Abstract

A method for generating a chatter-free tool axis vector in five-axis machining of a ball-end cutter. First, a representative tool axis vector is determined at a key cutter location point according to a Nyquist stability criterion, a key tool axis vector set is constructed, and by means of a four-element interpolation algorithm for vectors, interpolation is then performed on the key tool axis vector set in a general region, so as to generate a smooth tool axis vector; then, the machining stability of each cutter location point is checked, if chatter occurs, at a cutter location point where chatter occurs, a steepest descent method is used to determine chatter-free tool axis vectors having the minimum angle change relative to an original tool axis vector, and the chatter-free tool axis vectors are added to the key tool axis vector set; then, interpolation is performed on the basis of the key tool axis vector set, so as to obtain a new tool axis vector; and the process is repeated until tool axis vectors of all the cutter location points pass a cutting stability check. In this way, a smooth and chatter-free tool path can be generated along a tool path, thereby effectively inhibiting cutting vibration during multi-axis machining.

IPC Classes  ?

• G05B 19/19 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by positioning or contouring control systems, e.g. to control position from one programmed point to another or to control movement along a programmed continuous path

Abstract

A fixing device for temperature sensors in a combustion chamber of a solid rocket engine, comprising anti-static materials (1) and an elastic supporting part. The two anti-static materials (1) are fixedly installed at two ends of the elastic supporting part, respectively, and the outer side surfaces of the anti-static materials (1) are surfaces in contact with the inner wall surface of an annular grain in a combustion chamber of a solid rocket engine. The shapes of the outer side surfaces of the anti-static materials (1) match that of the inner wall surface of the annular grain in the combustion chamber of the solid rocket engine. Inlay recesses used for fixing temperature sensors are formed on the outer side surfaces of the anti-static materials (1). The elastic supporting part has a compression preload, and by means of the compression preload, the anti-static materials (1) at the two ends can be always attached to the inner wall surface of the annular grain in the combustion chamber of the solid rocket engine. The fixing device for temperature sensors in a combustion chamber of a solid rocket engine achieves the adaptive installation work of temperature sensors on a grain surface, can be applied to sensor installation when the grain has large deformation in different high and low temperature states, and prevents the sensors from falling off.

IPC Classes  ?

• G01K 1/143 - SupportsFastening devicesArrangements for mounting thermometers in particular locations for measuring surface temperatures
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• F02K 9/32 - Constructional partsDetails not otherwise provided for
• F02K 9/96 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by specially adapted arrangements for testing or measuring

Abstract

The present invention provides a solid rocket engine rear skirt connection mechanical arm type interstage separation test device and method. The separation test device comprises a front embracing ring assembly, a rear embracing ring assembly and a connecting rod, wherein the front embracing ring assembly and the rear embracing ring assembly each comprise an upper embracing ring, a lower embracing ring, a mechanical arm and a roller assembly; a rear connecting plate is further fixed at an outer end of the rear embracing ring assembly; several connecting holes which are uniformly distributed in a circumferential direction are provided in the rear connecting plate and are configured for connecting a rear skirt of a sub-stage engine; two circumferential sides of an outer surface of the upper embracing ring are each provided with an interface structure that is connected to the mechanical arm; and the interface structure can be fitted to an arc plate structure at one end of the mechanical arm, such that the mechanical arm can move along the outer surface of the upper embracing ring by means of the arc plate structure in a circumferential direction and is fixed after moving in place. The separation test device is convenient in that all the assembly processes are carried out on the ground, and the separation test device is lifted after assembly and does not need to be assembled at a high altitude; and all the adjustments are integrated on the mechanical arm, debugging is easy, and the safety is improved and the working efficiency is also improved.

IPC Classes  ?

• F02K 9/96 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by specially adapted arrangements for testing or measuring
• F02K 9/32 - Constructional partsDetails not otherwise provided for

Abstract

A thrust transfer apparatus for an ignition test of a solid rocket engine in a form of rear skirt connection, comprising a front end connecting plate (16), a base (20), a rear skirt connecting plate (14, 17), an arc-shaped seat (12), a connecting rod (11), and a hoop (13). The lower surface of the base is connected to a test movable/fixed frame platform; the front end connecting plate is fixed to one end of the base in a right-angle welding manner, and the front end connecting plate is connected to a force measuring assembly required by the test; the rear skirt connecting plate is connected to a rear skirt flange plate of the solid rocket engine, the rear skirt connecting plate is of an upper-lower split structure and is divided into a rear upper connecting plate (14) and a rear lower connecting plate (17), and the rear lower connecting plate is fixed to the other end of the base in a right-angle welding manner; the center of the rear skirt connecting plate consisting of the rear upper connecting plate and the rear lower connecting plate is provided with a central through hole having an aperture larger than the diameter of a cylinder at the rear skirt part of the fixed rocket engine to be tested; the arc-shaped seat is mounted on the base in a height-adjustable manner for directly supporting the solid rocket engine; and a detachable thrust connecting rod is mounted between the front end connecting plate and the rear skirt connecting plate.

IPC Classes  ?

• F02K 9/96 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by specially adapted arrangements for testing or measuring