RU2153155C2 - Stand to study process of separation of propelled object - Google Patents

Abstract

FIELD: testing equipment, equipment for experimental aeroballistic investigations. SUBSTANCE: stand includes bed frame that carries acceleration gear coming in the form of barrel and source of pressure, piston put into barrel, braking unit located ahead of section of barrel, unit fixing propelled object, carriages mounted for connection with propelled object. Longitudinal axes of guides are placed in pairs in planes crossing along line coinciding with longitudinal axis of barrel and carriages. Damping bushings made of plastic material and having bulges in direction of motion of propelled object are installed in carriages uniaxially to guides. Carriages are put on guides for movement of each part of propelled object along separate pair of guides. Length of piston is chosen from condition ensuring contact of one part of propelled object with butt of piston first in direction of movement. Braking unit is manufactured in the form of metal bushings mounted on guides whose external surfaces have shape of truncated cone. Stand makes it possible to study process of separation of propelled object into composite parts which takes place when propelled object achieves preset overload in process of acceleration, subsequent independent movement of composite parts by inertia and their braking without mutual collision, to allow cost of process of separation of object to be reduced and to ensure possibility of repetition of experiment. EFFECT: expanded functional capabilities. 2 cl, 4 dwg

Description

 The invention relates to a testing technique. The primary field of application is the technique of experimental aeroballistic research.

 One of the problems that can be solved in the formulation of aeroballistic research is the study of the process of separation into components of objects thrown from ballistic installations, and the joint flight of components (see, for example, Yu.L. Karpov and others. To the calculation of the separated flow between two bodies , "Mechanics of liquid and gas", N 3, 1968, p.90).

 To create devices that provide the required parameters of the process of separation of missile objects, their preliminary development at the stand is necessary.

 Known installation of an explosive type for mechanical testing (shock stand), containing an accelerating device made in the form of a barrel and a pressure source, consisting of several explosive chambers with explosive charges. In the trunk, acceleration, drainage and brake compartments are made. The internal cavities of the blast chambers and the booster compartment are separated by partitions with throttle openings. Smooth braking of an object is achieved due to the inelastic attachment of a mass of polyethylene chips and deformation of the brake damper located in the brake compartment of the barrel (see S. A. Novikov et al. Explosive-type installations for mechanical tests, “Combustion and Explosion Physics”, N4, 1989, pp. 147-151).

 Closest to the proposed technical solution is the stand selected for the prototype for impact testing of products selected as a prototype (see Russian patent N 2009456C1, IPC5 G 01 M 7/08, publ. 15.03.94, bull. N5).

 This stand contains a base, an acceleration device mounted on it, made in the form of a pressure source and a barrel, in which a piston with the test object, a piston-striker and a piston-inertial mass are placed, a brake device located in front of the barrel cut. The piston is loaded with the test object through an air cushion with a striking piston dispersed by compressed air. After loading, the piston with the test object is braked in the barrel when interacting also through an air cushion with inertial mass. The inertial mass is braked outside the barrel using dampers placed in the guide cylinder. In the wall of the barrel at the end of the acceleration section of the piston-striker and in the area between the piston for fixing the test object and the inertial mass, windows are made to relieve gas pressure.

 The disadvantage of the analogue and the prototype is the inability to study the process of separation of the test object without the mutual collision of its components during braking.

 The technical task to be solved is to provide the possibility of studying the process of separation of the test object, including testing the device for separation of the object, which is triggered by the action of a given overload, the subsequent autonomous movement of the components by inertia and their braking without mutual impact.

 EFFECT: obtaining information on parameters characterizing the process of separation of an object to be thrown from a ballistic installation, ensuring the possibility of repeatability of the experiment, reducing the cost of working out the process of separation of the object.

 The technical problem is solved due to the fact that in the test bench for the separation process, consisting of detachably connected parts of a missile object, containing a base on which an accelerating device is installed, made in the form of a barrel and a pressure source, a piston is placed in the barrel, a device for fixing a missile object and a brake device located in front of the cut of the barrel, a device for securing a missile object is made in the form of guides installed outside the barrel, the longitudinal axis of which is located enes pairwise in planes intersecting along a line coinciding with the longitudinal axis of the barrel, and configured to connect to the meta object carriages. Moreover, in the carriages coaxial with the guides installed damper bushings of plastic material, made with thickenings in the direction of movement of the missile object. The carriages are placed on the rails so that each of the parts of the missile object can be moved along a separate pair of rails. The length of the piston is selected from the condition of ensuring contact of one of the parts of the missile object with the front end of the piston in the direction of movement. The brake device is made in the form of metal bushings mounted on the guides, the profile of the outer surface of which can be in the form of a truncated cone, facing a smaller base towards the projectile. It is also possible to perform metal bushings consisting of coaxially arranged one cylindrical and the other with the outer surface profile in the form of a truncated cone of parts, the smaller base of the conical part of the sleeve facing the object being thrown, and the diameter of the larger base equal to the diameter of the side surface of the cylindrical part. The lengths of the metal bushings for each individual pair of rails are selected from the condition of ensuring the braking of parts of the missile object without impacting with each other. Metal bushings are mounted on rails with the possibility of limiting their movement in the direction of movement of the object.

