Propulsion enhancement arrangement for rocket
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F42B-015/36
F42B-015/10
출원번호
US-0351127
(2003-01-27)
발명자
/ 주소
Shi, Zhong-Wei
대리인 / 주소
Chan Raymond y.
인용정보
피인용 횟수 :
1인용 특허 :
5
초록▼
A rocket includes a front warhead, a rear propellant actuator, and a propulsion enhancement arrangement. The propulsion enhancement arrangement includes a storage chamber positioned between the warhead and the propellant actuator for storing a predetermined amount of explosive materials to provide p
A rocket includes a front warhead, a rear propellant actuator, and a propulsion enhancement arrangement. The propulsion enhancement arrangement includes a storage chamber positioned between the warhead and the propellant actuator for storing a predetermined amount of explosive materials to provide propelling impulse upon controlled explosion thereof, and a time-sensitive trigger device operatively communicated with the storage chamber, wherein the time sensitive trigger device includes a timing device and an ignition trigger operatively communicated with each other such that the ignition trigger is arranged to ignite the explosive materials stored inside the storage chamber at a particular predetermined time to generate a propelling impulse to further accelerate and propel the warhead to hit the a targeted object.
대표청구항▼
1. A rocket, comprising:a front warhead;a rear propellant actuator for generating propelling force to propel said warhead in a predetermined orientation and at a predetermined speed; anda propulsion enhancement arrangement comprising a propulsion impulse generator operatively mounted between said fr
1. A rocket, comprising:a front warhead;a rear propellant actuator for generating propelling force to propel said warhead in a predetermined orientation and at a predetermined speed; anda propulsion enhancement arrangement comprising a propulsion impulse generator operatively mounted between said front warhead and said rear propellant actuator, wherein a predetermined set of parameters is input into said propulsion impulse generator to control a timing and an elevation in air of an explosion that generates a propelling impulse, wherein said propulsion impulse generator comprises:a storage chamber positioned between said front warhead and said rear propellant actuator;a predetermined amount of explosive material selected from a group consisting of trinitrotoluene which is stored in said storage chamber and enclosed by a foam material to retain a spherical shape in said storage chamber to provide propelling impulse upon controlled explosion thereof, wherein said predetermined amount of explosive material is arranged for propelling said front warhead to a predetermined position; anda time-sensitive trigger operatively communicated with said storage chamber, wherein said time sensitive trigger device comprises a timing device and an ignition trigger operatively communicated with each other in order to ignite said explosive material stored in said storage chamber at a predetermined time pre-set to said timing device, wherein when said rocket reaches said elevation in air according to said predetermined set of parameters inputted, said time-sensitive trigger triggers said explosion of said explosive material stored in said storage chamber, wherein said explosion generates said propelling impulse which further propels said front warhead to said predetermined position at a predetermined velocity and after said explosion, said rear propellant actuator and said propelling impulse generator are separated from said front warhead. 2. The rocket, as recited in claim 1, wherein said time-sensitive trigger is mounted inside said storage chamber within said explosive material. 3. The rocket, as recited in claim 2, further comprising a set of stabilizing fins extended from said warhead to balance aerodynamic forces acting on said warhead. 4. The rocket, as recited in claim 3, wherein said explosive material has a volume of 606 cm 2 , a diameter of 5.83 cm, and a density of 1.65 g/ cm 2 . 5. The rocket, as recited in claim 2, wherein said explosive material has a volume of 606 cm 2 , a diameter of 5.83 cm, and a density of 1.65 g/ cm 2 . 6. The rocket, as recited in claim 1, further comprising a set of stabilizing fins extended from said warhead to balance aerodynamic forces acting on said warhead. 7. The rocket, as recited in claim 6, wherein said explosive material has a volume of 606 cm 2 , a diameter of 5.83 cm, and a density of 1.65 g/ cm 2 . 8. The rocket, as recited in claim 1, wherein said explosive material has a volume of 606 cm 2 , a diameter of 5.83 cm, and a density of 1.65 g/ cm 2 . 9. A propulsion enhancement arrangement for a rocket which comprises a front warhead and a rear propellant actuator for generating propelling force to propel the warhead in a predetermined orientation and at a predetermined speed, wherein said propulsion enhancement arrangement comprises:a propulsion impulse generator for operatively mounting between the front warhead and the rear propellant actuator, wherein a predetermined set of parameters is input into said propulsion impulse generator to control a timing and an elevation in air of an explosion that generates a propelling impulse, wherein said propulsion impulse generator comprises:a storage chamber for positioning between the front warhead and the rear propellant actuator;a predetermined amount of explosive material selected from a group consisting of trinitrotoluene which is stored in said storage chamber and enclosed by a foam material to retain a spherical shape in said storage chamber to provide propelling impulse upon controlled explosion thereof, wherein said predetermined amount of explosive material is arranged for propelling the front warhead to a predetermined position; anda time-sensitive trigger operatively communicated with said storage chamber, wherein said time sensitive trigger device comprises a timing device and an ignition trigger operatively communicated with each other in order to ignite said explosive material stored in said storage chamber at a predetermined time pre-set to said timing device, wherein said time-sensitive trigger triggers said explosion of said explosive material stored in said storage chamber when the rocket reaches said elevation in air according to said predetermined set of parameters inputted, wherein said explosion generates said propelling impulse for propelling the front warhead to said predetermined position at a predetermined velocity while the rear propellant actuator and said propelling impulse generator are separated from the front warhead after said explosion. 10. The rocket, as recited in claim 9, wherein said time-sensitive trigger is mounted inside said storage chamber within said explosive material. 11. The rocket, as recited in claim 10, wherein said explosive material has a volume of 606 cm 2 , a diameter of 5.83 cm, and a density of 1.65 g/ cm 2 . 12. The rocket, as recited in claim 9, wherein said explosive material has a volume of 606 cm 2 , a diameter of 5.83 cm, and a density of 1.65 g/ cm 2 .
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이 특허에 인용된 특허 (5)
Kaiserman, Michael J.; Rodack, Michael T.; Schneider, Arthur J.; Spate, Wayne V.; Weesner, Jennifer B.; Winetrobe, Stanton L., Modular missile and method of assembly.
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