KR101986652B1 - Soiid rocket motor steel case for space launch vehicles - Google Patents

Abstract

The present invention relates to a metal combustion tube for a solid propellant for a space launch vehicle, and is equipped with a fastening part (200) for connecting to a projectile component on the outer circumferential surface of a spherical metal combustion tube (110) A plurality of spaced apart fastening brackets 140, 150 are included.
The present invention has the advantage of lowering the structural ratio of the solid propellant metal combustion tube and increasing the structural stability when generating pressure in the combustion tube.

Description

TECHNICAL FIELD [0001] The present invention relates to a metal combustion pipe for a solid propellant for a space launch vehicle. BACKGROUND OF THE INVENTION [0002]

The present invention relates to a metal combustion tube for a solid propellant engine for a space launch vehicle, and more particularly, to a metal combustion tube for a solid propellant engine for a space launch vehicle capable of reducing a structural ratio and increasing structural stability when a pressure in a combustion tube is generated.

The space launch vehicle is a rocket for launching the upper part of the projectile outside the atmosphere for satellite launch, lunar exploration and so on.

In the case of space launch vehicles, high propulsion performance and low structural cost (structural weight of the propulsion unit) are required to fly over 100 km of space.

Currently, the space launch vehicle under development in Korea is a multi-stage launch vehicle with two or four stages and consists of a main engine using liquid fuel and a kick motor using solid fuel. The solid propellant fills the combustion tube with a solid propellant and burns the solid propellant to obtain the propelling power by the combustion gas coming out. The combustion tube should be free from deformation due to the combustion pressure (range of about 500 to 100 psia) generated when the propellant is burned and should be able to maintain its shape. The combustion tube of a solid propellant for space launch vehicle is made of composite material or titanium material to ensure weight and structural stability.

Composite combustion tubes can withstand large pressures compared to combustion tube thicknesses, but metal bosses are needed for connection to other structures such as igniter nozzles. Titanium combustion tubes have high strength and low density, which is effective in improving structural stability and lowering the structural ratio.

FIG. 1 shows an example of a solid propulsion engine (STAR series) for a space launch vehicle, and FIG. 2 shows a conceptual view of assembling the solid propulsion engine and the upper and lower structures.

The solid propellant carries loads such as satellites, lunar probes, and lunar orbiters that are ready to launch into space. Therefore, the combustion tube of the solid propellant has a fastening portion that is necessary for connection to the upper payload and lower projectile, which are the upper and lower structures, which increases the weight of the combustion tube.

As shown in FIG. 1, the solid propellant 1 makes the tightening ring 7 in the cylinder 5 of the combustion tube 3 and, as shown in FIG. 2, The upper payload 10 is connected to the upper part of the engine 1 and the lower spin table (or adapter) 20 is connected to the lower part thereof.

However, the structure ratio of the solid propellant 1 is increased due to the fastening ring 7 circumferentially surrounding the cylinder 5 of the combustion tube 3. It is most effective to apply a spherical combustion tube to reduce the load acting on the combustion tube 3 and the weight of the combustion tube 3 when the combustion pressure generated during combustion of the propellant is the same.

In the case of a cylindrical combustion tube, the thickness of the discontinuity portion (dome-cylindrical connection portion) must be thicker than the dome and the cylindrical portion, while in the case of a spherical combustor tube, there is no such discontinuity.

However, when the spherical combustion tube is used, the weight of the combustion tube is greatly changed according to the fastening ring 7, so there is a problem that the design change of fastening with the upper payload 10 and the lower spin table 20 is restricted.

Patent Document 1: Korean Patent No. 1735351 (Registered on May 1, 2017)

It is an object of the present invention to provide a metal combustion tube of a solid propellant engine for a space launch vehicle of a design which lowers a structural ratio of a solid propellant metal combustion tube and increases structural stability when a pressure in a combustion tube is generated.

According to an aspect of the present invention, there is provided a metal combustion tube for a solid propellant engine for a space launch vehicle, comprising: an outer circumferential surface of a spherical metal combustion tube forming an outer surface of the metal combustion tube; And a plurality of spaced apart fastening brackets for mounting the coupled fastening portions.

