32 results about "Closed orbit" patented technology

This invention relates to a method of operating a charged particle trap in which ions undergo multiple reflections back and forth and/or follow a closed orbit around, usually, a set of electrodes. The invention allows high-performance isolation of multiple ion species for subsequent detection or fragmentation by deflecting ions out of the ion trap according to a timing scheme calculated with reference to the ions' periods of oscillation within the ion trap.

The invention discloses an orbit expansion based multi-robot tracing formulation control method, comprising the following steps of: a) for a group of target orbit in a plane, expanding vectors of the target orbit, which point to each point on the orbit along the center of the target orbit, into an orbital cluster equivalent to an orbital function, and determining the movable range of robots; b) calculating tracing error by virtue of the orbital function, and designing the virtual angular velocity of the robots to ensure the tracing error to meet design requirements; c) calculating the generalized arc length and differential coefficient of the generalized arc length when the robots move along the orbit, by virtue of the orbital function and the target orbit, and designing the control force of the robots by virtue of neighbor information obtained by communication to realize formulation; d) calculating the error between the real angular velocity and the virtual angular velocity, and designing the control moment of force of the robot to complete tracing; and e) completing motion control on the robots by virtue of a servo system. The orbit expansion based multi-robot tracing formulation control method disclosed by the invention is especially applicable to nonholonomic constraint dynamic robots and simple and convexly- closed orbits. The method is simple and reliable, has higher accuracy and can be applied to multi-robot optimized information acquisition and the like.

A human powered drive units each including a pair of a rotatable member having a sprocket and a supporting member having a sprocket, which are arranged up and down, and including a chain extended around the rotatable member and the supporting member, are disposed at left and right sides, respectively. The left and right rotatable members 1, 100 are fixed on a driving shaft 15. A chain ring 6 on which the load is applied is mounted on the driving shaft between upper rotatable member 1 and rotatable member 100. In each of the units, constraining means including a free crank (10 for the right-hand unit, and 1000 for the left-hand unit) and arm (11 for the right-hand unit, and 1100 for the left-hand unit), is provided so as to maintain perpendicularity of a shaft of the pedal relative to the plane in which the chain moves. By the rider kicking the pedal along the closed orbit including a linear orbit portion, the force transmitted to the pedal from the foot of the rider is efficiently converted to a rotational force in a longer period of time, thus increasing the power input.

In the warp knitting machines and knitting machines for multi-axis must be one-way yarn layer (8) to mobile vertical conveyor belt installation (1,2) and hung on the conveyor belt at the vertical (1,2) on a fixed set of hooks (3 , 3a, 3b, or 4,4a, 4b) on the. Above the vertical conveyor (1,2) to send the direction (5) mobile. Described yarn (8) from the storage device (6) was extracted and transferred through the pulley off (9) transmission line to the first input device (10), referred to the input line of the device will hang the yarn to the first vertical conveyor belt (1) a fixed set of hooks (3,3a, 3b) in the. Then, the second transmission line unit (11) will be linked to the second vertical conveyor belt yarn (2) a fixed set of hooks (4,4a, 4b) in the. Described in two transmission-line device (10,11) in two mutually perpendicular extension of the direction of x axis and y-axis movement and the movement to draw a closed orbit (14 and 15). In order to grab yarn (8), referred to the input line of devices (10,11) set up branch with claws (12,13). The methods described can also be achieved through the yarn guide, which referred to the input line of devices (10,11) was designed to shift rake. Yarn made of layers is transported to a warp knitting machine knitting station (7) or knitting tools.

The invention discloses a multi-kind graphics output primitive mixed processing path optimization method. According to the method, DXF file graphics output primitive information is read, closed orbit segment figures and non-closed orbit segment figures that are formed by a single graphics output primitive or multiple graphics output primitives are subjected to sorting code number marking operation, different start points and nodes are chosen for different orbit segment figures, overall path ordering operation is performed via a genetic algorithm, local optimization searching start points are calculated according to orbit segment figure types, and therefore processing paths with minimum lengths can be obtained. The multi-kind graphics output primitive mixed processing path optimization method can be used for effectively solving a problem of multi-kind graphics output primitive mixed path optimization, and numerical control machine tool processing efficiency can be improved.

