34 results about "Control loading system" patented technology

The present invention discloses a simulation test table of tunnel structure, surrounding rock and underground water interaction, belonging to the field of underground engineering simulation test technology. Said test table is formed from the following four portions: (1), reaction frame; (2), hydraulic servo control loading system; (3), water pressure loading and sealing system; and (4), hydraulic loading and data acquisition computer control system.

The invention discloses a water permeability test method of jointed rock, which includes the steps as follow: preparing a sample of natural jointed rock; putting the sample in the inner of shearer core which is arranged at the inner cavity of a shearing box, providing a test environment to simulate the natural crack of jointed rock with water and the hydraulic stress; testing and collecting the stress and the displacement of the sample as well as the flow and intake pressure and outlet pressure of the liquid surrounding the sample; controlling the loading system, the detecting system and the hydraulic system according to the mining-induced fissure of the sample, promptly testing and collecting the dynamic changing data of the crack deformation, the stress, the flow and the water pressure of the sample; analyzing and processing the testing data result, and constantly maintaining the tester of the sample balance in the whole structure through the balance system in the test. The invention has simple procedure, convenient operation, wide application range and great practicability; and the invention can precisely test the related parameter of the dilatability of natural joint and the permeability, and the test precision is high.

The invention discloses a helicopter control load system based on a real-installed control lever system, which mainly includes three parts: human-sensing loading equipment, matching lever systems, control components and control loading system software, which can realize the simulation of the control load system in helicopter flight training , to meet the static and dynamic maneuvering characteristics of the helicopter under different flight conditions and different maneuvering modes. The invention also discloses a method for realizing the simulation of the helicopter control load system based on the control system of the control system. Firstly, the control system of the control system is equipped with the control system according to the structure of the control system; human-feeling loading equipment is installed at the corresponding position of the control load system. , and connected to the supporting rod system by connecting the rocker arm, the human sense loading equipment is installed; the human sense loading device, the rudder control box and the control computer are connected through the aviation cable; the control load system is completed through the control software Control to realize the maneuvering characteristics in various flight states.

The invention discloses an ocean engineering pile foundation experiment simulation apparatus and method under long-term horizontal cyclic loading. The apparatus comprises: an osmotic force system which provides continuous pressurized water for a saturated sandy soil foundation so that a uniform osmotic flow field forms in the sandy soil foundation to simulate a hyper-gravity environment; a displacement control loading system and a force control loading system that apply horizontal cyclic loadings to an offshore wind turbine superstructure model; a measuring system used for measuring water pressure before the entry into the saturated sandy soil foundation, displacements of the offshore wind turbine superstructure model and a pile model, strain of the pile model, and surface displacement of sandy soil; an uninterrupted power supply system used for powering the osmotic force system, the displacement control loading system, the force control loading system and the measuring system, thereby ensuring all systems can run stably in a long time; the invention also provides an experiment method of the apparatus; the apparatus and the method are widely applicable and suitable for various ocean engineering structures such as oil platforms and offshore wind turbines.

The invention discloses a method for simulating strength of a reversible control loading system of a flight simulator. A stick force simulation model identical with a reversible control system of a real plane is built, and is provided with a servo trim tab. Due to the fact that the level force simulation model and the real plane are the same in actual composition, force generated by the servo trim tab can be independently debugged, debugging is simplified compared with a hinge moment coefficient adjusting method in the prior art, the time for debugging and the production cycle of a product are shortened, and the time for debugging is shortened by 42.5% compared with the hinge moment coefficient adjusting method. Therefore, product competitiveness is improved; the level force simulation model is suitable for simulating force of a joystick, with a servo trim tab, of the reversible control system of the plane, and also suitable for stimulating force of a joystick, without the servo trim tab, of the reversible control system of the plane; coefficients of the level force simulation model can be modified along with the actual control of the simulated plane, and the level force simulation model has universality. According to the method for simulating strength of the reversible control loading system of the flight simulator, influence caused by aerodynamic force on hinge moment of a control surface is effectively eliminated, and fidelity of simulation of force of the joystick of the reversible control system is improved.

The invention provides a control loading system for a drive operation system of a flight simulator. The system includes an aircraft real data storage, a data motion calculation server and a data calculator, a hydraulic pressure servo computer. The data operation calculation server includes a configuration modeling module, a mechanics modeling module, a data verification module and a matching module. The hydraulic pressure servo computer includes a control module, a simulation communication verification module and a data collection module. The data collection module is in communicational connection with a motion platform through a motion platform communication module. The data collection module is in communicational connection with a driver cabin instrument through a driver cabin instrumentcommunication module. According to the invention, different hydraulic pressure auxiliary power systems are controlled through aircraft real flight data to generate simulation auxiliary power identical to practical flight auxiliary power. The simulation auxiliary power counteracts with a part of resistance of an operation mechanism, so that a driver can have a true force feeling of operation, thereal state during a flight of an aircraft can be simulated effectively and the dynamic simulation degree is high.