Wherein the saddle-shaped metal combustion tube body is formed in a shape having a cylinder portion connecting cylinders between the dome portions on both sides and the dome portions on both sides thereof, the rear surface of which is in close contact with the outer circumferential surface of the metal combustion tube body, .

The fastening bracket is formed with a fastening hole for bolt fastening a state in which a part of the fastening part is seated in the concave seating groove part.

The fastening bracket is formed in such a shape that the cross-sectional area gradually decreases from the rear surface toward the front surface.

The fastening portion includes a first fastening ring fastened by a bolt in a state of being seated on the front surface of the fastening bracket and a second fastening ring which is positioned in parallel with the first fastening ring and is fastened with bolts to a projectile component for connection with the metal combustion tube. And a plurality of connecting portions connecting the first and second fastening rings at a predetermined interval.

The plurality of spaced apart fastening brackets are circular, and the plurality of spaced apart fastening brackets are provided on both sides of the metal combustion tube in both the longitudinal direction and the transverse direction with respect to the cylinder.

A metal combustion tube for a solid propellant for a space launch vehicle, comprising: a plurality of spaced apart fastening brackets for mounting a fastening portion connected to a projectile component on an outer circumferential surface of a spherical metal combustion tube forming an outer appearance of the metal combustion tube; And a variable means provided on an outer circumferential surface of the spherical combustion tube so as to replace a fastening bracket having a shape and a size corresponding to the shape and size of the fastening portion.

The variable means may be a moving rail provided on the outer circumferential surface of the spherical combustion tube in a circular shape.

The fastening bracket may include a bracket to which the fastening portion is mounted, and a moving body provided on a bottom surface of the bracket to allow the bracket to move along the moving rail.

The moving rails are formed with rail grooves on both sides, and the moving body can be moved along the moving rails with ball bearings corresponding to the rail grooves on both sides of the moving rails.

The moving rail may be a circular moving rail whose one side is opened to replace the fastening bracket.

The moving rail may be longitudinally or transversely disposed on an outer circumferential surface of the metal combustion tube.

The bracket may be formed in a recessed groove shape having a concave surface.

The fastening portion includes a first fastening ring fastened to the bracket by a bolt in a state of being seated on the front surface of the bracket, and a second fastening ring located parallel to the first fastening ring and bolted to a projectile component for connection with the metal combustion tube A second fastening ring, and a plurality of connecting portions connecting the first fastening ring and the second fastening ring at regular intervals.

The spherical metal combustion tube may have a shape having a cylinder portion connecting cylinders between the both side dome portions and the both side dome portions.

A plurality of fastening brackets spaced apart from the outer circumferential surface of the spherical metal combustion tube may be included for assembly with front and rear or upper and lower launch vehicle components.

The plurality of fastening brackets are respectively formed in a circular shape on the front and rear and / or the upper and lower outer peripheral surfaces of the spherical metal combustion tube, and fastening parts for connecting to the projectile components can be mounted on the plurality of circular fastening brackets.

The fastening bracket may be movably coupled to a circular moving rail having one side thereof provided on the outer peripheral surface of the combustion tube, and may be displaceable and replaceable.

The spherical metal combustion tube may be made of titanium.

The present invention includes a plurality of spaced apart fastening brackets for mounting fasteners for assembly with projectile components on the front, rear, or top and bottom peripheral surfaces of the combustion tubes. A plurality of spaced apart fastening brackets do not constrain the combustion tube, so the discontinuous stress is not large, and the weight is reduced, so that the weight can be reduced.

Accordingly, the present invention has the effect of lowering the structural ratio of the solid combustion engine metal combustion tube and increasing the structural stability when generating pressure in the combustion tube.

Further, according to the present invention, a fastening bracket having lateral and longitudinal moving rails on the outer circumferential surface of the combustion tube and moving along the moving rail is designed so that the fastening bracket can be changed in position.

Therefore, according to the present invention, it is possible to replace the fastening bracket according to the shape or size of the fastening part.

