中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

15 records (took 0.013 seconds)

    Rocket motor
    2.
    发明授权
    Rocket motor 失效
    摇臂电机

    公开(公告)号：US3656304A

    公开(公告)日：1972-04-18

    申请号：US3656304D

    申请日：1966-07-19

    Applicant: THIOKOL CHEMICAL CORP

    Inventor： MCCULLOUGH EDWARD E

    IPC: F02K9/94 ,  F02K9/04

    CPC classification number: F02K9/94

    Abstract: 1. A rocket motor comprising: A MOTOR CASE HAVING A THRUST NOZZLE MOUNTED ON THE AFT END THEREOF; A PLURALITY OF OXYGEN-RICH SOLID PROPELLANT GRAINS TANDEMLY DISPOSED WITHIN SAID MOTOR CASE; A PLURALITY OF BAFFLES RESPECTIVELY DISPOSED BETWEEN ADJACENT END SURFACES OF SAID OXYGEN-RICH GRAINS, EACH OF SAID BAFFLES BEING FORMED OF A HEAT-RESISTANT MATERIAL SO THAT EACH OF SAID GRAINS CAN BE BURNED WITHOUT IGNITING THE ADJACENT ONE OF SAID GRAINS FORWARD THEREOF, AND EACH OF SAID BAFFLES BEING REMOVABLE BY GAS GENERATED BY COMBUSTION OF THE ADJACENT ONE OF SAID GRAINS FORWARD THEREOF; AT LEAST ONE OXYGEN-DEFICIENT SOLID PROPELLANT GRAIN DISPOSED WITHIN SAID MOTOR CASE BETWEEN SAID THRUST NOZZLE AND THE REARMOST OF SAID OXYGEN-RICH GRAINS, SAID OXYGEN-DEFICIENT GRAIN BEING FORMED WITH AT LEAST ONE LONGUTIDINALLY-EXTENDING PERFORATION THAT COMMUNICATES WITH SAID THRUST NOZZLE AND SAID REARMOST OXYGEN-RICH GRAIN; AND IGNITING MEANS FOR IGNITING EACH OF SAID OXYGEN-RICH GRAINS.

    Abstract translation: 1.一种火箭发动机，包括：

    Thrust vector control system
    6.
    发明授权
    Thrust vector control system 失效
    扭矩矢量控制系统

    公开(公告)号：US3698642A

    公开(公告)日：1972-10-17

    申请号：US3698642D

    申请日：1966-11-04

    Applicant: THIOKOL CHEMICAL CORP

    Inventor： MCCULLOUGH EDWARD E

    IPC: F02K9/82 ,  B63H25/46

    CPC classification number: F02K9/82

    Abstract: A thrust vector control system for a rocket motor wherein a pair of rows of injection ports are provided circumferentially of the nozzle for injection of fluid thereinto. Means for selectively varying the rate of flow of the fluid injected thereby creating a nonstructural, variable positioned throat to vary thereby the direction of the rocket motor thrust vector.

    Compact thrust nozzle for rockets
    9.
    发明授权
    Compact thrust nozzle for rockets 失效
    用于火箭的紧凑型推力喷嘴

    公开(公告)号：US3877646A

    公开(公告)日：1975-04-15

    申请号：US43146874

    申请日：1974-01-07

    Applicant: THIOKOL CHEMICAL CORP

    Inventor： MCCULLOUGH EDWARD E ,  BAMBRICK ROBERT W ,  LARAMEE RICHARD C

    IPC: F02K9/86 ,  B64C15/00

    CPC classification number: F02K9/86

    Abstract: A fixed convergent-divergent rocket nozzle has a movable throat section seated in an annular recess in the nozzle and retained therein at its forward end by a flexible bearing. The flexible bearing is constructed of alternate layers of rigid material and elastomer, stacked and bonded together, and conforming to concentric spherical surfaces, so that the throat section may be rotated about a fixed point. Actuators for moving the throat section bear upon it radially from their mounted positions in the nozzle. The throat section is greatly diminished in weight by being made of thin-walled material supported on its outside by ribs that also function as radiating fins to avoid heat buildup in the throat section. The air space surrounding the throat section is open at the downstream edge thereof to the propulsive gases of the rocket further to promote thermal equilibrium of all parts of the throat section, thereby avoiding the possibility of cracking due to differential thermal expansion of inner and outer surfaces of the throat. This air space, together with an annular space on the downstream side of the flexible bearing that is open to the combustion chamber of the rocket, also promotes a pressure balance of the throat member against the blowout load by permitting pressure on surfaces opposite those exposed to the blowout load. Hence, very little energy is required to move the throat member; and actuators therefor may be of minimal size and weight.

    Abstract translation: 固定会聚发散火箭喷嘴具有可移动的喉部，其位于喷嘴中的环形凹部中，并在其前端由柔性轴承保持在其中。 柔性轴承由刚性材料和弹性体的交替层构成，堆叠并结合在一起，并且与同心球形表面一致，使得喉部可以围绕固定点旋转。 用于移动喉部的致动器从其在喷嘴中的安装位置径向承受。 喉部通过由其外部支撑的薄壁材料制成，其重量也大大减小，其也用作散热片，以避免在喉部中产生热量。 喉部周围的空气空间在其下游边缘处开放到火箭的推进气体，进一步促进喉部的所有部分的热平衡，从而避免由于内表面和外表面的不同热膨胀而产生开裂的可能性 的喉咙 该空气空间与柔性轴承的向火箭的燃烧室开口的下游侧的环形空间一起，还通过允许与暴露于火焰的燃烧室相对的表面上的压力来促进喉部构件相对于吹出负载的压力平衡 井喷负荷。 因此，需要很少的能量来移动喉部构件; 并且其执行器可能具有最小的尺寸和重量。

Patent Agency Ranking