Abstract:
A method and apparatus for conducting proximity operations is disclosed. The method called inverser proximity operations includes maneuvering an active vehicle into general proximity to a target vehicle, transmitting from the target vehicle to the active vehicle data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle in accordance with the data to effect a desired proximity operation. Another method called distributed proximity operations includes maneuvering a carrier vehicle into general proximity to a target vehicle, releasing one or more active vehicles from the carrier vehicle, transmitting from the carrier vehicle to the active vehicle(s) data representing relative position and velocity between the target vehicle and the active vehicle, and maneuvering the active vehicle(s) in accordance with the data to effect a desired proximity operation. The proximity operations are similarly suitable for aeronautical systems, such as when using an active aircraft to re-fuel a target aircraft, such as a drone. Whether for space, air, or other environments, the proximity operations described can be used for re-fueling, repairing, and replacing components and/or systems.

Description:
BACKGROUND OF THE INVENTION 
   1. Field of the Invention 
   The present invention relates generally to remote control maneuvering of vehicles, and more specifically, to proximity operations between a relatively large target vehicle and a relatively smaller service vehicle. The service vehicle can have a multitude of specific missions, such as re-fueling the target vehicle, providing replacement components to the target vehicle, providing course corrections or other steering functions for the target vehicle, and even simple inspection. 
   2. Description of the Related Art 
   In a variety of fields, vehicles capable of sophisticated functionality and/or operating in hostile or remote environments tend to be costly to build and place in use. In no other field is this more dramatic than space vehicles, such as satellites, which can cost hundreds of millions of dollars. Satellites costing hundreds of millions of dollars to produce can also cost hundreds of millions of dollars to launch. Launch costs are directly related to the size or weight of the payload. 
   Occasionally a satellite can become either completely or partially inoperable due to system wide or component-specific failures. Even in the absence of an unexpected failure, satellites are considered to have finite, and relatively short, lives due to the limited supply of fuel for operating thrusters (which are required to maintain a desired orbit and attitude), and the limited life span of moving parts or heat-generating parts, such as momentum wheels that are used for attitude control. Batteries and solar cells are also known to have only so many charge/discharge cycles before they too become either inoperable or of diminished capacity. 
   In the past, it has been known to employ human resources, i.e., astronauts, on manned space missions, to dock with a troubled satellite to initiate a repair. Probably the most notable example of that would be the Hubble Space Telescope where an optical correction package was installed by what could be described as a conventional proximity operation. 
     FIG. 1  illustrates a conventional proximity operation in which a target vehicle  10  is presumed to have some need for a proximity operation. In the case of the Hubble Space Telescope, the target vehicle would be the Hubble satellite which, schematically illustrated, would include a sensor component  12 . The sensor component  12  for the Hubble Space Telescope is an optical telescope that includes a plurality of optical elements. 
   When it became clear that a repair to the optical elements was required of the Hubble Space Telescope, NASA launched the Space Shuttle as a service vehicle  14  with the mission of repairing the sensor  12 . In that case, the service vehicle  14  was manned, relatively large, and relatively expensive to launch and provision. The service vehicle  14  included an on-board sensor  16  for sensing position and velocity of the target satellite  10  for the purpose of making proximity maneuvers. The service vehicle  14  also included a processor module  18  for taking the position and velocity data of the sensor  16  and converting that data into command signals for thrusters, such as thrusters  20 ,  22 , and  24 , which can be differentially operated to provide a desired approach for docking. The service vehicle  14  also includes an attitude control system  25  which can also be used to precisely position the service satellite during docking or for precise inspection vectors. 
   A cooperating docking means allows the two satellites to be coupled together during the repair operation. A typical docking means could include a post  26  which is grabbed by a grappling arm  28 . 
   Thus, the repair mission performed in the past, as demonstrated by the Hubble Space Telescope mission, entails the following operations. First, the service vehicle is launched. Following launch, the service vehicle will rendezvous with the target vehicle. During the rendezvous, the two vehicles come into proximity to each other as a result of orbital software. The orbital software takes into account the dynamics of the two orbits, meaning the orbit of the target vehicle and the orbit of the service vehicle. Orbital software allows the service vehicle to undergo a series of maneuvers to get somewhat close to the target vehicle; depending on the size of the vehicles, “close ” can be anywhere from 1 to 100 kilometers, although greater or lesser distances can be foreseen. 
