CN112228247A

CN112228247A - Guide vane type sleeve type grain structure with honeycomb holes

Info

Publication number: CN112228247A
Application number: CN202010982944.9A
Authority: CN
Inventors: 张群; 王紫欣; 王晓燕; 高耀红; 马晓曦
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2020-09-18
Filing date: 2020-09-18
Publication date: 2021-01-15

Abstract

The invention provides a guide vane type sleeve type grain structure with honeycomb holes, wherein a series of honeycomb holes are arranged on the inner surface of a grain on the outer side of a sleeve type, guide vane structures are uniformly arranged on the outer surface of a central grain, and the diameter of the central grain is increased along with the increase of the axial length. The face also can backward move when the gas is at the inside flow of powder column, when the gas flows through this structure, some gas flows along the axial and leads the flow of blade structure and produce the whirl, make the torrent viscosity and the temperature gradient on powder column surface bigger, and then improved powder column surface heat flux density, the powder column surface convection heat transfer has been strengthened, the propellant burning rate has been showing and has been improved, another part gas can be at the inside vortex that produces of honeycomb holes under the effect of outside powder column internal surface honeycomb holes structure, make the abundant burning of fuel, when burning the face axial displacement, along with the increase of central powder column diameter, the burning rate also can increase gradually. The invention greatly increases the burning speed and is beneficial to more fully burning the fuel.

Description

Guide vane type sleeve type grain structure with honeycomb holes

Technical Field

The invention relates to the field of solid rocket engines, in particular to a guide vane type sleeve type grain structure with honeycomb holes.

Background

Modern war is largely the amount of air strength, and air-to-air missiles are the main weapons for capturing air war victory. An air-to-air missile is a missile that is launched from the air and attacks an air target. The attack target can be carried and launched by fighters, attackers, bombers, helicopters and the like, and the attack target comprises various manned airplanes, unmanned airplanes, helicopters, cruise missiles and the like. Therefore, air-to-air missiles need to have the capability of rapid acceleration and high-speed flight.

The solid rocket engine is characterized in that all solid propellants are filled in a combustion chamber, a supply system is not provided, and a propulsion system is a guided missile subsystem which provides power for guided missile flight and obtains required flight speed and range of the guided missile. With the increasing energy of solid propellant, the wider adjustable range of burning speed, the more advanced charging process and the application of a thrust vector device, the solid rocket engine as a propelling system of an air-to-air missile shows more and more superiority compared with a liquid rocket engine.

The solid propellant is placed in the combustion chamber in the form of one or more cartridges, called grains. The working time, combustion chamber pressure and thrust of the engine are all related to the geometry and dimensions of the charge, which also affect the structural integrity of the charge and the mass ratio of the engine and the mass ratio of the propellant to the total mass of the engine. The burning rate of the fuel in the combustion chamber is the most important propellant property in determining the internal ballistic process. At nominal pressure, it should be sufficient to achieve the performance required of the engine installation, for example, in some cases, a solid rocket engine may require a short period of high thrust and be subjected to a large overload. At this time, according to the strength requirement, it is not allowed to use several powder columns for increasing combustion surface, and the acceptable solution is to use wall-attached powder charge mode, and under the condition of limited combustion surface, it must use high combustion speed to ensure the required gas production quantity, so that the only reliable method for raising combustion speed is to improve the structure of powder column, at the same time make the fuel burn more fully to obtain greater energy and thrust.

Disclosure of Invention

The technical problem to be solved by the invention is to provide a guide vane type sleeve type grain structure with honeycomb holes, compared with the prior art, the scheme has the advantages that on the basis of the geometric shape of the traditional sleeve type grain, a plurality of circulating honeycomb hole units are arranged on the inner surface of an outer grain, a series of guide vane structures are uniformly arranged on the outer surface of a central grain, meanwhile, the diameter of the central grain is increased along with the increase of the axial length, the grain structure enables a part of gas to generate vortex due to the honeycomb hole structures which are circularly distributed on the inner surface of the outer grain when high-temperature gas flows through, so that the high-temperature gas is fully combusted, the other part of high-temperature gas continuously flows forwards along the central grain, and the vortex is generated due to the series of guide vane structures which are uniformly distributed on the outer surface of the central grain in the flowing process, and the diameter of the central grain is increased along with the increase of the axial length, the burning rate of the high-temperature fuel gas is improved to a certain extent.

Technical scheme

The invention aims to provide a guide vane type sleeve type grain structure with honeycomb holes.

The technical scheme of the invention is as follows:

the utility model provides a take guide vane formula sleeve pipe type grain structure of honeycomb holes which characterized in that: the honeycomb hole structure is uniformly distributed on the annular explosive column on the outer side of the sleeve type explosive column, the structure is a circulating structure, the minimum circulating unit is composed of three adjacent honeycomb holes, and the circulating structure can be obtained by firstly axially arraying the minimum circulating unit and then circumferentially rotating the obtained circulating unit. And the structure can be adjusted to adapt to various working conditions by changing the structural parameters of the honeycomb holes, such as wall thickness, hole depth, edge distance and the like. Wherein the range of the wall thickness is 10-80 mm, the range of the hole depth is 20-100 mm, and the range of the opposite edge distance is 40-120 mm.

