专利汇可以提供Space Vehicle and Guidance and Control System for Same专利检索,专利查询,专利分析的服务。并且A space vehicle has a frame with a configuration of fiber optic gyroscopes (FOGs) and control moment gyroscopes (CMGs) at the outer perimeter of the frame. The FOGs and CMGs provide guidance and control for the space vehicle. This arrangement results in the largest possible FOG and CMG diameters, and therefore yielding the highest signal sensitivities and precision inertial control of vehicle orientation and pointing. Because the configuration places these guidance and control system components at the perimeter of the vehicle, it also provides a platform for multi-aperture signal channels in the interior of the vehicle by freeing up volume within the vehicle.,下面是Space Vehicle and Guidance and Control System for Same专利的具体信息内容。
This application claims the benefit of U.S. provisional patent application No. 61/789,938, entitled “Spherical Satellite System,” filed on Mar. 15, 2013. Such application is incorporated herein by reference in its entirety.
Not applicable.
The present invention relates to the field of space vehicle systems and subsystems used for inertial measurements, guidance and control. Specifically, the present invention relates to such systems and subsystems employing fiber optic gyroscopes (FOGs) and control moment gyroscopes (CMGs). FOGs perform a function similar to a mechanical gyroscope, but operate based on the interference of light that passes through a coil of optical fiber. Because they require no moving parts, they are generally considered more reliable than mechanical gyroscopes and are commonly used in space applications as a result. CMGs are attitude control devices that consist of a spinning rotor and one or more motorized gimbals that tilt the rotor's angular momentum, thereby causing a torque that rotates the spacecraft.
It has historically been assumed in space vehicle design that all the antenna communications systems be placed externally and configured to provide signal paths into the satellite via cables, with the electronics systems occupying various subsystems within the vehicle. These electronics systems thus take up valuable space within the space vehicle. Most three-axis FOG inertial measurement units (IMU) consist of a single, standalone package containing all three fiber coils placed orthogonally, thereby providing three axes of rotation rate measurements. CMG torqueing systems for space vehicles also typically occupy standalone volumes dedicated to providing torque, often configured with several solid heavy metal torqueing wheels; these are spun-up and maintained at various rotational speeds and are rotated to apply torque in varying conditions, thus providing various torque values to the space vehicle for orientation. A key but previously unrecognized limitation to these standalone subsystem packaging paradigms is that the diameters are restricted to only the space provided solely for the FOG 3-axis IMUS and separate volumes for the CMG wheels and electronics. In addition, the inventor hereof has recognized that placing these components nearer to the center of the space vehicle reduces their sensitivity.
Given the great cost of launching satellites and other space vehicles into space and the premium attached to available volume within a space vehicle, a more efficient way to configure systems and subsystems associated with a space vehicle or satellite, particularly systems and subsystems related to FOGs and CMGs, would be highly desirable. In addition, a configuration of FOGs and CMGs that maximized the sensitivity of these instruments would also be highly desirable.
References mentioned in this background section are not admitted to be prior art with respect to the present invention.
The present invention is directed to a new configuration of FOGs and CMGs specifically placed into the outermost perimeter of the space vehicle, thereby providing the largest possible FOG and CMG diameters, and therefore yielding the highest signal sensitivities and precision inertial control of vehicle orientation and pointing. Both FOGs and CMGs provide better precision for their measurements in proportion to their diameters; a larger diameter improves the precision of the rotation rate, measured in degrees per second or radians per second, of the FOG, and a greater amount of space vehicle torque with larger diameter CMGs. At the same time, this new configuration provides a platform for other components, including multi-aperture signal channels, by freeing up volume within the space vehicle.
In certain embodiments, three separate FOG fiber coils are placed orthogonally and normal to the space vehicles' inertial reference frame's orthogonally defined axes, X, Y, and Z, thereby providing rotation rates about each axis. Each fiber coil is configured into the outer perimeter of the space vehicle, and thus uses a maximum possible diameter for the best possible measurement sensitivity. In these embodiments, a common circular mechanical structure for each orthogonal fiber coil and the CMGs is employed comprising solid heavy metal annular rings. The annular ring CMGs and FOGs are packaged directly adjacent to one another in the three orthogonal ring mechanical structures. While providing the best possible precision by occupying the space vehicle's outer perimeter, this also provides an open inner volume for signal processing transmitters, receivers, optical imaging sensors, or other components. These embodiments therefore provide single-axis FOG & CMG navigation and guidance components contained in a common annular ring package, with the signal processing electronics adjacent to each of the three orthogonal rings.
These and other features, objects and advantages of the present invention will become better understood from a consideration of the following detailed description of the preferred embodiments and appended claims in conjunction with the drawings as described following:
Before the present invention is described in further detail, it should be understood that the invention is not limited to the particular embodiments described, and that the terms used in describing the particular embodiments are for the purpose of describing those particular embodiments only, and are not intended to be limiting, since the scope of the present invention will be limited only by the claims.