Figure 1 shows an example of a solid propulsion engine for a space launch vehicle (STAR series)
FIG. 2 is a conceptual diagram of assembling solid propellant and upper and lower projectile components. FIG.
3 is a schematic view of a solid propellant metal combustion tube for a space launch vehicle.
FIG. 4 is a view showing a metal combustion tube of a solid propellant for a space launch vehicle according to an embodiment of the present invention. FIG.
FIG. 5 is a view showing a structure in which a fastening part is mounted on a metal combustion tube of a solid propellant for a space launch vehicle according to an embodiment of the present invention; FIG.
Figs. 6 and 7 are graphs showing results of analysis of the structure of a metal combustion tube of a solid propellant for a space launch vehicle according to an embodiment of the present invention
8 is a schematic view of a metal combustion tube of a solid propellant for a space launch vehicle according to another embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

FIG. 3 is a block diagram of a solid propellant metal combustion tube for a space launch vehicle, and FIG. 4 is a diagram illustrating a metal combustion tube of a solid propellant for a space launch vehicle according to an embodiment of the present invention.

The metal combustion tube (hereinafter referred to as 'metal combustion tube') of the solid propellant for space vehicles of the present invention removes the front fastening ring and the rear fastening ring from the solid propellant metal combustion tube for space launch vehicle shown in FIG. 3 and employs a fastening bracket It is.

The metal combustion tube 100 shown in FIG. 3 includes an upper payload 10 and a lower spin table (or an adapter) 120. The upper payload 10 and the lower spin table 130 are attached to the front tightening ring 120 and the rear tightening ring 130, (20) can be connected by fastening bolts (125, 135), respectively.

The metal combustion tube 100 shown in FIG. 3 has a shape in which the front fastening ring 120 and the rear fastening ring 130 are closely attached to the combustion tube 110 with a predetermined area.

The present invention employs the shape of the metal combustion tube of FIG. 4 to further reduce the structural ratio of the combustion tube compared to the front and rear fastening ring structures of FIG.

As shown in FIG. 4, the metal combustion tube 100 has a metal combustion tube 110 whose outer shape is nearly spherical.

The metal combustion tube 110 closest to the sphere includes a cylinder 113 connecting between the two side dome portions 111 and 112 and the two side dome portions 111 and 112 in a cylindrical shape. The two side dome portions 111 and 112 and the cylinder portion 113 are integrally formed without a discontinuous portion at the time of designing, so that they are advantageous in terms of the structure ratio.

The dome portions 111 and 112 have a high discontinuous stress and a high hemispherical shape. The hemispherical dome widens its internal volume, reduces weight, and acts as a uniform distribution of internal pressure, resulting in less deformation. That is, the hemispherical dome is structurally safe and has a high weight saving effect.

The metal combustion tube 110 has a sufficient strength and rigidity to withstand the high pressure and high temperature generated during the combustion of the propellant, and is made of a metal material having a weight reduction effect. Since the weight of the metal combustion tube 110 is an important factor directly related to the performance, the weight should be reduced as much as possible.

For example, the metal combustion tube 110 is made of a titanium material. The titanium material has high strength and low density, which is effective in improving the structural stability of the combustion tube and lowering the structural ratio.

A plurality of spaced apart fastening brackets 140 and 150 are mounted on the outer circumferential surface of the metal combustion tube 110 to mount the fastening part 200 connected to the projectile components.

The rear surface of the fastening brackets 140 and 150 is in close contact with the outer circumferential surface of the metal combustion tube 110 and the front surface of the fastening brackets 140 and 150 is curved inward toward the inside. The concave curved groove portion serves as a seating groove portion 141 on which the fastening brackets 140 and 150 and the fastening portion 200 for fastening are seated and is for stable mounting with increased adhesion with the fastening portion 200.

The fastening brackets 140 and 150 are formed with a fastening hole 142 for bolt fastening a part of the fastening part 200 in the seating groove part 141 recessed toward the inside. The plurality of fastening brackets 140 and 150 are formed into a circular shape and the fastening portions 200 are mounted on the plurality of fastening brackets 140 and 150 spaced from each other.

