公开(公告)号：US20030062452A1

公开(公告)日：2003-04-03

申请号：US09947186

申请日：2001-09-04

Inventor： David Oh

IPC: B64G001/42 ,  F02K001/00 ,  F03H003/00 ,  F02K007/00

CPC classification number: B64G1/007 ,  B64G1/242 ,  B64G1/401 ,  B64G1/403 ,  B64G1/406

Abstract: Systems and methods for launching a satellite into orbit that optimize the mass of the satellite delivered into orbit. A satellite carrying one or more chemical propulsion devices and one or more electric propulsion devices is launched into a transfer orbit using a launch vehicle. In one embodiment, a selected chemical propulsion device is fired to raise the orbit of the satellite from the transfer orbit to an intermediate orbit. One or more electric propulsion device is fired to raise the orbit of the satellite from the intermediate orbit to final geosynchronous orbit, and the one or more electric propulsion device is throttled to produce variable thrust levels so as to operate at an optimum specific impulse level to optimize the mass of the satellite delivered into orbit. In another embodiment, the electric propulsion device may deliver the satellite into a near-geosynchronous orbit instead of final geosynchronous orbit. In this case, a selected chemical propulsion device is fired to place the satellite in its final orbit. In yet another embodiment, the launch vehicle may be used to deliver the satellite into the intermediate starting orbit after which the electric propulsion device is used to achieve final orbit. In this case, the transfer orbit raising step is omitted.

Abstract translation: 将卫星发射到轨道的系统和方法，优化传送到轨道的卫星的质量。 携带一个或多个化学推进装置和一个或多个电推进装置的卫星使用运载火箭发射到转移轨道中。 在一个实施例中，选择的化学推进装置被发射以将卫星的轨道从转移轨道升高到中间轨道。 一个或多个电力推进装置被发射以将卫星的轨道从中间轨道升高到最终的地球同步轨道，并且一个或多个电动推进装置被节流以产生可变的推力水平，以便以最佳比冲量水平运行 优化传送到轨道的卫星的质量。 在另一个实施例中，电力推进装置可以将卫星输送到近地球同步轨道，而不是最终的地球同步轨道。 在这种情况下，发射选定的化学推进装置将卫星置于其最终轨道中。 在另一个实施例中，运载火箭可以用于将卫星递送到中间起始轨道，之后使用电推进装置来实现最终轨道。 在这种情况下，省略了转移轨道提升步骤。

公开(公告)号：US20030079463A1

公开(公告)日：2003-05-01

申请号：US10029760

申请日：2001-10-29

Inventor： Bevin C. McKinney

IPC: F02K007/00

CPC classification number: F02K9/78

Abstract: A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.

Abstract translation: 具有改进的推力和高空能力的涡轮喷气发动机。 提供了在压缩机部分之前将液氧或其它氧化剂注入到涡轮喷气发动机中的布置。 通过液氧来冷却进入的空气减少了空气体积，这允许固定的入口与变化的流动条件匹配，允许由压缩机部分吸收更多质量的空气并导致较低的压缩机出口温度。 增加的质量流量，加上更多的燃料导致更高的废气温度和更大的推力。 向入口空气流中添加氧气允许发动机通过防止由于稀薄的空气而导致的熄火而在更高的高度运行。

公开(公告)号：US20040244359A1

公开(公告)日：2004-12-09

申请号：US10890337

申请日：2004-07-13

Inventor： John Michael Koshoffer ,  Kevin R. Drake ,  Lawrence Butler

IPC: F02K005/02 ,  F02K007/00

CPC classification number: F02K3/04 ,  F02K3/08 ,  F02K7/02

Abstract: A method facilitates generating thrust from a gas turbine engine using a pulse detonation system. The method includes introducing fuel and air to the engine, mixing fuel and air in a pulse detonation system deflagration chamber positioned radially outward from an engine exhaust centerbody, and detonating the fuel and air mixture within the pulse detonation system to facilitate increasing the temperature and pressure within the engine and to generate engine thrust.

