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公开(公告)号：US20080315039A1
公开(公告)日：2008-12-25
申请号：US11820916
申请日：2007-06-21
申请人： Lael Rudd , Bernard Morgowicz
发明人： Lael Rudd , Bernard Morgowicz
IPC分类号： B64G1/24
摘要： A spacecraft attitude controller balances external torques, including those resulting from gravity gradient and those resulting from other orbital disturbances, to achieve a comparatively stable, neutral attitude or orientation. Torque is balanced by selecting spacecraft attitude Euler angles and angular rates such that orbital disturbances and cross-coupling inertial effects are cancelled by the external forces, based on Euler's equation. A spacecraft attitude torque-balancing controller and related method compares spacecraft attitude angles and angular rates with an orbit reference frame, and provides instructions to conventional momentum management and propulsion controls to responsively adjust the spacecraft attitude and angular rates. This feedback loop drives to zero (or an acceptably small quantity) the rate of change of the difference between spacecraft and reference attitude and angular rates, thus minimizing the net accelerations on the vehicle. A further method is provided to determine a desired physical structure and mass distribution of the spacecraft, needed to achieve torque balancing in a spacecraft attitude such that appliances, such as antennas, solar panels, and instruments, will have the required orientation once in their final on-orbit deployed position.
摘要翻译： 航天器姿态控制器平衡外部扭矩，包括由重力梯度引起的外力和由其他轨道扰动引起的扭矩，以达到相对稳定，中立的态度或方向。 通过选择航天器姿态欧拉角度和角速率来平衡扭矩，使得轨道干扰和交叉耦合惯性效应基于欧拉方程被外力抵消。 航天器姿态扭矩平衡控制器和相关方法将航天器姿态角度和角速度与轨道参考系进行了比较，并提供了常规动量管理和推进控制指令以响应地调整航天器的姿态和角速率。 该反馈回路驱动零（或可接受的小量）航天器与参考姿态和角速率之差的变化率，从而最小化车辆的净加速度。 提供另一种方法来确定在航天器姿态下实现扭矩平衡所需的航天器的期望的物理结构和质量分布，使得诸如天线，太阳能电池板和仪器的电器将在其最终的一次中具有所需的取向一次 在轨部署位置。
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公开(公告)号：US10060419B2
公开(公告)日：2018-08-28
申请号：US14550372
申请日：2014-11-21
申请人： Lael Rudd , Robert W. Parker , Edmond K. Tajirian
发明人： Lael Rudd , Robert W. Parker , Edmond K. Tajirian
CPC分类号： F03H1/0087 , B60L15/08 , B60L50/50 , B60L2200/10 , B64G1/406 , F02K7/04 , Y02T10/645 , Y02T10/7005
摘要： A vehicle propulsion system includes an air heating chamber that receives inlet air from an air intake chamber and provides thrust through an exhaust chamber. A battery powered pulse generator generates a pulsed electrical output signal. An amplifier amplifies the pulsed electrical output signal to provide an amplified pulsed power output signal to the air heating chamber. The amplified pulsed power output signal directly heats the inlet air to generate thrust through the exhaust chamber.
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公开(公告)号：US07980514B2
公开(公告)日：2011-07-19
申请号：US12048981
申请日：2008-03-14
申请人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
发明人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
CPC分类号： B64G1/506 , B64G1/283 , B64G1/285 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , Y10S136/292
摘要： One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.
摘要翻译： 本发明的一个实施例包括一个航天器。 宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。 每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。 航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩 的太阳能电池部分和太阳能电池部分阵列的失活部分。
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公开(公告)号：US20090230250A1
公开(公告)日：2009-09-17
申请号：US12048981
申请日：2008-03-14
申请人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
发明人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
IPC分类号： B64G1/44
CPC分类号： B64G1/506 , B64G1/283 , B64G1/285 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , Y10S136/292
摘要： One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.
摘要翻译： 本发明的一个实施例包括一个航天器。 宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。 每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。 航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩 的太阳能电池部分和太阳能电池部分阵列的失活部分。
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