The fastening brackets 140 and 150 are formed in such a shape that the sectional area gradually decreases from the rear surface toward the front surface. The shape of the fastening bracket, whose sectional area gradually decreases from the rear to the front, is for weight reduction.

The plurality of fastening brackets 140 and 150 spaced in a circular shape may be respectively provided to be symmetrical to both the longitudinal direction and the transverse direction of the metal combustion tube 110 with respect to the cylinder portion 113. That is, the plurality of fastening brackets 140 and 150 may be circularly formed on the front and rear sides of the metal combustion tube 110 or on the upper and lower peripheral surfaces, respectively.

The fastening part 200 is mounted on a place where a plurality of spaced apart fastening brackets 140 and 150 are circular.

The fastening part 200 can be mounted on the front and rear sides or the upper and lower outer circumferential surfaces of the metal combustion tube 110 by fastening brackets 140 and 150.

For example, the fastening part 200 can be fastened to the fastening brackets 140 and 150 spaced symmetrically around the front and rear sides of the metal combustion tube 110, respectively.

The fastening brackets 140 and 150 may be fastened to the outer circumferential surface of the metal combustion tube 110 by bolts or by welding.

The fastening brackets 140 and 150 may be made of the same material as the metal combustion tube 110 to withstand high temperatures and high pressures.

The detailed configuration of the fastening part 200 will be described with reference to Fig. 5 below.

FIG. 5 is a view showing a structure in which a fastening part is mounted on a metal combustion tube of a solid propellant for a space launch vehicle according to an embodiment of the present invention.

5, the fastening part 200 includes a first fastening ring 210, a second fastening ring 240, and a connecting part 230. As shown in FIG.

Specifically, the fastening part 200 includes a first fastening ring 210 fastened to the fastening brackets 140 and 150 by bolts in a state of being seated on the front surfaces of the fastening brackets 140 and 150, A second fastening ring 240 that is bolted to the projectile component for connection to the metal combustion tube 110 and a second fastening ring 240 that fastens the first fastening ring 210 and the second fastening ring 240 to a plurality of And may include a connecting portion 230.

The first fastening ring 210 and the second fastening ring 240 are circular and may have different sizes. For example, the size of the first fastening ring 210 coupled with the fastening brackets 140 and 150 is relatively larger than that of the second fastening ring 240 fastened to the projectile component. However, the size of the first fastening ring 210 may be smaller than or equal to the size of the second fastening ring 240, depending on the design conditions of the combustion tube 100 applied to the space launch vehicle and the space launch vehicle.

The connection portion 230 can be formed in a variety of shapes such as a plurality of straight shapes, a plurality of X-shaped shirred shapes, and a shape in which a plurality of pieces are connected in a staggered manner between the first and second fastening rings 210 and 240 .

The fastening part 200 includes a first fastening ring 210, a second fastening ring 240, and a connecting part 230 connecting the first fastening ring 210 and the second fastening ring 240 in this embodiment. Is similar to the truncated cone shape. The coupling part 200 may be made of the same metal material as that of the combustion tube 110, that is, titanium material for light weight and structural stability, and is formed in a frame structure using a ring, pipe, or the like for weight reduction.

The first fastening ring 210 of the fastening part 200 has a diameter corresponding to the front seating groove 141 of the fastening bracket 140 and the diameter of the second fastening ring 240 and the connecting part 230 And is made to correspond to the diameter of the first fastening ring 210 to be lightweight.

The launcher component may be an upper payload 10 and a lower spin table (or adapter).

Hereinafter, the process of assembling the fastening part to the spherical combustion tube will be described with reference to FIG.

The first fastening ring 210 of the fastening part 200 is seated against the seating groove 141 of the front fastening bracket 140 of the spherical combustion tube 110. Since the seating groove portion 141 is formed in a predetermined curved shape toward the inside, the first locking ring 210 is formed to surround the first locking ring 210 from the outside, and the structural stability is high. In this state, the bolt passes through the first fastening ring 210 and is fastened to the fastening hole 142 of the front fastening bracket 140. The bolts are fastened at the positions corresponding to the front fastening brackets 140 at the first fastening ring 210 to increase the fastening force.

