53results about How to "Small disturbance torque" patented technology

The invention provides a zero-counterweight barycenter deploying method for a parallel tiling tank satellite. The method comprises the following steps: (1) preliminarily calculating a satellite barycenter position; (2) preliminarily calculating an adjustable scope of a barycenter; (3) after testing mass characteristics of the satellite, acquiring a measured value of the barycenter, analyzing and calculating the mass and position of a to-be-adjusted propellant according to the measured value, and causing the barycenter to approach to the original point; (4) performing propellant filling for the satellite according to a calculating result of the filling quantity of the propellant of each tank, controlling different filling quantities, and meanwhile, setting a work state after filling. The invention provides the new barycenter deploying method for a parallel tiling tank layout high-orbital satellite; under the condition of not increasing the total mass of the satellite, the original barycenter offset of the satellite is reduced, so that the barycenter variation of a satellite orbital transfer section is reduced, the disturbance torque is reduced, the safety of the satellite orbital transfer is ensured, the consumption of the propellant is reduced, and the service life of the satellite is prolonged.

The invention provides a transverse centroid high-precision guarantee method for a parallel tiled tank satellite in AIT stages. The transverse centroid high-precision guarantee method comprises the following steps: in the structural assembly stage, tank mounting plate form and position errors as well as apogee engine bracket mounting errors are controlled; in the propulsion system welding assembly stage, tank mounting position errors as well as apogee engine mounting position and pointing errors are controlled; in the whole satellite general assembly stage, the quality and the centroid are controlled when a solar array in the unfolded state; and before delivery, the whole satellite transverse centroid measurement is performed through high-precision centroid measurement equipment. According to the transverse centroid high-precision guarantee method provided by the invention, a plurality of transverse centroid guarantee measures are implemented in all the AIT stages of the whole satellite, the transverse centroid of the satellite is controlled to be near the origin when the solar array is in the initial unfolded state, the transverse centroid determination accuracy of the satellite is improved (lower than or equal to 1 mm), and the transverse centroid change of a satellite orbit maneuver section is reduced, thereby reducing the disturbance torque generated by an apogee engine and ensuring safe orbit maneuver; and meanwhile, the consumption of a propellant is lowered.

The invention provides an exchange apparatus and method for a double-workpiece stage based on double-guide rail double-drive step scanning, belonging to the technical field of manufacture equipment for semiconductors. The exchange apparatus comprises a base station and workpiece stages located at an prealigning station and an exposure station; four Y-oriented rectilinear motion units and two X-oriented rectilinear motion units are preset on a balancing mass, and three-phase exchanging of the workpiece stages between a prealigning area and an exposure area is finished through butt joint between rectilinear motor stators of the Y-oriented rectilinear motion units and Y-oriented transitional rectilinear motion units; a first Y-oriented rectilinear motor mover 1 is fixedly connected with a first workpiece stage, a fourth Y-oriented rectilinear motor mover 1 is fixedly connected with a second workpiece stage, and the Y-oriented rectilinear motion units and the X-oriented rectilinear motion units form a double-guide rail double-drive structure at the exposure station. According to the invention, during exchanging of the workpiece stages, three phases are employed, which allows exchanging efficiency to be improved; in specific embodiments of the invention, the advantages of small inertia of motion, short time for stabilization, great structural rigidity, centroidal driving at the exposure station and the like are realized.

The invention discloses a method for determining mounting parameters of orbit control engines of satellites. The method includes determining a mounting position of each engine by the aid of included angles alpha<E>, beta <E> and gamma <E> among a normal line O<m>X<m> of an accurate measurement mirror of the engine and an axis O<sc>X<sc>, an axis O<sc>Y<sc> and an axis O<sc>Z<sc> of a mechanical coordinate system of the corresponding satellite and coordinates x<E>, y<E> and z<E> of the center O<m> of the accurate measurement mirror of the engine on the axis O<sc>X<sc>, the axis O<sc>Y<sc> and the axis O<sc>Z<sc> of the mechanical coordinate system of the satellite. The method has the advantages that change conditions of mass centers of the satellites and thrust vectoring thermal marking results of the engines are comprehensively considered, so that the mounting parameters of the engines can be optimally determined, disturbance torque generated in orbital transfer periods of the satellites can be reduced, satellite propellants can be saved, and the in-orbit lives of the satellites can be prolonged; thrust of each engine points to the average mass center of the corresponding satellite in the corresponding orbit transfer period, so that counterweights for the satellites can be reduced or can be omitted, and the effective load weight of each satellite can be increased.

The invention provides a satellite orbit control engine installation optimization method based on a genetic algorithm. The method comprises the following steps that (1) an objective function of the engine installation optimization is determined according to the requirement of a control system on the satellite layout; (2) according to the engine geometrical parameters and the installation requirements, a constraint function of the engine installation optimization is determined; (3) an AMTLB genetic algorithm toolkit is used for carrying out engine installation parameter optimization. The satellite orbit control engine installation optimization method has the advantages that the interference moment in the orbital transfer period is further reduced, so the satellite fuel is saved, and the satellite on-orbit life is prolonged.

The invention discloses a coaxial contra-rotating terrestrial magnetism energy storage and release delivery ground experiment system, which comprises a supporting through shaft and a magnetic moment generation device, and is characterized in that a first target delivery assembly and a second target delivery assembly are coaxially and rotatably mounted on the supporting through shaft, and are both used for mounting and releasing a delivery target; the working method comprises the steps that the first target delivery assembly and the second target delivery assembly are configured to receive a rotation starting signal of the magnetic moment generation device, then rotate oppositely with the supporting through shaft as a rotating shaft, and when the linear speed of a delivery target reaches the linear speed set by the system, the first target delivery component or the second target delivery component releases the delivery target. According to the invention, two sets of delivery devices rotate coaxially and oppositely, so that the air resistance moment in a ground experiment can be overcome, and the restriction that the target linear velocity has an upper limit is relieved, thereby being better used for ground principle verification of a terrestrial magnetism energy storage method.

