50results about How to "Quick maneuver" patented technology

The invention discloses a saturated sliding mode variable structure control method for rapidly maneuvering attitudes of satellites. The saturated sliding mode variable structure control method includes steps of 1, acquiring current attitudes of the satellites and acquiring attitude errors of the current attitudes of the satellites relative to target attitudes; 2, determining bandwidths, damping coefficients, the maximum torque of actuating mechanisms, torque regulation coefficients and fundamental frequencies of flexible accessories, and computing control parameters for rapidly maneuvering the attitudes of the satellites; 3, computing saturated sliding mode surfaces of the satellites in rolling directions and computing linear sliding mode surfaces of the satellites in pitching and yawing directions; 4, acquiring control torque by means of computation; 5, acquiring corresponding control instructions for the actuating mechanisms by the aid of the control torque acquired in the step 4, transmitting the instructions to the corresponding actuating mechanisms and controlling the actuating mechanisms to rapidly maneuver the attitudes of the satellites. The saturated sliding mode variable structure control method has the advantages that the method is simple and reliable and is low in computational complexity, the satellites can be rapidly maneuvered and stabilized by the aid of the saturated sliding mode variable structure control method, accordingly, the attitude maneuvering time can be shortened, and the saturated sliding mode variable structure control method is obviously superior to other methods.

A novel mast mechanical equipment vertical assembling foundation is a regular polygon prism, cylinder or polygon prism concrete independent foundation structure which is obtained by vertically assembling the concrete prefabricated part. The invention is widely suitable for the mast mechanical equipment which periodically moves or is fixedly used in fields of building, electric power, information,geological industry and military industry. The invention is mainly characterized in that the horizontal side pressure and the friction of the foundation soil are fully utilized for increasing the dumping resistance of the foundation. The invention has the advantages of small accommodation area, high installing and detaching velocity, no water operation on the construction side, providing new condition for the foundation installing at the high-cold and dry areas, predominant resource-saving and energy-saving and environment-protecting benefits, and evident economic benefit.

The invention discloses a subminiature tethered balloon system and relates to the field of tethered balloons. The system comprises a balloon body system, a winch system, an inflation system, a ground control and receiving system, a mooring rope system, a loading system and a containing and carrying system. A balloon body in the balloon body system is a flat round rotary balloon body, the wind-resistant effect is good, stability is good, winding and unwinding are convenient, and occupied space is small. A power system in the winch system is a winding and unwinding manual rocker or a winding and unwinding motor, and is convenient to carry. The subminiature tethered balloon system is easy and convenient to operate, the number of operators in need is small, quick deployment can be achieved, and the tethered balloon system is flexible. Requirements of sites are low, and the tethered balloon system can be unfolded and released in cities, countryside or remote areas.

The invention provides a satellite platform having dynamic imaging capability. The satellite platform comprises a load cabin, a platform cabin and a non-contact magnetic suspension mechanism arranged between the load cabin and the platform cabin. The satellite platform has the following innovative design: 1) The performance is excellent: a technical bottleneck it is difficult to measure and control micro-vibration and a large flexibility influence exists is solved thoroughly, fast maneuver and rapid stabilization of the load cabin are implemented, and high stability in the maneuvering process can be ensured. 2) requirements for platform cabin precision are not high, and the load performance is implemented easily: inertia separation of the two cabins is implemented through 'dynamic and static isolation' in space, requirements of controlling the platform cabin to follow precision of the load cabin are not high, which is equivalent to that the rigid load cabin can concentrate on super-agile dynamic imaging tasks, and the precision is implemented easily. 3) Inertia constraint contradiction is eliminated, the scalability is high: through 'dynamic and static isolation non-contact and principal and subordinate cooperation high-precision', a bottleneck problem of inertia requirement contradiction in agility and stability is solved, and the satellite platform not only is suitable for small satellites, but also is suitable for medium-sized or large satellites.

The invention relates to a discretization method for shortening delay generated when a reaction wheel is connected into a semi-physical system. The discretization method comprises the steps that 1, the rotating speed pulse numbers and turning signals of the reaction wheel are collected by a ground dynamic simulation computer; 2, threshold value judgment is conducted on a difference value of the rotating speed pulse numbers in the adjacent sampling periods, the turning signals are filtered, and the rotating speed pulse number and the turning signal in the current sampling period are obtained; 3, the current rotating speed of the reaction wheel is calculated; 4, differential processing is conducted on the rotating speeds in the adjacent sampling periods, and the current control moment output by the reaction wheel is calculated; 5, amplitude limiting processing is conducted on the output control moment; 6, the output control moment and the rotating speed are input to a satellite dynamic model to achieve closed-loop control over the ground satellite attitude control system. According to the discretization method, system delay can be shortened, the influences on the phase stabilization margin of the system are reduced, the test precision of the satellite attitude control system is improved, and high stability and rapid maneuvering capacity of ground satellite attitude controlling are achieved.