The above process is also applied to the process of assembling the fastening part 200 to the rear fastening bracket 150 of the spherical combustion tube 110.

When the fastening portions 200 are assembled to the front and rear sides of the spherical combustion tube 110 by the above process, the shape as shown in FIG. 5 is obtained.

In this state, the fastening part 200 assembled to the front fastening bracket 140 is connected to the upper payload 10 and the fastening part 200 assembled to the rear fastening bracket 150 is connected to the lower spin table 20 .

6 and 7 show results of analysis of the structure of a metal combustion tube of a solid propellant for a space launch vehicle according to an embodiment of the present invention.

FIG. 6 is a structural analysis result of a combustion tube using the fastening ring of FIG. 3, and FIG. 7 is a structural analysis result of a combustion tube using the fastening bracket of FIG.

The metal combustion tube (FIG. 4) to which the fastening bracket of the present invention was applied had a weight reduction of about 14% compared to the metal combustion tube (FIG. 3) to which the fastening ring was applied. This means that in the case of a solid propellant of the same weight, a fuel (propellant) corresponding to 14% of the weight of the combustion tube can be additionally charged.

The weight saving contributes to the weight reduction of the combustion tube.

6 and FIG. 7, which are structural analyzes assuming an internal pressure of 650 psia, the metal ring of the fastening ring shown in FIG. 6 has a stress of around 800 MPa around the fastening ring, The combustion tube has a stress around the fastening bracket of 70 ~ 700 MPa

The combustion tube to which the fastening ring shown in Fig. 3 is applied is an essential design element because the fastening ring serves to connect the upper and lower projectile components (the upper payload 10 and the lower spin table (or adapter) 20). The tightening ring designed in the circumferential direction on the dome portion of the spherical combustion tube has a large difference in the weight of the combustion tube depending on the position thereof. In addition, since the front and rear fastening rings 120 and 130 constrain the combustion tube 110 in the circumferential direction, stress around the fastening rings 120 and 130 around the front and rear rings is greatly increased when internal pressure is generated due to combustion of the propellant.

On the other hand, in the combustion tube 100 using the fastening brackets 140 and 150 shown in FIG. 4, the structure ratio is reduced and the fastening brackets 140 and 150 are not constrained to the combustion tube 110 due to the disposition when the pressure in the combustion tube 100 is generated So that the structural stability can be increased.

Accordingly, it is confirmed that the metal combustion tube 100 to which the fastening brackets 140 and 150 of the embodiment of the present invention is applied is advantageous in terms of structure.

In another embodiment, the fastening bracket may be configured to be variable in position and to be replaced with a fastening bracket of a shape and size corresponding to the shape and size of the fastening portion.

FIG. 8 is a view illustrating a structure of a metal combustion tube of a solid propellant for a space launch vehicle according to another embodiment of the present invention.

8, the metal combustion tube 100 of the solid propellant engine for space launch vehicle according to another embodiment can change the position of the fastening bracket 170 and change the shape and size And a variable means provided on the outer circumferential surface of the spherical combustion tube 110 so as to be replaceable with the fastening bracket 170 of the combustion tube 110.

The variable means includes a movable rail 160 provided on the outer circumferential surface of the spherical combustion tube 110 in a circular shape. The movable rail 160 may have rail grooves 161 formed on both sides thereof. The movable rail 160 having the rail grooves 161 formed on both sides can move in a state in which the ball bearings 173 of the moving body 171 are hooked on both the side rail grooves 161 so that the ball grooves 173 Can be prevented from being released.

The rail groove 161 may have various shapes as long as the ball bearing 173 moving along the rail groove 161 is not detached.

The movable rail 160 may be a movable rail 160 having a circular shape and open at one side so as to replace the fastening brackets 170.

The movable rail 160 having a circular shape with one side open can be provided in the longitudinal or transverse direction on the outer circumferential surface of the metal combustion tube 110.

