30results about How to "Solving Compensation Issues" patented technology

The invention provides a volume-type fluid mechanism which comprises an eccentric shaft and a working medium moving part, wherein the eccentric shaft comprises a driving shaft and a deflection non-sleeve body; the deflection non-sleeve body is arranged on the rotating shaft of the driving shaft and / or arranged on the eccentric part of the driving shaft; and the working medium moving part sleeves the driving shaft and the deflection non-sleeve body. According to the volume-type fluid mechanism provided by the invention, the compensation problem of the mechanism is effectively solved, the life of the volume-type fluid mechanism is prolonged, the sealing performance of the volume-type fluid mechanism is effectively improved and the efficiency is improved.

The invention belongs to the technical field of small hole electric machining and particularly relates to a machining method of a gravity-free smelting layer air membrane hole of an aviation engine turbine blade. The machining method comprises four steps: firstly, machine a circular hole with a needed size a nickel-based high-temperature alloy blade on a gas turbine by utilizing washing liquid electric sparks in a hollow electrode according to a design requirement; then utilizing the same electrode to electrolyze the machined circular hole in an electrolyte environment of an outer washing solution to remove a re-smelted layer; then, raising the electrode and utilizing an electric spark servo scanning and milling and machining process to machine a dustpan-shaped hole opening of the air membrane hole; and finally, utilizing the end part of the electrode to carry out electrolytic milling machining on the dustpan-shaped hole opening to remove the re-smelted layer of the hole opening so as to improve the surface quality. According to the machining method disclosed by the invention, the problem of a residual re-smelted layer and small cracks of the air membrane hole machined by the electric sparks can be solved, a secondary clamping and positioning error is avoided and the machining efficiency is improved.

The invention provides an aeromagnetic compensation method based on a non-linear aeromagnetic total field gradient compensation model. Time series weighting modeling of output of a flux-gate magnetometer is carried out, and a direction cosine of a geomagnetic field and a direction cosine of an airplane, and an aeromagnetic compensation model characteristic matrix are estimated, and thereafter airplane platform magnetic interferences observed by an optical pump magnetometer is predicted to acquire the non-linear aeromagnetic total field gradient compensation model, and then the non-linear aeromagnetic total field gradient compensation model is solved to acquire an aeromagnetic compensation result. By establishing the non-linear aeromagnetic total field gradient compensation model, a compensation problem of an interference magnetic field caused by time delay between data channels is effectively solved, and the precision of the aeromagnetic compensation is greatly improved.

A latitude unknown self-aligning method of a strapdown inertial navigation system under the dynamic interference condition includes the steps that firstly, a geometrical analytic formula is built by means of the characteristic that the projection of gravity acceleration is unchanged in an inertial coordinate system, the gravity acceleration is subjected to integration to obtain speed information, and the latitude value of the position where a carrier is located is calculated according to the speed information; secondly, on the basis of the double-vector altitude determination principle and by means of the characteristic that the gravity acceleration of an inertial system includes north orientation information, rough solution of an initial attitude matrix under the inertial system is achieved; finally, on the basis that coarse alignment is finished, a precise alignment error model under the latitude unknown dynamic interference condition is built according to a speed error equation, a misalignment angle equation and a latitude error equation, the latitude error angle and the misalignment angle of the carrier are calculated by means of the self-adaptive filtering method based on information, the latitude value is compensated with the latitude error angle, the strapdown altitude matrix is corrected according to the misalignment angle, and high-precision quick self-aligning of the strapdown inertial navigation system is achieved.

The invention discloses an industrial tail gas liquefaction energy storage power generation system and a power generation method. The system is characterized in that industrial tail gas is subjected to condensation and purification through a tail gas purification heat storage unit; heat energy generated during the condensation and purification process is stored; electric energy is generated from condensed and purified tail gas through a tail gas turbine power generation unit; useful gases like sulfur, carbon, oxygen and nitrogen are liquefied and separated from tail gas output by the tail gas turbine power generation unit through a liquefaction separation storage unit; a pressurization gasification power generation unit drives liquefied useful gases of the liquefaction separation unit to be gasified, and electric energy is further generated; and thereby, industrial tail gas liquefaction, separation, storage and gasification power generation are achieved, the comprehensive utilization rate and emission reduction rate of industrial tail gas are increased, the energy compensation problem of peak regulating and valley filling is efficiently solved, investment of matching generating sets, power transmission and distribution facilities and gas supply networks for building energy storage power stations or peak regulating power stations is reduced, the remote power supply loss and running cost are reduced, and the safety, stability and economy of power supply and peak regulating are improved.

The invention provides a blade vibration detection and fault prediction system for fan. The fan rotates in a circular motion centering on a connecting shaft at a certain rotating speed. The system comprises a fan blade vibration detecting device as a hardware part and a fan fault prediction method as a software part.

The invention discloses a rotary compensator used for anti-corrosion piping and a system thereof. The rotary compensator comprises a rotary connecting pipe (1), a sealing gland (3), a sealing seat (4) and a conical connecting pipe (7). The invention is characterized in that one end of the rotary connecting pipe (1) is welded with a coupling flange (8), the other end thereof is equipped with a terrace (9) and is inserted into a taper connecting pipe (7). The sealing seat (4) is covered on the rotary connecting pipe (1), the internal surface of the sealing seat (4) is equipped with an internal convex ring (10), one side of one end surface (1001) of the internal convex ring (10) is equipped with a high pressure resistant sealing gasket (6), and the side of the other end surface (1002) of theinternal convex ring (10) is equipped with a low pressure sealing gasket (6'), the flange end of the sealing gland (3) is inserted into the sealing space of the ring surface and touches against the sealing gasket (6'), and the sealing gland (3) and the sealing seat (4), the sealing seat (4) and the taper connecting pipe (7) are all connected via the flange connection structure. The compensation system comprises at least two compensators. The rotary compensator has the advantages of long service life, good pressure resistance and large compensation rate.

The invention provides an overload electrohydraulic executing mechanism drive valve system with a compensation function, and aims to solve the problem that CN101709807 is constrained by a spring and thus cannot be applied to the overload electrohydraulic executing mechanism drive valve system. The key points are that the system comprises a drive oil cylinder, a compensation oil cylinder and a spring, wherein a piston rod of the drive oil cylinder is connected with a valve rod of an overload valve; a piston rod of the compensation oil cylinder is abutted against the spring; the compensation oil cylinder is connected with the drive oil cylinder in parallel. The system has the positive effects that energy is absorbed, stored and released by the spring and the compensation oil cylinder together, the spring is not a unique involved part, the problem of spring constraint is solved, further the application to the overload electrohydraulic executing mechanism drive valve system is realized, and reliable operation of the overload electrohydraulic executing mechanism drive valve system is guaranteed.

The invention discloses an optical axis variation compensating device for a lens module of an unmanned aircraft and a compensating method thereof. As for the driving part of the angle of the fuselage, the driving part controls the rotation angle of the imaging device. In the optical axis variation compensation device and compensation method of the lens module of the unmanned aircraft, when the lens in the camera device moves and the center of gravity shifts, the drive unit provided on the camera device controls the rotation angle of the camera device for Compensation, the compensation data is adjusted according to the matching angle of the moving distance of the lens, which solves the compensation problem of the unmanned aircraft when the optical axis changes, improves the stability of the shooting picture, and obtains high-quality pictures. The present invention is applicable to the field of unmanned aerial vehicles.