The invention relates to a duct type multi-rotor tethered drone and a control system thereof, belongs to the field of drones, and aims to solve the problems that existing drones are short in flight duration and prone to crash due to the fact that the rotors of the drones are exposed. The duct type multi-rotor tethered drone is characterized in that the an inner central pipe is connected with an outer duct pipe through a group of guide vanes, a group of carbon fiber pipes is fixedly mounted on the outer wall of the lateral side of a block formed by central plates, the middle section of each carbon fiber pipe is fixed with the wall of the duct pipe, and an auxiliary rotor is mounted at the tail end of each carbon fiber pipe through an auxiliary motor; a hardware control system is mounted onthe upper surface of the central plate block, a main motor is coaxially mounted on the lower surface of the central plate block, the main motor drives a main rotor, and a power supply system is arranged beside the main motor; the hardware control system is connected with the main motor, a group of auxiliary motors, the power supply system, a video collecting unit and an automatic pilot, and a tether is connected with the hardware control system, the main motor, the group of auxiliary motors and the video collecting unit through the power supply system. The duct type multi-rotor tethered dronecan constantly work around the clock.

The invention provides a slight-splashing high-performance two-hull amphibious aircraft which comprises an aerodynamic lift type main fuselage, wings, empennages, turbofan engines and slight-splashing sliding hulls. The wings 2 are arranged in the middle of the aerodynamic lift type main fuselage. The turbofan engines are arranged on the upper position, near the aerodynamic lift type main fuselage, of the wings. The empennages are arranged at the tail end of the aerodynamic lift type main fuselage. The two slight-splashing sliding hulls are arranged on the two longitudinal sides of the lower portion of the aerodynamic lift type main fuselage. A longitudinal aerodynamic groove channel 5 is formed after the connection of the two slight-splashing sliding hulls and the aerodynamic lift type main fuselage. The aerodynamic lift type main fuselage is provided with reverse profile planing steps which divide the aerodynamic lift type main fuselage into a front fuselage body and a rear fuselage body. An upper transverse bent sliding face and a lower transverse bent sliding face are arranged in the position, at the bottom of each slight-splashing sliding hull, on the sliding face of the front fuselage body sequentially from inside to outside. The anti-wave ability of the amphibious aircraft is improved, and the amphibious aircraft has an excellent hydrostatic and wave splashing controlling ability to adapt to a more complex marine environment.

The invention relates to the field of flood control and emergency rescue of the Yellow River, in particular to a depth-limited portable bridge for bursting rescue, comprising a modular portable bridgecage emergency rescue device and a bridge leg depth limiter, wherein the bridge leg depth limiter is directly stuck at the reserved position of the bridge leg of the portable bridge cage emergency rescue device, and then a throwing operation is carried out by using the portable bridge. The portable bridge for bursting rescue can be quickly assembled on the spot, and a cage-leg portable bridge isestablished at the crevasse, and the problems of low load bearing force and inclined instability of the quick-built convenient bridge are solved by utilizing the bridge-leg depth limiter, and the damcrevasse can be effectively repaired in the first time, and the transportation is light and quick, and the construction step is simple, and the application range is wide.

The invention belongs to the technical field of bionic underwater propellers, and particularly relates to a two-joint bionic fishtail device capable of swinging at a high speed. The fishtail comprisesa fishtail front part, a fishtail middle part and a fishtail tail fin, a driving device mounting frame, a driving shaft, a first crankshaft and a second crankshaft are arranged in the fishtail frontpart; a first joint driven shaft is arranged at the front end of the fishtail middle part; and a second joint driven shaft is arranged at the front end of the fishtail tail fin. During operation, thedriving shaft is driven by a motor to rotate so as to drive the first crankshaft and the second crankshaft to rotate through gears, the first crankshaft and the second crankshaft drive the first jointdriven shaft and the second joint driven shaft to rotate through the belts arranged on connecting rod journals in a sleeving mode correspondingly, and the bionic fishtail swinging is achieved. The high-speed swinging of the double-joint bionic fishtail can be achieved only through the single motor, and the rapid maneuvering of the robotic fish is achieved.