A preferred operational embodiment of the present invention consists of three FOGs with circular fiber coils wrapped and embedded orthogonally in the outer diameter of a spherical structure, with respect to the spacecraft's X-Y-Z coordinates. The three rotational measurements are electronically coupled continuously to the inertial navigation and guidance system, consisting of CMGs and closed-loop electronics, via direct and short signal paths. Three orthogonal rings with the co-planar CMGs and FOGs in close proximity can provide a full range of rotational motion for vehicle orientation and pointing. This also provides the inner volume of the vehicle for optical signal processing of images and sensors, and free space optical communications (FSOC) channels, all with entrance and exit apertures occupying opposite inner sides of the vehicle. The first optical element at each entrance/exit is a wide field lens through the middle of the vehicle sphere, with a continuous optical path toward the opposite side of the sphere. A focal length equal to the diameter of the sphere terminated at the opposing surface would be used for shorter distance free space optical (FSO) links, while a longer focal length telescope could be used by placing a concave reflecting mirror at the opposing side, as in a Cassegrainian configuration, for longer distance FSO links. This configuration is ideal for using FSO beam pointing and tracking at the focal plane of these telescopes, as set forth in U.S. Pat. Nos. 7,612,329, 7,612,317, 7,224,508, and 8,160,452, which are incorporated by reference herein. The light signals use telescope optical designs configured into the vehicle structure using the empty inner volume for the telescope's optical signal paths and focus onto the imaging/sensor array (for example, CCD, visible, IR, and cooled). A fiber optic data handling network is embedded into the FOG fiber optic coils, using optical taps and splitters for inserting and removing the optical data signals. The fiber optic data handling networks consists of high-speed optical channels for relays and processing, and command, telemetry, and control (CT&C) networks. Separating the optical data channels from the FOG signals is straightforward using optical electronic filtering, as well known in the art.
Describing the preferred embodiment of the present invention more specifically now with reference to the figures,
with the measured rotational rate being directly proportional to the optical path length difference Δφ and wavelength λ. The faster the rotation, the larger the path length difference Δφ, and thus the more precise the rotation rate measurement θR. Thus the preferred embodiment of the present invention, which places the FOG coils along the outer perimeter of the space vehicle, results in the best possible precision, and also provides an open inner volume for signal processing transmitters, receivers, optical imaging sensors, or other devices.
In operation of the FOGs, three separate rotation measurements are made via the three separate orthogonally configured Sagnac interferometers. The Sagnac interferometer is the well-known FOG interferometer that utilizes counter-propagating optical beams to measure an optical signal that is proportional to the optical phase difference (optical path difference) caused by rotation. This arrangement increases the sensitivity of the devices, since the coil diameter will be at a maximum in this configuration and the precision sensitivity of the detected rotation rate is inversely proportional to the coil diameter and fiber length. Additionally, a large diameter and longer fiber length can be spooled while keeping the thickness (volume) to a minimum.
The CMG wheel may reside within the outermost portion of the ring structure, or inside of the FOG coil, as depicted in
A variety of configurations for the apparatus can provide vehicle stabilization since the orientations of the rings can be configured in various ways. A basic orientation with the rings placed in three orthogonal planes as in the preferred embodiment of the present invention provides three rotational degrees of rotation. More complex configurations could include multiple CMG/FOG rings to provide enhanced precision in orientation and pointing. In alternative embodiments, two CMG rings could be placed in the same parallel plane of rotation, and spun up in opposite rotating directions, and a relative rotational speed between the two would vary the orientation of the vehicle, while stabilizing the vehicle. This configuration would have a similar effect as used for spin-stabilized satellites, which are spun about a relatively fixed axis for stabilization. However, the spinning CMGs would apply the stabilizing torque while the satellite overall vehicle attitude remains fixed. As is well known in the art, imparting a balanced overall torque to the vehicle keeps the attitude of the vehicle at a known fixed value.
The CMGs in the preferred embodiment function like those onboard space telescopes, and other momentum wheels in many other satellites, except that their mass is distributed about the diameter of the sphere, thereby providing the greatest amount of torque per unit mass. A desired result of this configuration is that the three CMGs are able to provide a full pointing capability for the vehicle with a minimum or no use of external correction thrusters.
Referring now to
As depicted in
Unless otherwise stated, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Although any methods and materials similar or equivalent to those described herein can also be used in the practice or testing of the present invention, a limited number of the exemplary methods and materials are described herein. It will be apparent to those skilled in the art that many more modifications are possible without departing from the inventive concepts herein.
All terms used herein should be interpreted in the broadest possible manner consistent with the context. In particular, the terms “comprises” and “comprising” should be interpreted as referring to elements, components, or steps in a non-exclusive manner, indicating that the referenced elements, components, or steps may be present, or utilized, or combined with other elements, components, or steps that are not expressly referenced. When a Markush group or other grouping is used herein, all individual members of the group and all combinations and subcombinations possible of the group are intended to be individually included. All references cited herein are hereby incorporated by reference to the extent that there is no inconsistency with the disclosure of this specification.
The present invention has been described with reference to certain preferred and alternative embodiments that are intended to be exemplary only and not limiting to the full scope of the present invention, as set forth in the appended claims.
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