   Once rendezvous has been completed, for a manned mission, a pilot or astronaut takes manual control of the service vehicle and completes maneuvers either to perform the inspection sequence, or to bring the service vehicle into close proximity, meaning, close enough for the software and control to take over. Thus, for example, at the end of the proximity maneuvers, the two vehicles are ready to dock. Once docking has been completed, the repair is made by manual replacement of the sensor  12  on the target vehicle  10 . 
   A number of patents describe maintenance and/or repair operations in space. For example, U.S. Pat. No. 5,421,540 to Ting describes a method and apparatus for recovering space debris, in which recovery vehicles are launched, and maneuvered to come into close proximity with a target object, which may-be a satellite or simply debris. As described therein, the sensing and maneuvering aspects of the proximity operation are carried by the repair or recovery vehicle. Such arrangements tend to require large, complicated vehicles that are relatively expensive to build and launch. 
   U.S. Pat. No. 4,298,178 to Hujsak describes a roving geosynchrounous orbit satellite maintenance system, in which a maintenance vehicle docks with a larger vehicle and off-loads replacement equipment. The vehicle includes a rotatable cradle containing part modules which can be rotated into position so that parts can be off-loaded. 
   U.S. Pat. No. 4,079,904 to Groskopfs et al. describes in greater detail some known docking structures that might be used in vehicles such as the Space Shuttle. U.S. Pat. No. 6,364,252 to Anderman describes a technique for implementing a particular rendezvous sequence or operation. 
   While the aforementioned proximity operations, particularly the Hubble repair mission, can be very effective at making certain repairs, they can also be so costly as to bring into question whether it might be less expensive to launch a replacement of the satellite  10 , rather than make repairs to it. 
   SUMMARY OF THE INVENTION 
   The present invention provides a unique approach to proximity operations for many types of vehicles, including satellites. In one aspect of the invention, a method of conducting a proximity operation is provided, in which a service vehicle is maneuvered into general proximity to a target vehicle. Then, vehicle data is transmitted from the target vehicle to the service vehicle, wherein the vehicle data represents relative position and velocity between the target vehicle and the service vehicle. The service vehicle is then maneuvered in accordance with the data to effect a desired proximity operation. In a second aspect of the invention a method of conducting a proximity operation is provided in which the service vehicle, once in general proximity to a target vehicle, releases a secondary active vehicle. In this case the service vehicle transmits the relative position and velocity data between the target vehicle and active vehicle for the desired proximity operations. 
   In one embodiment, the target vehicle is a first satellite and the service vehicle is a second satellite, and the at least one control device includes at least one thruster disposed on the second satellite. Maneuvering is thus accomplished by throttling the at least one thruster in accordance with the command signals that are derived from the vehicle data. Alternatively, the target vehicle can be a first aircraft and the service vehicle a second aircraft. In such an embodiment, the at least one control device includes at least one control surface, such as a vertical stabilizer, flap, etc. Maneuvering the service vehicle is thus accomplished by moving the at least one control surface in accordance with the command signals that are derived from the vehicle data. 
   The features and advantages of the invention will become more apparent from the following detailed description when taken in conjunction with the illustrative embodiments in the accompanying drawings. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
       FIG. 1  is a schematic view depicting a conventional proximity operation, in which a target vehicle, such as a satellite, is approached by an active vehicle; 
       FIG. 2  is a schematic view depicting an inverse proximity operation and systems for performing same according to one embodiment of the present invention; 
       FIG. 3  is a schematic view depicting a distributed proximity operation and systems for performing same according to another embodiment of the present invention. 
   

   DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
   Referring to  FIG. 2 , a target satellite  30  includes a payload or sensor  32  which could be, for example, a telescope or other sensing device. The target satellite  30  could have been designed for any number of different missions. For example, the satellite  30  could be an earth observation satellite, a space telescope, or any number of other satellites or space vehicles carrying a variety of instruments. For demonstration of the present inventive concepts, it will be assumed that the satellite  30  includes other standard components including a processor  34  and an attitude control module  36 . 
   One aspect of the invention is to provide a proximity operation in order to effect a repair or service the satellite  30  as the need arises. For example, the satellite  30  may run out of fuel that is necessary to operate on-board thrusters. Without fuel for the thrusters, the orbit of the satellite will eventually decay, causing the satellite to burn up on re-entry into Earth&#39;s atmosphere. Other failure possibilities include failures in the attitude control system or components thereof (such as failures of one or more of the momentum wheels), failures in the processor section or components thereof (or simply the need for upgraded processors) or failure to deploy solar arrays or antennae. Any number of other failures may be encountered that could shorten the useful life of the satellite  30  or even cause complete failure of the satellite and/or its mission. 
