8 results about "Shock wave" patented technology

The compressor blades of an aircraft engine are, in at least one natural-vibration critical area, designed such that at the blade leading edge (6), the leading edge shock wave (14) attaches to the leading edge (6), as a result of which a laminar boundary layer flow (7) on the suction side (13) quickly transitions into a turbulent boundary layer flow (9) which is kept constant and prevented from re-lamination by the further, continuous curvature of the suction side. Therefore, the transition, whose periodic movement is also suppressed, cannot communicate with a suction-side compression shock (10), preventing the compression shock from augmenting the natural vibrations of the blade occurring under certain flight conditions. The blade leading edge can, for example, be designed as an ellipse with a semi-axis ratio equal to or smaller than 1:4.

The invention provides an unsteady impact wave generation method for numerical simulation. The unsteady impact wave generation method for the numerical simulation comprises the following steps. Step 1, one boundary of a numerical simulation flow field is chosen to be an impact wave boundary; step 2, a coordinate x s and an impact wave angle beta of a point of incidence of the impact wave are set on the impact wave boundary; step 3, a parameter condition, namely, the parameter condition of a known impact wave front airflow, of a front boundary of the impact wave is set; step 4, a parameter condition of a rear boundary of the impact wave is determined according to an impact wave relation; and step 5, an unsteady impact wave is generated in the numerical simulation. According to the unsteady impact wave generation method for the numerical simulation, the unsteady impact wave easy to control is generated and the method is simple and easy.

A system and method for treatment of adipose tissue. One or more shock waves are generated focused on a region of adipose tissue located between 0.2 and 3 cm below the skin surface.

The invention provides an aircraft aerodynamic layout method and device capable of meeting a wide-speed-domain waverider performance and a medium. The layout method comprises the following steps: establishing a basic shape, and drawing a grid for a computational domain of the basic shape; performing flow field calculation on the calculation domain of the basic shape by adopting a shock wave assembly method, and respectively performing calculation according to the state parameters of the ballistic points to obtain a flow field stability solution and a stable shock wave surface; for shock wave surfaces obtained by calculating flight Mach numbers from large to small, selecting a cutting position from the windward sides in the flow direction of the shock wave surfaces respectively, cutting theshock wave surfaces, taking obtained cutting lines as leading edge lines of the windward sides of the waverider, taking points on the cutting lines as starting points, and obtaining the waverider surfaces through a streamline tracking method. The length and the width of each cutting line are multiplied by a coefficient according to the actual length requirement of the wave rider design, the actual length requirement and the actual width requirement are met, and then the leeside of the wave rider is obtained according to the filling ratio requirement of the wave rider design.

The invention relates to the field of shock wave measurement methods and techniques, specifically to a comparison-type calibration method for shock wave measurement. The comparison-type calibration method comprises the following steps of: 1) clamping ballistic rifles with different calibers on a fixed shooting platform; 2) placing a calibrated noise measurement system and a shock wave measurement system to be calibrated at equal distance respectively from left and right sides of the ballistic rifles in the shooting direction; 3) conducting shooting via the ballistic rifles with different calibers, and simultaneously acquiring, in real time, shock waves generated by the calibrated noise measurement system and the shock wave measurement system to be calibrated during the ball firing; 4) performing statistics of acquired mass data, and figuring out a linear regression equation about a noise peak and a shock wave peak; and 5) correcting, by using the linear regression equation in the step (4), the shock wave pressure peak acquired after the measurement. The comparison-type calibration method of the invention comprehensively improves the shock wave measurement precision and solves the problem that there is no way to carry out field calibration for shock wave measurement.

The invention discloses an extracorporeal shock wave therapy handle with an adjustable volume. The extracorporeal shock wave therapy handle comprises a gas pipe, a cone, a gas pressure inlet, a therapy head, an outer gas chamber and a volume adjusting device, wherein the cone can move in a reciprocating way in the gas pipe; the gas pressure inlet is arranged at one end of the gas pipe; the therapy head is arranged at the other port of the gas pipe; the outer gas chamber is communicated with the gas pipe so that gas in the outer gas chamber can enter the gas pipe and a rebound speed of the cone is improved; and the volume adjusting device is used for adjusting the volume of the outer gas chamber 4. According to the extracorporeal shock wave therapy handle with the adjustable volume, provided by the invention, extracorporeal shock wave therapy is carried out by utilizing a pneumatic ballistic shock wave source; and the extracorporeal shock wave therapy handle is high in accuracy, low in energy consumption, small in volume and convenient and flexible to use.