For example, the movable rail 160 may be a pair of symmetrically arranged front and rear outer circumferential surfaces of the metal combustion tube 110, and may have a circular shape with one side opened.

That is, the moving rail 160 is provided with a longitudinally and transversely outer peripheral surface around the cylinder portion (central axis) 113 in the combustion tube 110 so as to vary the position of the fastening bracket 170, And can be installed on the outer circumferential surface.

The movable rail 160 can be configured such that one side opened on the circular opening is opened only when the fastening brackets 170 are replaced. For example, when the closing bracket is replaced with a closing rail protruded by an elastic force at a portion opened to the moving rail 160, a circular moving rail is formed without applying an external force. When replacing the closing bracket, It can be constituted to be a circular movement rail having one side opened from the one pushing in the direction of insertion into the rail.

In this case, any deviation of the fastening bracket 170 movably coupled to the movable rail 160 can be prevented.

The bottom surface of the movable rail 160 can be integrally fixed to the outer circumferential surface of the combustion tube 110 by welding or bolting.

A fastening bracket 170 is movably coupled to the movable rail 160.

The fastening bracket 170 includes a bracket 175 to which the fastening portion 200 is mounted and a moving body 171 provided on the bottom surface of the bracket 175 to allow the bracket 175 to move along the moving rail 160 can do.

That is, the fastening bracket 170 may include a moving body 171 moving along the moving rail 160 and a bracket 175. The fastening brackets 170 can be replaced according to the shape or size of the fastening portions.

The moving body 171 can be smoothly moved along the movable rail 160 by providing the ball bearings 173 corresponding to the rail grooves 161 on both sides of the movable rail 160. The movable body 171 may have one or more bodies crossing the upper surface of the movable rail 160 and may have a ball bearing spaced apart from the bottom of the body.

The bracket 175 may be fixed to the upper surface of the body constituting the moving body 171. The bracket 175 may be integrally formed with the moving body, or may be separately manufactured and fixed to the moving body with a bolt.

The brackets 175 are formed in the shape of a recessed depressed surface with the front surface facing inward so as to ensure structural stability when assembled with the fastening part 200. The bracket 175 may be formed in a shape such that its cross-sectional area becomes smaller toward the front side in order to reduce the weight.

In other embodiments, the fastening portion 200 may be fastened to the bracket by bolts in a state where the first fastening ring 210 is seated in the front seat recess 176 of the bracket 175.

The bolt passes through the first fastening ring 210 and is fastened to the fastening hole 177 formed in the bracket 175. The bolts are fastened at the positions corresponding to the brackets 175 in the first fastening ring 210 to secure fastening force.

Hereinafter, a process of assembling the fastening portion to the fastening bracket shown in FIG. 8 will be described.

The fastening brackets 170 are positionally variable since the ball bearings 173 of the moving body 171 are positioned in the rail grooves 161 of the moving rail 160 and are movable along the moving rail 160. Also, the fastening bracket 170 can be replaced according to the shape or size of the fastening part 200.

The first fastening ring 210 of the fastening part 200 is seated against the seating recess 176 of the bracket 175 by locating the fastening bracket 170 at the fixed distance on the moving rail 160. Since the seating groove portion 176 is a recessed shape, the seating groove portion 176 has a shape that wraps around the first fastening ring 210, so that the structural stability is high. In this state, the bolt passes through the first fastening ring 210 and is fastened to the fastening hole 177 of the bracket 175. The bolts are fastened at the positions corresponding to the brackets 175 in the first fastening ring 210 to increase the fastening force.

The first fastening ring 210 of the fastening part 200 is fastened to the fastening bracket 170 movably coupled to the front and rear moving rails 160 of the spherical combustion tube 110 by the above- It is possible to rotate the coupling part 200 with respect to the spherical combustion tube 110 in a shape as shown in FIG.

In this state, the fastening part 200 assembled to the fastening bracket 170 is connected to the upper and lower projectile components. Since the fastening part 200 is rotatable with respect to the combustion tube 110, the fastening part 200 ) Can be varied.