   According to the present invention, the satellite  30  includes a communication module  38  that includes a broadcast antenna  40 . An active satellite  42  could be launched in response to the discovery of one or more of the aforementioned needs. Alternatively, the active satellite  42  could have been launched at a prior time and placed in a service orbit from which it can be called on an as needed basis. The active satellite  42  is intentionally of smaller dimensions and carries fewer systems, in terms of size and functionality. However, like the satellite  30 , active satellite  42  includes an attitude control module  44  and a processor  46 . Active satellite  42  is un-manned, and does not carry a mission payload or sensor such as those carried by the target satellite  30 . It does, however, include a communication module  48  which includes a receive antenna  50 . 
   As an example of size differences, the target satellite  30  could be in the range of a 3×3×3 meter cube weighing 5,000 kg, while the active satellite  42  could be in the range of a 0.5×0.5×0.5 meter cube weighing 100 kg. Because of these relative size differences, the active satellite is relatively inexpensive to launch compared to the target satellite. For example, the target satellite may require a Space Shuttle mission to launch, while the active satellite  42  could be launched from a single, smaller rocket, such as the Pegasus rocket. 
   As an initial step in the inverse proximity operation, the active satellite  42  is programmed to initiate a rendezvous operation with the target satellite  30 . The rendezvous operation brings the two satellites into general proximity to each other, generally within 1 to 100 kilometers of each other. The rendezvous operation can be effected by launching the active satellite into the target satellite&#39;s orbit at a velocity which results in the two satellites coming into proximity. A sensor on the target satellite  30  is directed at the active satellite to obtain data reflecting the position and velocity of the active satellite  42  relative to the target satellite  30 , or visa versa. In one embodiment, the payload or sensor  32  of the target satellite  30  is turned in the direction of the active satellite  42 , either by turning the target satellite  30  or turning the sensor  32 . 
   Once the sensor  32  begins receiving data indicative of the active satellite&#39;s position and velocity, the data is sent to the communication module  38 , processed appropriately, and then broadcast to the active satellite  42  via broadcast antenna  40 . In accordance with this position and velocity data, the processor  46  computes control signals for rocket motors  52  arranged around the active satellite to effect pitch, roll, yaw, and translational movement of the active satellite  42 . 
   As the active satellite  42  moves into closer proximity to the target satellite  30 , the sensor  32  continually provides updated velocity and position data so that the rocket motors  52  can be throttled accordingly. Preferably, the two satellites are brought into an inspection position or a docking position by which a docking mechanism similar to that shown in the prior art example is used. The docking stage of the operation occurs in the last ten (10) centimeters of the maneuver and is typically controlled by known docking software. 
   Once docking has taken place, the need of the target satellite can be satisfied. For example, if the target satellite  30  is in a declining orbit due to failure of its primary boost motor, the active satellite  42  can use its rocket motors to re-boost the target satellite  30 . After re-boosting, the active satellite  42  can de-couple and return to a service orbit, or simply de-boost itself into re-entry into Earth&#39;s atmosphere to prevent orbiting debris. 
   Thus, the active satellite  42  can have a single, primary mission, such as the aforementioned re-boost operation, after which the active satellite  42  can be disposed of. Alternatively, the active satellite  42  can be equipped to perform multiple missions so that, for example, the active satellite  42  can be returned to a service orbit after performing a mission vis-a-vis one target satellite, to be “on call” for other missions for the serviced satellite or other satellite. 
   Examples of other missions include the following, which is not intended to be an exhaustive list. In the event of a major failure of the target satellite&#39;s on-board computer or processor  34 , the active satellite  42  may be tasked to provide a replacement processor, either by attaching a removable processor module from the active satellite through the docking mechanism, or by remaining attached after coupling through the docking mechanism with the replacement processor taking over processor functions from the original processor. Similarly, failure of the target satellite&#39;s attitude control module could require replacement of the module via attachment of the active satellite  42  to the target satellite  30 . 
     FIG. 3  describes another embodiment of the present invention in which distributed proximity operations are performed. A target satellite  54  includes a sensor  56 , but may or may not include a processor, attitude control module, or communication module. Such a satellite may have been launched some time ago and subsequently developed a problem, such as a failed sensor  56 , and may need repair to salvage its mission. Alternatively, the satellite  54  could have been newly launched but because of some system failure, may never have been activated, or -may be unable to achieve a desired orbit. 