A comparative analysis of the proposed solution and the prototype showed that the claimed stand is characterized by a combination of new design features:
a device for securing a missile object is made in the form of guides and carriages mounted outside the barrel;
the longitudinal axis of the guides are arranged in pairs in planes intersecting along a line coinciding with the longitudinal axis of the barrel;
carriages are configured to be connected to a missile object;
Damper bushings are installed in the carriages;
damper bushings are installed coaxially with guides;
damper bushings are made of plastic material;
the damper bushings have a thickening in the direction of movement of the propelled object;
the carriages are placed on rails with the possibility of moving each of the parts of the missile object along a separate pair of rails;
the length of the piston is selected from the condition of ensuring contact of one of the parts of the missile object with the front end of the piston in the direction of movement;
the brake device is made in the form of metal bushings;
metal bushings are mounted on rails with the possibility of limiting their movement in the direction of movement of the object;
the profile of the outer surface of the metal bushings may be in the form of a truncated cone, the smaller base of which is located first in the direction of movement of the missile object;
the metal bushings of the brake device may consist of one cylindrical located coaxially, the other - with the profile of the outer surface in the form of a truncated cone of parts, the smaller base of the conical part of the metal sleeve is located first in the direction of movement of the missile object, the diameter of the larger base of the conical part of the metal sleeve is equal to the diameter of the side surface cylindrical part;
the length of the metal bushings for each individual pair of rails is selected from the condition of ensuring the braking of parts of the missile object without impacting with each other.

 The implementation of the device for securing a missile object in the form of guides with carriages mounted outside the barrel makes it possible to investigate the process of separating missile objects of arbitrary shape and dimensions and allows the object to slide along the guides. The location of the longitudinal axes of the guides in pairs in planes intersecting along a line coinciding with the longitudinal axis of the barrel provides an instantaneous loading of parts of the missile object during their braking.

 Installing damper bushings in the carriages makes it possible to brake parts of the missile object during the interaction of the damper bushings with the brake device.

 Installing the damper bushings coaxially with the guides eliminates the seizure of the missile object and its parts when moving them along the guides. The implementation of the damper bushings of plastic material reduces the amount of overload during the interaction of the damper bushings with brake devices.

 The presence of thickening of the damper bushings in the direction of movement of the missile object prevents them from being squeezed out of the carriages when interacting with brake devices.

 Placing the carriages on the rails with the possibility of moving each of the parts of the missile object along a separate pair of guides makes it possible to brake both parts of the missile object without their mutual impact using brake devices mounted on the rails.

 Ensuring the contact of one of the parts of the missile object with the front in the direction of movement of the end face of the piston provides shockless acceleration of the missile object.

 The implementation of the brake device in the form of metal bushings makes it possible to reuse it.

 The installation of metal bushings on the rails with the possibility of limiting their movement in the direction of movement of the object provides braking of the parts of the missile object by interacting with the damper bushings installed in the carriages.

 The execution of the profile of the outer surface of the metal bushings in the form of a truncated cone allows you to change the value of the braking force during the interaction of the damper bushings of plastic material with metal bushings.

 The location of the metal bushings with a smaller base first in the direction of movement of the missile object provides a smooth increase in overload when braking parts of the missile object.

 The execution of metal bushings consisting of one located coaxially one - cylindrical, the other - with the profile of the outer surface in the form of a truncated cone, parts is advisable if there is a restriction on the transverse dimensions of the metal bushings, carriages and damper bushings and there is no limit on the length of the metal bushings.

 The invention is illustrated by drawings.

 Figure 1 shows a diagram of a stand for investigating the process of separation of a missile object, figure 2 - section aa, figure 3 - section bb, figure 4 - section bb.