A method is disclosed for designing an orbit of a spacecraft which allows the spacecraft to take a small-radius halo orbit near a Lagrange point while avoiding the prohibited zone where the spacecraft may be shadowed or might be prevented from making communication. The method makes it possible to have a closed orbit although being similar to a Lissajous orbit, under a restricted condition where a propulsion force magnitude applied to a spacecraft is fixed, and where it rotates at a constant angular velocity, based on the equation of motion close to a Lagrange point. The method also provide a theory for guiding/controlling the orbit of a spacecraft, that is, the embodiment of the above orbit design method.

The present invention relates to an elliptical sports machine with the tread-board orbit being adjustable, which comprises a skeleton, a movable bracket, a driving device, a right suspension arm, a left suspension arm, a right supporting rod, a left supporting rod, a right tread-board and a left tread-board, wherein, the movable bracket is provided with a right bracket body and a left bracket body, which are connected with each other through a motion part, and both the right and the left bracket bodies are provided with a bearing part and a rotation-shaft part, which are arranged at the back of the motion part; the rotation-shaft parts of the bracket bodies are coaxially hinged to the skeleton; the straight-line distance between the rotation-shaft part of the bracket bodies and the motion part is more than the straight-line distance between the rotation-shaft part and the bearing part; the driving device is arranged on the skeleton and is provided with a motor, and the force output thereof is connected with the power of the motion part of the movable bracket; both the right and the left suspension arms are provided with a suspension end and a swinging end; each of the right and the left supporting rod is provided with a return-winding part and a swinging part that is arranged after the return-winding part, and the return-winding part moves on a closed orbit corresponding to the skeleton, and the swinging part is hinged on the swinging end of the corresponding suspension arm; each of the right and the left tread-boards is respectively supported by the two supporting rods directly or indirectly. The driving device has high work doing efficiency; moreover, with the elliptical sports machine, the user can directly acknowledge of the inclined degree of the tread-board orbit.

The invention discloses a method and a device for improving interlayer bonding force of a fiber reinforced building plate. The method comprises the following basic steps of a, adding slurry to a forming cylinder layer by layer by rotating to form a wet blank; b, when the wet blank reaches a certain thickness, enabling array needles on a plurality of arc-shaped acupuncture tiles above the forming cylinder to be in contact with and inserted into the wet blank gradually, and generating corresponding array holes; c, continuing receiving the slurry by the array holes so that the array holes are filled to form array rivets, and stripping the array rivets after the wet blank reaches the thickness; and d, pulling the arc-shaped acupuncture tiles to a starting side, and repeating the process aboveto realize continuous production. The device comprises the forming cylinder, the plurality of the arc-shaped acupuncture tiles, hinges, the array needles, an elliptical closed orbit, universal joints,hanging rods, a pulling motor, a control system, a lifting system and the like. The method and device disclosed by the invention are easily combined to a conventional copying method or slurry flowingmethod production line at present, and do not have limitation on components, thickness and the like of materials; and the performance of the obtained fiber reinforced building plate with improved interlayer bonding force is greatly improved.

The present invention relates to a device for generating a variable angular momentum or torque, which has a container (1) partially filled with a magnetizable fluid (2) and a device for generating one or several rotating or wandering magnetic fields, with which the magnetizable fluid (2) in the container (1) can be made to continuously move on a closed orbit. The device for generating the rotating or wandering magnetic fields has several electric coils (4), whose coil axes lie in the orbital plane. This structure makes it possible to generate a variable angular momentum without mechanical moved parts or the necessity of external magnetic fields. For example, the device enables a simple and cost-effective spacecraft attitude control.

The invention belongs to the technical field of carrier rocket guidance. The invention particularly provides an accurate control method for a launch vehicle fire-strike launching orbit. The method comprises the following steps: when a flight section of the carrier rocket is a final-stage injection section or a final speed correction section, determining a shutdown amount of the carrier rocket in a current control period according to a first shutdown control parameter of the carrier rocket; and determining whether shutdown control needs to be performed on the carrier rocket according to the shutdown amount of the carrier rocket in the current control period. Based on the technical scheme provided by the invention, when the operation orbit of the carrier rocket is transited to the non-closed orbit from the closed orbit, the high-precision and reliable shutdown requirement of the orbit energy state is met.