A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudi
A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the first thruster in the longitudinal direction into the radial direction. A large number of thrusters can be mounted at the side thruster module thus to generate a high thrust, and the side thruster module can be slim in the radial direction perpendicular to the longitudinal direction.
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What is claimed is: 1. A side thruster module, comprising: a cavity-type body skin extending in a longitudinal direction; a plurality of first thrusters arranged in the body skin and extending in a longitudinal direction; a plurality of second thrusters arranged to be spaced from the plurality of f
What is claimed is: 1. A side thruster module, comprising: a cavity-type body skin extending in a longitudinal direction; a plurality of first thrusters arranged in the body skin and extending in a longitudinal direction; a plurality of second thrusters arranged to be spaced from the plurality of first thrusters in the longitudinal direction of the body skin so as to be extending in a radial direction, for generating a thrust in the radial direction through a jointing groove of the body skin; and a plurality of conversion nozzles being arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the plurality of first thrusters in the longitudinal direction into the radial direction, wherein the conversion nozzles are arranged in a circumferential direction of the body skin, and in at least two rows spaced from each other in the longitudinal direction of the body skin. 2. The side thruster module of claim 1, wherein each of the first thrusters comprises: a cavity-type combustion tube; a propellant arranged in the combustion tube for generating a thrust at the time of combustion; and an igniter jointed to the combustion tube for igniting the propellant. 3. The side thruster module of claim 2, wherein the combustion tube is formed by filament-winding a composite material on an outer circumference of a cavity-type alloy steel. 4. The side thruster module of claim 3, wherein the cavity-type alloy steel is a titanium alloy, and the composite material is a carbon fiber. 5. The side thruster module of claim 2, wherein the propellant is a solid propellant, and wherein each of the first thrusters further comprises a liner attached to an inner wall of the combustion tube for jointing the solid propellant to the inner wall. 6. The side thruster module of claim 1, wherein the conversion nozzle is integrally formed at the body skin, and the conversion nozzle includes: a length portion opened in the longitudinal direction and connected to a first thruster; and a radius portion opened in the radial direction and connected to the length portion and outside. 7. The side thruster module of claim 6, wherein there is provided a plurality of said conversion nozzles, and wherein conversion nozzles which are arranged adjacent to each other in the longitudinal direction have radius portions of different lengths so that the first thrusters jointed to the conversion nozzles are stacked in the radial direction. 8. The side thruster module of claim 1, wherein the conversion nozzle is integrally formed at an inner circumference of the body skin, and further comprising a jointing portion formed between the conversion nozzle and a first thruster for jointing therebetween. 9. The side thruster module of claim 8, wherein the jointing portion includes: a male screw thread formed on one of an inner circumferential surface of an inlet of the conversion nozzle and an outer circumferential surface of an outlet of a first thruster; and a female screw thread formed on another of an inner circumferential surface of an inlet of the conversion nozzle and an outer circumferential surface of an outlet of a first thruster, and jointed to the male screw thread. 10. The side thruster module of claim 1, wherein said plurality of first thrusters and the conversion nozzles are arranged in a circumferential direction of the body skin in plural, and a weight reduction hole for reducing a weight of the body skin is formed between the adjacent conversion nozzles of the body skin. 11. The side thruster module of claim 2, further comprising a conversion nozzle closure jointed to an outlet of the conversion nozzle for sealing the conversion nozzle and a combustion tube connected to the conversion nozzle. 12. The side thruster module of claim 1, wherein each of the second thrusters comprises: a cavity-type combustion tube; a propellant arranged in the combustion tube for generating a thrust at the time of combustion; an igniter jointed to the combustion tube for igniting the propellant; and an injection nozzle jointed to an outlet of the combustion tube for outwardly injecting a thrust generated by a combustion of the propellant through the jointing groove of the body skin. 13. The side thruster module of claim 12, wherein the combustion tube is formed by filament-winding a composite material on an outer circumference of a cavity-type alloy steel. 14. The side thruster module of claim 13, wherein the cavity-type alloy steel is a titanium alloy, and the composite material is a carbon fiber. 15. The side thruster module of claim 12, wherein the propellant is a solid propellant, and each second thruster further comprises a liner attached to an inner wall of the combustion tube for jointing the solid propellant to the inner wall. 16. The side thruster module of claim 12, further comprising a jointing portion formed between an outer circumferential surface of the injection nozzle and an inner circumferential surface of the body skin that defines the jointing groove, for jointing the injection nozzle to the jointing groove. 17. The side thruster module of claim 16, wherein the jointing portion includes: a male screw thread formed on one of an outer circumferential surface of the injection nozzle and an inner circumferential surface of the body skin that defines the jointing groove; and a female screw thread formed on another of an outer circumferential surface of the injection nozzle and an inner circumferential surface of the body skin that defines the jointing groove, and jointed to the male screw thread. 18. The side thruster module of claim 12, further comprising an injection nozzle closure jointed to an outlet of the injection nozzle for sealing the combustion tube. 19. The side thruster module of claim 1, wherein said plurality of said second thrusters are arranged in a circumferential direction of the body skin in at least two rows at a spacing from each other in the longitudinal direction of the body skin, and the second thrusters of adjacent two rows are arranged in a zigzag form.
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이 특허에 인용된 특허 (5)
Bonnelie Guy (Le Bouscat FRX), Combustion chamber for a thruster with a sealed connection between an end wall and a composite tubular structure.
McGrath, David K.; Kirschner, Jr., Thomas J.; Dombrowski, Daniel C., Rocket nozzle assembly having rotatable variable thrust control cylinders, and rocket assembly comprising the same.
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