Meanwhile, in the movable rail applying structure of another embodiment, the movable rail has a rail groove formed on both sides thereof, but a rail groove may be formed on the upper side. In this case, the rail groove has a circular cross section and the ball bearing of the moving body moved along the rail groove can adopt a spherical shape. In addition, various shapes and positions of the movable rail can be employed as long as the movable rail can be moved along the rail groove while preventing the ball bearing from being released.

As described above, the present invention is configured to include a plurality of fastening brackets spaced apart from the outer circumferential surface of the spherical metal combustion tube for front and rear and upper and lower portions for assembly with projectile components. Multiple spaced brackets improve the structural stability of the combustion tube by reducing the weight and reducing the stress around the bracket.

The reduction of the stress around the fastening bracket minimizes the difference in strain rate between the combustion tube and the combustion tube at high pressure and high temperature in the combustion of the propellant, thereby improving the structural stability of the combustion tube and enhancing the reliability of the solid propellant.

The plurality of fastening brackets are respectively formed in a circular shape on the front and rear and / or the upper and lower outer peripheral surfaces of the spherical metal combustion tube, and fasteners for connecting to the projectile components are mounted on a plurality of circular fastening brackets.

The plurality of fastening brackets are spaced at regular intervals so as to have a regular number of bolts and axially symmetrically provided on the outer circumferential surface of the metal combustion tube, thereby preventing stress from concentrating at a certain position.

The fastening bracket is movably engaged with a circular moving rail on one side of which is provided on the outer circumferential surface of the combustion tube and can be selectively opened to be displaceable and replaceable.

It is easy to connect the fastening portions of various shapes and sizes to the outer circumferential surface of the combustion tube by arranging the position of the fastening bracket on the outer circumferential surface of the combustion tube.

The spherical metal combustion tube is made of titanium material, and it can secure the capacity and structural stability.

In particular, the metal combustion tube shown in FIG. 4 can further include the fuel by a reduced weight by reducing the total weight of the combustion tube by 14% using spaced fastening brackets, and reduce the peripheral stress of the fastening portion.

In addition, the metal combustion tube shown in FIG. 8 can be generally used depending on the size and shape of the fastening portion.

Accordingly, the solid propellant metal combustion tube for space launch vehicle of the present invention can be applied to a space launch vehicle for entering the equipment into the atmosphere for achieving the purpose of satellite launching, lunar exploration, etc., So that the reliability of the projectile can be ensured.

Best Mode for Carrying Out the Invention The present invention has been disclosed in the best mode for the drawings and specification. Although specific terms are used herein, they are used for the purpose of describing the present invention only and are not used to limit the scope of the present invention described in the meaning of the claims or the claims. Therefore, it is to be understood that the present invention may be embodied in many other specific forms without departing from the spirit or essential characteristics thereof. Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims.

1: Solid propellant 3: Combustion pipe
5: cylinder part 7: fastening ring
10: upper payload 20: lower spin table
100: combustion tube 110: combustion tube
111, 112: dome portion 113:
120: front fastening ring 130: rear fastening ring
125: Bolt 140: Front fastening bracket
141: seat groove portion 142: fastening hole
150: rear fastening bracket
160: moving rail 161: rail groove
170: fastening bracket 171: moving body
173: Ball Bearing 175: Bracket
176: seat groove portion 177: fastening hole
200: fastening part 210: first fastening ring
230: connection part 240: second fastening ring

Claims (19)