Abstract translation: 一种方法有助于使用脉冲爆震系统从燃气涡轮发动机产生推力。 该方法包括将燃料和空气引入发动机，将燃料和空气混合在从发动机排气中心体径向向外定位的脉冲爆震系统爆燃室中，并引爆脉冲爆震系统内的燃料和空气混合物以便于增加温度和压力 在发动机内部并产生发动机推力。

公开(公告)号：US20030209635A1

公开(公告)日：2003-11-13

申请号：US10142239

申请日：2002-05-09

Inventor： John Quincy St. Clair

IPC: B64G001/24 ,  F02K001/00 ,  F03H003/00 ,  F02K005/00 ,  F02K007/00 ,  F02K011/00

CPC classification number: F03H99/00 ,  B64G1/409 ,  F03H3/00

Abstract: This invention relates to a spacecraft propulsion system utilizing a rotating octagon of trapezoidal electrically charged flat panels to create an electric dipole moment that generates lift on the hull. On the interior side of each panel are electrostatically charged rods which produce a planar electric field that emerges from holes in the panel to form an ellipsoidal potential energy bubble on the outside of the hull. The rotating hull dipole moment generates a magnetic moment which, together with the magnetic field gradient developed by the rotating electric field of the electrostatically charged panels, produces said lift force. The potential energy field is enhanced by using a double cladding of hull material with different ranges of permittivities.

Abstract translation: 本发明涉及一种利用梯形带电平板的旋转八角形产生电偶极矩的航天器推进系统，该偶极矩在船体上产生升力。 在每个面板的内侧是静电充电棒，其产生从面板中的孔出来的平面电场，以在船体的外部形成椭圆形势能泡。 旋转的船体偶极矩产生磁矩，其与静电带电面板的旋转电场产生的磁场梯度一起产生所述提升力。 通过使用具有不同范围的介电常数的船体材料的双包层来增强势能场。

公开(公告)号：US20040216447A1

公开(公告)日：2004-11-04

申请号：US10739082

申请日：2003-12-19

Inventor： Thomas H. Sharpe

IPC: F02K007/00

CPC classification number: F02K7/12 ,  F05D2260/601

Abstract: A turbineless jet engine includes no internal moving components, yet operates using a continuous combustion principle. The present engine is self-starting, i.e., no auxiliary source of pressurized airflow or unconventional fuels is required for its starting and operation. The present engine also requires no electrical energy after the combustion process has been initiated, with its fuel pump being operated by exhaust air from the engine. Starting injectors entrain airflow through the engine, with a portion of the inlet air being drawn through radially disposed, hollow pressure generators to the combustion section of the engine. Exhaust gas is recirculated to the front of the engine and passed through the pressure generators to entrain fresh air, to continue the cycle of operation. The present engine may be constructed in a variety of non-circular cross-sectional shapes, with or without inlet vane sweep, as desired, due to its lack of internal rotating components.

Abstract translation: 无涡轮喷气发动机不包括内部运动部件，而是使用连续燃烧原理进行操作。 本发动机是自启动的，即其起动和操作不需要辅助的加压气流源或非常规燃料。 在发动燃烧过程之后，本发动机也不需要电能，其燃料泵由来自发动机的废气运转。 起动喷射器夹带气流通过发动机，一部分入口空气通过径向设置的中空压力发生器被吸入发动机的燃烧部分。 废气再循环到发动机前部并通过压力发生器夹带新鲜空气，继续运行。 根据需要，本发动机可以以各种非圆形横截面形状构造，具有或不具有入口叶片扫掠，这是由于其缺少内部旋转部件。

公开(公告)号：US20040035098A1

公开(公告)日：2004-02-26

申请号：US10207796

申请日：2002-07-31

Inventor： Karim El Hamel ,  Arnold C. Newton

IPC: F02K003/00 ,  F02K007/00 ,  F02K009/00 ,  F02K009/74 ,  F02K009/76 ,  F02K011/00 ,  F02K009/78

CPC classification number: B64C11/001 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/10 ,  B64D27/12 ,  B64D27/14

Abstract: An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20). The support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced from the body or airframe of the aircraft.

Abstract translation: 发动机装置（14）包括燃气涡轮发动机单元（16）和第一和第二支撑构件（18,20）。 支撑构件（18,20）从发动机壳体（22）的结构部件（24）延伸，以将发动机单元支撑在与飞行器的主体或机身间隔开的位置。