The sleeve type grain column is characterized in that: a series of guide blade structures are uniformly distributed on the outer surface of the central grain, the guide blades are arranged on the outer surface of the central grain at equal intervals, and the included angle between the tangent line at the front edge of each guide blade and the tangent line at the rear edge of each guide blade, namely the torsion angle range of each guide blade is 15-45 degrees. The diameter of the central grain can be slowly increased along with the increase of the axial length, and the central grain is in a round table shape and can play a role in accelerating gas when the gas flows through.

The invention has the following beneficial effects:

compared with the common sleeve type grain of the existing solid rocket engine, the invention has the advantages that: the honeycomb hole structure is uniformly distributed on the inner surface of the outer circular grain, high-temperature gas can form vortex in the honeycomb holes when flowing through, and a backflow area can be formed to ensure that the propellant is fully combusted, so that higher energy and thrust are obtained. And evenly arrange the guide vane structure at central grain surface, the gas can produce the whirl along axial guide vane structure when flowing, the resistance that the gas gos forward has been weakened, make the torrent viscosity and the temperature gradient on medicine column surface bigger, and then improved the grain surface heat flux density, the convection heat transfer on medicine column surface has been strengthened, the propellant burning rate has been showing and has been improved, the diameter of central grain increases along with axial length's increase simultaneously, when the axial displacement of combustion face promptly, along with the increase of central grain diameter, the burning rate also can increase gradually. The invention greatly increases the burning speed, is beneficial to more fully burning the fuel, obtains higher energy and thrust and obtains more excellent inner ballistic performance.

Drawings

FIG. 1: guide vane type sleeve type grain structure overall structure schematic diagram with honeycomb holes

FIG. 2: guide vane type sleeve type explosive column structure top view with honeycomb holes

FIG. 3: guide vane type sleeve type grain structure cross-sectional view with honeycomb holes

FIG. 4: guide vane type casing type grain structure honeycomb hole cross-sectional view with honeycomb holes

In the figure: 1-outer circular grain, 2-honeycomb holes, 3-guide blades, 4-central grain

Detailed Description

The invention will now be further described with reference to the accompanying drawings in which:

fig. 1 is a schematic view of the overall structure of a guide vane type sleeve type grain structure with honeycomb holes, fig. 2 is a top view along the axial direction of the grain, from which the layout of the grain structure can be seen, and fig. 3 and 4 are a cross-sectional view of the guide vane type sleeve type grain structure with honeycomb holes and a cross-sectional view of the honeycomb holes, respectively, for determining the arrangement mode and relative position of the honeycomb holes and guide vanes.

High temperature gas in the combustion chamber flows along the axial after the ignition, and when evenly arranging honeycomb hole structure 2 on the internal surface of ring grain 1, high temperature gas can form the vortex in honeycomb hole inside, forms the backward flow district and makes propellant fully burn to obtain bigger energy and thrust. Meanwhile, when the high-temperature gas evenly arranges the guide vane structure 3 on the outer surface of the central grain 4, the gas can generate rotational flow, weaken the resistance of the gas to advance, make the turbulent viscosity and the temperature gradient on the surface of the grain bigger, and then improve the surface heat flux density of the grain, strengthen the convection heat transfer on the surface of the grain, and along with the increase of the diameter of the central grain, the burning speed can also be gradually increased, thereby the burning speed of the propellant is obviously improved, the propellant is favorable for the full combustion of the propellant, the solid rocket engine obtains bigger energy and thrust, and more superior inner ballistic performance is obtained.

Claims

1. The utility model provides a take guide vane formula sleeve pipe type grain structure of honeycomb holes, includes honeycomb hole structure's size and arrangement on the outside ring grain internal surface, guide vane structure's size and arrangement on the central cylinder surface.

2. The guide vane type sleeve type grain column structure with the honeycomb holes as claimed in claim 1, wherein: evenly distributed has honeycomb hole structure on the outside ring grain of sleeve type grain, this structure is a loop construction, minimum circulation unit then comprises the three adjacent honeycomb holes of arranging, can obtain this loop construction along circumference rotation with this minimum circulation unit along axial array earlier with the circulation unit that obtains again, and the accessible changes honeycomb holes's wall thickness, the hole depth, adjust this structure in order to adapt to various operating modes to structure parameters such as margin, wherein the size range of wall thickness is 10 ~ 80mm, the size range of hole depth is 20 ~ 100mm, the size range to the margin is 40 ~ 120 mm.

3. The guide vane type sleeve type grain column structure with the honeycomb holes as claimed in claim 1, wherein: a series of guide blade structures are uniformly distributed on the outer surface of a central grain of the sleeve-type grain, the guide blades are arranged on the outer surface of the central grain at equal intervals, and the included angle between the tangent line at the front edge of each guide blade and the tangent line at the rear edge of each guide blade is 15-45 degrees, namely the torsion angle range of each guide blade is 15 degrees-45 degrees.

4. The guide vane type sleeve type grain column structure with the honeycomb holes as claimed in claim 1, wherein: the diameter of the central grain can be slowly increased along with the increase of the axial length, and the central grain is in a round table shape, so that the burning speed of the propellant is obviously improved.