In a metal combustion tube of a solid propellant for a space launch vehicle,
And a plurality of fastening brackets spaced apart from each other for mounting fastening portions connected to the projectile components on the outer circumferential surface of the spherical metal combustion tube forming the outer surface of the metal combustion tube,
The spherical metal combustion tube
And a cylinder portion connecting the two side dome portions and the two side dome portions in a cylindrical shape,
Wherein the fastening bracket is formed in a concave recessed groove shape in which the rear surface is in close contact with the outer circumferential surface of the metal combustion tube and the opposite surface is in the form of a concave recessed groove. delete The method according to claim 1,
Wherein the fastening bracket is formed with a fastening hole for bolt fastening a state in which a part of the fastening portion is seated in the concave seating groove portion. The method according to claim 1,
Wherein the fastening bracket is formed to have a shape in which the cross-sectional area gradually decreases from the rear surface to the front surface of the metal combustion tube. The method according to claim 1,
The fastening portion
A first fastening ring fastened by bolts in a state of being seated on the front surface of the fastening bracket;
A second fastening ring positioned parallel to the first fastening ring and bolted to a projectile component for connection with the metal combustion tube; And
A plurality of connecting portions connecting the first fastening ring and the second fastening ring at predetermined intervals;
Wherein the shape of the metal combustion tube of the solid propellant for a space launch vehicle is a shape including at least one of the first and second shapes. The method according to claim 1,
Wherein the plurality of spaced-apart fastening brackets are circular,
Wherein the plurality of spaced apart fastening brackets are provided on both sides of the metal combustion tube in the longitudinal direction or on both lateral sides of the metal combustion tube in relation to the cylinder. In a metal combustion tube of a solid propellant for a space launch vehicle,
A plurality of fastening brackets spaced apart from each other for mounting a fastening portion connected to a projectile component on an outer circumferential surface of a spherical metal combustion tube forming an outer appearance of the metal combustion tube; And
A variable means provided on an outer circumferential surface of the spherical combustion tube so as to change a position of the fastening bracket and to replace a fastening bracket having a shape and a size corresponding to the shape and size of the fastening portion;
Wherein the metal combustion tube of the solid propellant for space vehicles is characterized by comprising: The method of claim 7,
The variable means
And a movable rail provided on the outer circumferential surface of the spherical combustion tube in a circular shape. The method of claim 8,
The fastening bracket
A bracket to which the fastening portion is mounted; And
A moving body provided on a bottom surface of the bracket to allow the bracket to move along the moving rail;
Wherein the metal combustion tube of the solid propellant for space vehicles is characterized by comprising: The method of claim 9,
The moving rails are formed with rail grooves on both sides thereof,
Wherein the movable body is provided with ball bearings corresponding to the rail grooves on both sides of the movable rail and is moved along the movable rail. The method of claim 8,
The moving rail
Wherein the movable bracket is a circular moving rail having one side opened so as to replace the fastening bracket. The method of claim 11,
The moving rail
Wherein the metal combustion tube is provided on the outer circumferential surface of the metal combustion tube in a longitudinal direction or a transverse direction. The method of claim 9,
Wherein the bracket is formed in a concave recessed groove shape in a front surface of the bracket. 14. The method of claim 13,
The fastening portion
A first fastening ring fastened to the bracket by a bolt in a state of being seated on the front surface of the bracket;
A second fastening ring positioned parallel to the first fastening ring and bolted to the projectile component for connection to the metal combustion tube; And
A plurality of connecting portions connecting the first fastening ring and the second fastening ring at predetermined intervals;
Wherein the shape of the metal combustion tube of the solid propellant for a space launch vehicle is a shape including at least one of the first and second shapes. The method of claim 7,
The spherical metal combustion tube
And a cylindrical portion connecting the two side dome portions and the two side dome portions in a cylindrical shape. In a metal combustion tube of a solid propellant for a space launch vehicle,
A plurality of fastening brackets spaced apart from the outer circumferential surface of the spherical metal combustion tube for assembly with front-rear or upper and lower launch vehicle components,
The fastening bracket
And the movable combustion chamber is movably coupled to the lateral and longitudinal moving rails provided on the outer circumferential surface of the combustion tube to be displaceable and replaceable. 18. The method of claim 16,
Wherein the plurality of fastening brackets each have a circular shape on the front and rear sides or on the upper and lower peripheral surfaces of the spherical metal combustion tube,
And a fastening portion for connecting to the projectile component is mounted on the plurality of fastening brackets that form the circular shape. delete In a metal combustion tube of a solid propellant for a space launch vehicle,
A plurality of fastening brackets spaced apart from the outer circumferential surface of the spherical metal combustion tube for assembly with front-rear or upper and lower launch vehicle components,
Wherein the spherical metal combustion tube is made of a titanium material.

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