   In the distributed proximity operation embodiment, a satellite  60  may be launched to carry out a repair mission with respect to the target satellite  54  and others. The launch of the satellite  60  may have occurred in response to the failure of the target satellite  54 , or it may have been launch prior to that time on an unrelated mission. As an example, the satellite  60  could be the Space Shuttle, or any other vehicle that includes a sensor  62 . 
   Satellite  60  can carry one or more active satellites  64  and  66  which can be decoupled from the satellite  60  for specified missions. Each active satellite includes the same components as the active satellite  42  of the  FIG. 2  embodiment, including attitude control system, a processor, a communications module which includes a receive antenna, and a plurality of rocket motors to effect desired maneuvers. Similarly, the satellite  60  includes a communication module  68  which transmits position and velocity data to the one or more active satellites. The active satellites  64  and  66  may be detachably coupled to the satellite  60  prior to deployment for a mission, or may be separately launched and placed in a service orbit, awaiting command signals from a control satellite or vehicle, such as satellite  60 . Individual active satellites  64  and  66  may or may not be detachably coupled to each other prior to deployment on a mission. 
   To initiate the distributed proximity operation, an active satellite, such as satellite  66 , is launched to rendezvous with the target satellite  54 . The launch may be from the satellite  60 , in which case the launch is more of a jettison step, or from a separate launch vehicle, such as a Pegasus rocket. In either event, the satellite  60 , acting as a control satellite, also maneuvers to rendezvous with the target satellite  54  but remains at a distance. The distance is one that allows the sensor  62  to “see” both the target satellite  54  and the active satellite  66 . Once this happens, the communication antenna of the control satellite broadcasts data indicative of relative position and velocity between the active satellite  66  and the target satellite  54  to the receive antenna of the active satellite  66 . 
   The on-board processor of the active satellite  66  derives control signals for the rocket motors to cause the active satellite  66  to maneuver into an inspection vector or a docking position with respect to the target satellite  54 . As in the embodiment of  FIG. 2 , a docking sequence may be executed which completes the proximity operation, resulting in the coupling of the active satellite  66  to the target satellite  54 . Alternatively, the mission of the active satellite  66  may be simply to observe the target satellite  54 , e.g., to assess damage visually or with other instrumentation. In such situations, the active satellite would include a broadcast antenna for delivering data to the control satellite, but given the desire to keep the active satellites small, the broadcast of data would be over short distances to limit power requirements and thus size. 
   In the distributed proximity operation embodiment, any number of missions can be accomplished, include a re-boost, where the active satellite is coupled to the target satellite, and one or more rocket motors of the active satellite are throttled to boost the target satellite into a different, usually higher, orbit. For a re-boost operation, multiple active satellites may be couple at different locations of the target satellite to achieve a desired maneuver. 
   A variation of the re-boost mission would be a de-boost mission, where, for example, a target satellite is incapable of repair or salvage, and the mission is to send the dead or crippled satellite into the Earth&#39;s atmosphere for burn-up, thereby freeing the orbital space from debris. 
   As mentioned, the mission could be one of simple observation, to collect data without docking, and deliver the data to the mother ship. In the data collection mission, either low power transmission of data is accomplished with a transmit antenna, or the data can be stored on-board the active satellite, and the active satellite can be retrieved by and re-coupled to the control satellite  60 . 
   To describe a typical sequence of steps undertaken for a distributed proximity operation, a target satellite is launched on an independent mission, which may be, for example, a scientific mission to measure gamma radiation The target satellite will include a number of critical sub-systems, such as its on-board processor, power systems, an attitude control system (which in this example includes rocket motors with a finite supply of fuel carried on-board), and the primary mission instrumentation, such as a gamma radiation measuring instrument. 
   At some time after launch, a system failure is detected, or an anomaly is suspected, and a decision is made to launch a repair mission. A control satellite or vehicle is launched which carries an instrument or sensor capable of sensing telemetry data (typically velocity and position) and a communication module for sending the data to the active satellite. The control satellite, which could be the Space Shuttle, for example, or an unmanned vehicle, undertakes a rendezvous operation, which brings the control satellite in proximity to the target satellite. The rendezvous operation, if carried out by an un-manned vehicle, is typically executed using orbital data of the target satellite and of the control satellite. The timing of launch and other launch and initial guidance parameters may alone bring the control vehicle into a rendezvous with the target satellite. 
