a plurality of locating plate, and the blade includes blade main part and locating protruding, and locating protruding sets up at the root of blade main part, and hub assembly includes detachably connected first hub and second hub, and first hub includes first hub main part and a plurality of first connecting part, and second hub includes second hub main part and a plurality of second connecting part, and first connecting part and the second connecting part of direct setting form the slot, and the slot is used for and the root of blade main part inserts, and first hub main part and second hub main part splice and form a plurality of open slot, and open slot and the slot correspond and communicate with the slot, and locating plate inserts in open slot, and locating plate is provided with locating insertion hole, and locating insertion hole is used for and locating protruding inserts. The variable pitch propeller in this technical scheme can realize quick variable pitch and improve variable pitch accuracy.

The invention discloses a fixed-wing unmanned aerial vehicle self-adaptive flight control method based on a variable-pitch propeller and the self-adaptive variable-pitch propeller. The method comprises the steps that multi-sensor data such as the air speed, the height, the vertical speed, the accelerator and the rotating speed are collected in real time; based on a predefined comprehensive scoring model, scores of all flight stages are calculated through piecewise scoring functions of five dimensions of height, air speed, vertical speed, accelerator and time, and a strict conversion logic and hysteresis mechanism is combined to intelligently judge that the aircraft is in a take-off, climbing, cruising or descending stage at present; according to the judged stages and the real-time state, the pitch angle of the variable pitch propeller and the position of an engine throttle are dynamically calculated, control parameters are adjusted according to the stages, and height and rotating speed compensation is introduced; meanwhile, three-level safety protection including warning, active intervention and emergency response is implemented, and thrust and system efficiency are calculated online to optimize energy efficiency. According to the invention, self-adaptive, high-safety and high-efficiency control in the whole flight process is realized.

The application discloses a pitch feedback adjusting circuit based on frequency signal transmission of a pitch control propeller, and relates to the technical field of electrical control.The circuit comprises a pitch signal acquisition circuit, a voltage-to-frequency signal transmission circuit and a frequency-to-voltage signal adjusting circuit.The pitch signal acquisition circuit is connected with a pitch potentiometer, used for acquiring and processing a pitch feedback signal and transmitting the signal to the voltage-to-frequency signal transmission circuit to be converted into a frequency signal for long-distance transmission.The frequency-to-voltage signal adjusting circuit converts the long-distance transmitted frequency signal into a voltage signal, and outputs a pitch feedback signal meeting the use requirements of a pitch control propeller ship after signal adjustment.The pitch signal acquisition circuit comprises a signal acquisition circuit, a filter following circuit and a zero point and range adjusting circuit.The voltage-to-frequency signal transmission circuit comprises a voltage / frequency conversion chip and a peripheral circuit thereof.The frequency-to-voltage signal adjusting circuit comprises a frequency / voltage conversion chip and a peripheral circuit thereof.

The invention relates to an integrated plant for regeneration and recovering waste industrial and engine oils, such as marine oils (MOBILGARD M430 for the main propulsion engines, Devlac MX15W40 for the diesel generators, M-14G2CS for lubricating the stern tube, BARTRAN HV 68 for the blade control system of variable pitch propellers, CASTROL T 68 for lubricating the gas turbine of the main propulsion engine, OMALA 220 for lubricating the gear components), motor vehicle oils, oils for textile machinery, etc., comprising several units, and can also be used across various industries. The technical result of the invention is the improved degree of purification of waste industrial and engine oils and safe operation of the plant. An integrated plant for regeneration and recovering waste industrial and engine oils comprises a module for removing moisture and fuel fractions from the oil to be purified, which module is connected to a module for diagnostics and monitoring of the oil to be purified, a module for controlling the quality of the oil to be purified and a module for applying functional additives to the oil to be purified.

The invention discloses a real-time communication new energy aircraft variable pitch propeller, and belongs to the technical field of aviation, the real-time communication new energy aircraft variable pitch propeller comprises a mounting frame, a plurality of adjusting shafts are arranged on the side wall of the mounting frame, blades are arranged at the ends, away from the mounting frame, of the adjusting shafts, an electric slip ring is arranged at the bottom of the mounting frame, and sliding pins are arranged on the sides, close to the mounting frame, of the adjusting shafts; an incomplete gear is arranged on the outer side wall of the adjusting shaft, an angle sensor is arranged in the installation frame, and a detection shaft of the angle sensor is provided with a transmission gear meshed with the incomplete gear. According to the device, the threaded column is automatically locked after adjustment, rotation caused by potential difference after the motor stops adjustment and is powered off is reduced, the adjustment error is reduced, the accuracy and accuracy of paddle adjustment are improved, the threaded column can be locked in all directions after adjustment is completed, the position of the adjustment block and the angle of the paddle are continuously limited, and the adjustment efficiency is improved. And the stability of the paddle during normal working is improved.

The rigid-flexible composite propeller hub connecting device for the variable pitch propeller comprises a propeller hub and a propeller root assembly, and is characterized in that a flexible connecting assembly is arranged at the connecting interface of the propeller hub and the propeller root assembly. The assembly is composed of rigid inner and outer ring bushings and a rubber elastomer embedded between the rigid inner and outer ring bushings. The inner ring lining is in close contact with the propeller root, and the outer ring lining is in interference fit with the propeller hub. By means of the rigid-flexible composite structure, reliable and accurate transmission of torque and centrifugal force is ensured, meanwhile, vibration energy generated by working of the propeller is effectively absorbed and dissipated through the high-damping rubber material, and therefore a vibration transmission path is remarkably blocked, the excellent vibration and noise reduction effect is achieved, and the working stability and reliability of a system are improved; and the service life of the propeller is prolonged. The variable-pitch propeller is compact in structure, convenient to assemble and maintain and easy to integrate into an existing variable-pitch propeller structure.

The application discloses a pitch signal adjusting circuit and a three-way feedback redundancy control method for a variable pitch propeller, comprising a power supply circuit, a pitch signal collecting and adjusting circuit and a three-way feedback redundancy control module; the three-way feedback redundancy control module receives three-way pitch feedback current signals respectively and is configured to execute a three-way feedback redundancy control method; the method comprises safety threshold judgment, weighted voting, consistency detection, majority voting, dynamic selection, stability judgment, recursive average filtering and median filtering algorithms executed in a preset rule sequence, and according to the deviation, change rate and fluctuation state of the three-way signals, effective signals are dynamically selected to participate in the closed-loop control of the variable pitch propeller, or the pitch is locked and an alarm is given when all the signals are abnormal. The three-way pitch feedback signals of the variable pitch propeller are independent of each other and do not interfere with each other, the three-way pitch signals are processed through the method, the reliability of the variable pitch propeller system is improved, and the method is suitable for popularization and use in a pitch control system of the variable pitch propeller.