 The inventive stand includes a base 1 on which four guides 2 are made, made in the form of rods, and an accelerating device including a pressure source (charging chamber) 3 and barrel 4. A powder charge 5 and an initiating device 6 are placed in the charging chamber 3 The piston 7 is located in the barrel 4, which protrudes beyond the cut of the barrel 4. The missile object can consist of two detachably connected parts: the rear 8 and the front one worn on it 9. The rear part 8 of the missile object, in turn, is put on the barrel 4 until it stops in the front direction zheniya end of the piston 7. The parts 8 and 9 are connected to the propelled object carriages 10, which are aligned with the guide 2 damper bushing 11 of plastic material formed with a bulge in the moving direction of the propelled object. The carriages 10 of each of the parts of the missile object are placed in pairs on their own pair of guides 2 and have the ability to move freely along them. In the missile object, a pyrotechnic separation mechanism 12 can be installed, protruding into the cavity 13 formed by the shared parts of the missile object. The brake device is located in front of the cut of the barrel 4 and is made in the form of metal sleeves 14. The metal sleeves 14 can be made with the profile of the outer surface in the form of a truncated cone or consist of coaxially arranged one cylindrical, the other with the profile of the outer surface in the form of a truncated cone, parts moreover, the smaller base of the sleeve with the profile of the outer surface in the form of a truncated cone is located first in the direction of movement of the missile object, and the diameter of the larger base is equal to the diameter of the lateral surface rhnosti cylindrical portion. The restriction of the movement of metal sleeves 14 in the direction of movement of the object is carried out in this case using the racks 15.

 The functioning of the stand is as follows.

 When an electric pulse is applied to the initiating device 6, the powder charge 5 placed in the charging chamber 3 is ignited. The resulting powder gases are pressed against the piston 7 located in the barrel 4. The piston 7, leaning with its front end into the rear part 8 of the missile object, worn on the barrel 4, pushes the missile object. Under the influence of overload arising during acceleration of a missile object, the pyrotechnic separation mechanism 12 is activated, the combustion products of which fall into the cavity 13 formed by the rear 8 and the front 9 parts of the missile object worn on it. After reaching a predetermined pressure in this cavity, the divergence of parts 8 and 9 of the missile object begins (front part 9 is pulled from the rear part 8). The movement of parts of a missile object in the process of joint acceleration, separation and subsequent autonomous movement is carried out along its pair of guides 2. After the front carriages reach the metal bushings 14 installed on their way, braking of parts 8 and 9 of the missile object begins.

 The lengths of the metal bushings 14 are such that the braking of both parts of the missile object begins at the same time, or the rear part 8 of the missile object and then the front part 9 begin to brake first. This ensures that no parts of the missile object collide during their braking. Braking is carried out due to the deformation of the damper bushings 11 when they interact with metal bushings 14, which consist of parts aligned coaxially with the other, with the profile of the outer surface in the form of a truncated cone, the smaller base of the sleeve with the profile of the outer surface in the form of a truncated cone the first in the direction of movement of the missile object, and the diameter of the larger base is equal to the diameter of the side surface of the cylindrical part.

 In the process of acceleration of the missile object, its separation into components, their inertia and subsequent braking, the pressure of the powder gases in the barrel 4 and in the cavity 13 between the separated parts 8 and 9 of the missile object is recorded, as well as the overload and speed of movement of these parts. (Sensors recording these parameters are not shown in FIGS. 1-4).

Claims (3)

 1. A stand for studying the separation process of a missile object, consisting of detachably connected parts, containing a base on which an accelerating device is installed, made in the form of a barrel and a pressure source, a device for securing a missile object, a piston located in the barrel, a brake device located in front of a cut of the barrel, characterized in that the device for securing the missile object is made in the form of guides installed outside the barrel, the longitudinal axes of which are arranged in pairs in planes intersecting along a line coinciding with the longitudinal axis of the barrel, and made with the possibility of connecting carriages with a missile object with coaxial damper bushings made of plastic material installed in them, made with a thickening in the direction of movement of the missile object, placed on guides with the possibility of moving each of parts of the missile object along a separate pair of guides, the piston length is selected from the condition of ensuring contact of one of the parts of the missile object with the front in the direction movement of the piston end face, the braking device is configured to restrict their movement in the direction of the object’s movement on the metal guide rails, the length of which for each individual pair of guides is selected from the condition that the parts of the missile object are braked without collisions with each other.  2. The stand according to claim 1, characterized in that the metal bushings of the brake device are made with the profile of the outer surface in the form of a truncated cone, the smaller base of which is located first in the direction of movement of the missile object.  3. The stand according to claim 1, characterized in that the metal bushings of the brake device are made up of one located coaxially — cylindrical, the other — with the profile of the outer surface in the form of a truncated cone, parts, the smaller base of the sleeve with the profile of the outer surface in the form of a truncated cone , parts, and the smaller base of the sleeve with the profile of the outer surface in the form of a truncated cone is located first in the direction of movement of the missile object, and the diameter of the larger base is equal to the diameter of the side surface of the cylinder indric parts.

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