49results about How to "Suppression of thrust fluctuations" patented technology

The invention discloses a double-side staggered-tooth tau / 2 low-thrust-ripple permanent magnet synchronous linear motor. A first primary assembly and a second primary assembly are both composed of anarmature winding and a primary iron core, each primary iron core is of a tooth groove structure, and the armature windings are wound on teeth; the first primary assembly and the second primary assembly are located on the two sides of a secondary assembly and form air gaps with the secondary assembly respectively; the secondary assembly comprises a yoke plate and a plurality of permanent magnets, each pair of poles comprises four permanent magnets, the first permanent magnet and the second permanent magnet of each pair of poles are located on the same side of the yoke plate, the third permanentmagnet and the fourth permanent magnet of each pair of poles are located on the same side of the yoke plate, the positions of the first permanent magnets and the third permanent magnets are opposite,the positions of the second permanent magnets and the fourth permanent magnets are opposite, the magnetizing directions of the first permanent magnets and the third permanent magnets are the same, the magnetizing directions of the second permanent magnets and the fourth permanent magnets are the same, and the magnetizing directions of the first permanent magnets and the second permanent magnets are opposite; the displacement of the first primary assembly and the second primary assembly in the transverse direction is S which is equal to tau / 2, and tau is the polar distance of the motor. By means of the structure, the thrust ripple of the motor can be reduced, and meanwhile unilateral magnetic tension and fluctuation of the unilateral magnetic tension are reduced.

The invention discloses a five-phase permanent-magnet embedded fault-tolerant linear-motor adjacent two-phase fault-tolerant vector control method. According to principles that traveling wave magnetomotive forces before and after a two-phase open-circuit fault are invariant and a non-fault-phase current sum is zero, a condition that non-adjacent two-phase current amplitudes are equal is taken as a constraint condition so as to derive and popularize a Clark transformation matrix; matrix transposition is used to estimate a counter potential; and an inner model controller, a first-order inertia feedforward voltage compensator and a counter potential observer are used to change a nonlinear strong coupling system of the motor under a fault state into a first-order inertia system. According to a principle that a synthesized magnetomotive force of a non-fault-phase short circuit compensation current and a short circuit fault phase current is zero, a short circuit compensation voltage is calculated. The voltage is superposed with an output voltage of a vector control device. By using the method of the invention, a motor thrust fluctuation caused by adjacent two phase faults of the motor is restrained, dynamic performance and stable state performance are consistent with the performance under a normal state, and a switch frequency of a voltage source inverter is constant.

The invention discloses a thrust fluctuation compensating secondary of an annular winding permanent magnet linear synchronous motor, which is composed of a plurality of plate-shaped secondary assemblies and forms a multi-faceted air gap structure with a primary armature with annular winding; the primary The cross section of the armature is rectangular, and the permanent magnet in the secondary assembly corresponding to its length interacts with the primary armature current to generate electromagnetic thrust. shift to achieve compensation for the electromagnetic thrust fluctuation component. The present invention can realize more stable electromagnetic thrust output while ensuring the improvement of thrust density and structural compactness.

The invention proposes a high-thrust-density electromagnetic actuator for a nano-satellite deployer, which is mainly composed of a stator and a mover. The stator mainly includes: a stator frame, a magnetic yoke, a magnetic ring and a lock nut; the mover mainly includes: a coil Skeleton and coil. The invention forms upper and lower double permanent magnetic branch magnetic fluxes on the single-layer magnetic pole, realizes the shunting of the permanent magnetic flux, effectively relieves the magnetic saturation of the magnetic yoke, reduces the thickness of the magnetic yoke, and has a single-layer magnetic pole and single-layer coil configuration. The axial size and volume mass of the actuator are reduced; the double permanent magnet branch circuit improves the air gap magnetic field distribution, reduces the thrust fluctuation and increases the thrust density. The invention has the characteristics of small size, light weight, high thrust density and stable thrust, and is very suitable for the deployer to release the nano-satellite on-orbit speed.