   Once rendezvous is complete, one or more active satellites can be release from the control satellite on an initial trajectory which puts it on a course with the target satellite. This typically would occur when the control satellite is within 1 to 100 kilometers of the target satellite, which is the approximate distance it would take the sensor  62  to begin providing data indicative of the relative position and velocity of the active satellite and the target satellite. 
   After initial de-coupling of the active satellite from the control satellite, the active satellite is programmed to start moving towards the target satellite. However, once position and velocity information is transmitted to the active satellite from the control satellite, the rocket motor or motors of the active satellite are throttled to bring the active satellite into very close proximity, such as to collect data without docking, or to close the gap between the two until a docking sequence can take over and effect the final docking operation, resulting in a coupling of the active satellite with the target satellite. Depending on the mission, the active satellite may provide boosting, de-boosting, or may augment failed systems by remaining attached but connecting in modular fashion to one or more of the target satellite subsystems. 
   All of the embodiments described can be analogously applied to the field of aeronautics. For example, an unmanned aircraft such as a drone may be remotely controlled to stay airborne over an area to be observed. When the drone is low on fuel, it must be returned to base for the refueling operation. Using the proximity operations of the present invention, an active aircraft is equipped with a receive antenna, and the drone is equipped with a transmit antenna and a sensor for sensing the position and velocity of the active aircraft. The active aircraft carries a supply of fuel to deliver to the drone. During proximity operation, the sensor gathers data indicative of the relative velocity and position of the drone relative to the active aircraft, and transmits this data through its transmit antenna to the receive antenna of the active aircraft. An on-board processor associated with the active aircraft calculates control signals that will cause the active aircraft to maneuver into a docking position relative to the drone. Once the docking position is achieved, a deployable fuel line connects the fuel tank of the drone to the fuel tank of the active aircraft. Once the re-fueling has been completed, the active aircraft can be programmed to return to base, or to crash land. 
   Similarly, the active aircraft can be used to perform other functions relative to the drone, such as, observing the drone to detect an otherwise undetectable malfunction, or providing a transfer of field data from the drone to the active aircraft. Such a transfer could be effected without a physical coupling of the two aircraft, in the event of using low-power wireless communication between the drone and the active aircraft. Additional fields of applications include naval and ground vehicle applications. 
   A further embodiment for satellites is to deploy satellites on initial launch to include detachable pods of the type referred to as the active satellites. In some circumstances, a piece of debris or other obstruction in space may come into a collision course with the target satellite. Once this is detected, the satellite can release one or more pod satellites which are released in the general direction of the obstruction. As soon as the pod and the obstruction can be detected by a sensor located on the satellite, and data can be generated which correlates to the relative velocity and position between the pod and the debris, this data is transmitted to the receive antenna of the pod from the transmit antenna of the target satellite. The pod&#39;s processor converts this data into control signals for its propulsion system, in effect guiding the pod into the vicinity of, or into contact with the obstruction. Once in contact, the pod&#39;s thrusters can be activated to nudge the obstruction out of its original course. 
   In general, the inventions described herein can potentially change the design of spacecraft and the way orbital operations are performed by enabling smaller, nimbler spacecraft to perform the required operations. This could potentially decrease by orders of magnitude launch and operation costs, thereby enabling a whole new view of how to use space-based assets. 
   The new techniques described herein separate the sensing activities of the target and/or host spacecraft (location and orientation of target spacecraft) from the maneuvering activities of the active satellite by taking advantage of communication services and/or relative navigation information between spacecraft. Since the maneuvering satellite does not have to carry the large sensing suite, it can be much lighter and use less fuel. Also, it could dock with a disabled satellite or a satellite that was not originally designed to support a cooperative docking activity. 
   For inverse proximity operations, where the host spacecraft is required to rendezvous, dock or re-acquire a remote sensing or servicing platform, the host spacecraft&#39;s sensing suite is used to determine the relative position of the two spacecraft and to compute the desired commands and trajectories for the active spacecraft to follow. These commands are then transmitted to the active spacecraft which performs the proximity operations with its propulsion system. 
   For distributed proximity operations, where a third (possibly disabled) spacecraft is the target, the host spacecraft sensing suite is used to determine the relative position of the maneuvering spacecraft and the target spacecraft, and to compute a trajectory and propulsion commands. This information is communicated to the active spacecraft which executes the desired proximity operations. 
   In both cases the feedback for the proximity operations is sensed and preferably computed on a spacecraft separate from the spacecraft that maneuvers. 
   Although the invention has been described with reference to particular embodiments, it will be understood to those skilled in the art that the invention is capable of a variety of alternative embodiments within the sprit of the appended claims.