The invention which relates to a double-rail double-drive-based three-beat double-workpiece bench exchange apparatus and a method thereof belongs to the technical field of semiconductor manufacturing equipment. The apparatus is characterized in that: the apparatus comprises workpiece benches which operate on a prealigned station and an exposure station; the prealigned station and the exposure station are respectively provided with a well type driving unit which comprises a two side X-directional liner motion unit and a two side Y-directional liner motion unit; two Y-directional transitional liner motion units are arranged between the two well type driving units; and the bench replacement of the double-workpiece bench is completed through the butt joint of the Y-directional liner motion unit and the X-directional liner motion unit. According to the invention, the two workpiece benches are driven in the prealigned station and the exposure station in a dual side mass center mode, so the system angle rigidity is increased; only three beats are needed to exchange the two workpiece benches between the prealigned station and the exposure station, so the lithography efficiency is improved; and the apparatus has the advantages of small motion inertial, short stable time, large structure rigidity and the like in the concrete embodiment process.

The invention discloses a method and a system for estimating disturbance torque caused by an asymmetric rotational scanning load. The method comprises the following steps of: calculating according to coordinate conversion to obtain a rotational inertia matrix of a rotating body formed by a load cabin and a magnetic suspension joint rotor in an orbital coordinate system; calculating to obtain the angular velocity vector of the rotating body in the inertial coordinate system; calculating the angular momentum of the load cabin according to the rotational inertia matrix and the angular velocity vector of the rotating body; establishing the attitude dynamic model of the rotating body according to an Euler equation; classifying nominal rotating speeds in the attitude dynamical model to obtain a variable inertia reaction torque and gyroscopic torque interference model caused by an orbital angular velocity and a rotating body angular velocity; and substituting the rotational inertia of the rotating body in the satellite and the nominal rotating speed of the rotating body into the interference model, and estimating constant value, first frequency multiplication and second frequency multiplication interference torques caused by the rotating body. According to the invention, a basis for applying interference is provided for control, ground simulation and test verification of the magnetic suspension rotary joint and the satellite.

The invention relates to a lintel type dual-guide rail dual-drive stepping scanning double silicon wafer stage exchanging device and a method thereof, and belongs to the field of semiconductor manufacturing equipment. According to the device, the system comprises two silicon wafer stages arranged on the same base station, wherein one silicon wafer stage operates at the exposure working position, and the other silicon wafer stage operates at the pretreatment working position; the edge of the base station is provided with 4 Y-direction linear movement units and 2 X-direction linear movement units; the middle of the base station is provided with 2 lintel type linear movement units, wherein the X directions of the lintel type linear movement units are higher than the working surfaces of the silicon wafer stages; the Y-direction linear movement units can perform the movements in the X direction through the X-direction linear movement units, and can collectively perform the movements of thesilicon wafer stages in the X direction or in the Y direction with Y-direction movement sliders of the Y-direction linear movement units. According to the present invention, the torsion interference resistance of the guide rail can be enhanced, the movement deviation and the deformation deviation can be decreased or overcome, and the movement precision of the silicon wafer stage can be improved; the operation of the device of the present invention only comprises three steps so as to shorten the required double stage exchanging time, and significantly improve the production efficiency of the photoetching machine.

The invention discloses a three-degree-of-freedom spherical hybrid magnetic bearing with an axial self-loop. An outer axial stator, an upper annular permanent magnet, a radial stator, a lower annularpermanent magnet and a lower axial stator sequentially coaxially sleeve a rotator from top to bottom, each of the upper axial stator and the lower axial stator is formed by axially connecting an upperdisc, a middle disc and a receiving disc, the inner end surface of every upper disc extend radially inwards extends to form a conical disc, small discs are arranged between the upper and lower end surfaces of the rotor and the corresponding conical discs, the small discs are closely attached to the upper and lower surfaces of the corresponding conical discs, the upper small disc is located abovethe upper end surface of the rotor, and the lower small disc is located below the lower end surface of the rotor; and axial air gaps are left between the upper and lower small disks and the end surface of the rotor, and a control magnetic flux enters the receiving discs through return air gaps to axially form the self-loop without mounting a pushing disc, so the rotating speed of the rotor is optimized, and coupling of axial and radial magnetic fields is reduced.

The invention relates to a sensor, in particular to a sensor for a three-floated gyroscope and a stator preparation process thereof, and solves the problems of oil leakage of a sensor rotor and asymmetry of a sensor magnetic circuit of an existing moving-coil sensor device. The sensor rotor comprises a rotor bracket, a rotor coil and a rotor pouring sealant layer. The rotor support is an annular support, an annular groove is formed in the circumferential direction of the outer circumferential face of the annular support, and one side wall of the groove is a step face. The rotor coil is wound in the small end of the groove. The pouring sealant is poured in the large end of the groove along the outer peripheral surface of the rotor coil to form a rotor pouring sealant layer. The first end surface of the pouring sealant layer clings to the large end surface of the groove, and the second end surface of the pouring sealant layer is flush with the end surface of the rotor bracket. The sensorstator comprises an inner magnetic conductive ring and a plurality of magnetic poles, and the plurality of magnetic poles and the inner magnetic conductive ring are integrally arranged. By optimizingthe structure of the sensor, the center of mass of the gyroscope does not obliquely float in a certain slope trend any more, and the precision and reliability of the gyroscope are guaranteed.