Deployable satellite system for dynamic space domain awareness

Abstract

Spacecraft systems, methods and devices comprising satellite upgrade modules or hosted payload modules that facilitate the deployment of small, deployable satellites from a base station to perform various potential missions including, for example, space domain awareness (SDA) missions to inspect and characterize resident space objects in orbit.

Description

DEPLOYABLE SATELLITE SYSTEM FOR DYNAMIC SPACE DOMAIN AWARENESSInventors: Ghonhee Lee, Andrew Sabovik, Ryan Herberg, and Jeremy CorreaGOVERNMENT LICENSE RIGHTS

[0001] This invention was made with government support under contract FA864924P0892 awarded by Air Force Research Laboratory / AFWERX.The government has certain rights in the invention.TECHNICAL FIELD

[0002] The present disclosure relates generally to spacecraft systems, methods and devices comprising satellite upgrade modules or hosted payload modules that facilitate the deployment of small, deployable satellites from a base station to perform space domain awareness (SDA) missions to inspect and characterize objects in orbit.BACKGROUND

[0003] The surge of Resident Space Objects (RSO) and space actors has led to a congested, contested, and complex space environment. This poses a risk to the security of on-orbit assets from, for example, collisions with space debris or conjunction with another satellite. Spacecraft owner / operators must reduce the time required for RSO characterization, avoidance maneuvers, and anomaly resolution from months / years to hours / days to protect assets. Accordingly, spacecraft systems, methods and devices that perform SDA missions to inspect and characterize objects in orbit, non-SDA missions including sensing, jamming, anti-jamming and other missions, are desirable.SUMMARY

[0004] A spacecraft command and control system for a spacecraftsystem comprising an operator-interface that uses a generalized path planning algorithm to identify optimal rendezvous and proximity operations (RPO) around a resident space object (RSO), wherein the system receives operator-configurable mission parameters and priorities for operations including at least one of an RSO state, an RSO form, a speed of mission completion, a fuel usage, required viewing angles, a relative position with respect to celestial bodies, a relative position with respect to the RSO, and a keep out zone.

[0005] A spacecraft system in a staged orbit for performing rapid RPO around a resident space object in response to a deployment command issued via a spacecraft command and control system, the spacecraft system comprising a base station and a satellite deployment subsystem containing at least one deployable satellite capable of carrying out a variety of missions, including, among others, at least one RPO mission, SDA missions, non-SDA missions including sensing, jamming, antijamming and other mission (any of which may be referred to herein as a ’’mission” or “missions”), each deployable satellite comprising deployable unit subsystems comprising a bus structure with embedded computational subsystems, power subsystems, and communications subsystems. The base station may comprise an SDA subsystem, a bus structure with embedded computational subsystems, power subsystems, and communications subsystems, and at least one of an electro-optical sensor payload, infrared sensor payload, radiofrequency sensor payload, and LIDAR sensor payload to provide local situational awareness and far-field resident space object detection from a staging orbit, and an interface for attachment to a host satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] The accompanying drawings are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of thisspecification, illustrate embodiments of the disclosure, and together with the description serve to explain the principles of the disclosure, wherein:

[0007] Figure 1 illustrates perspective views of a base station and a deployable satellite in accordance with the present disclosure;

[0008] Figure 2 illustrates exploded perspective views of a base station and a deployable satellite in accordance with the present disclosure;

[0009] Figure 3 illustrates that detection range is a function of the angle between the sun, target, and observer, namely, with a sun angle of 45° the base station detects a Boeing 702HP satellite bus and a 16U CubeSat at 2,000 km and 40 km, respectively in accordance with the present disclosure;

[0010] Figure 4 illustrates integrated multi-parameter systems engineering optimization to decouple maneuvers from attitude constraints to meet mission needs such as payload, ground communication, and solar pointing requirements to enable complex RPOD maneuvers in accordance with the present disclosure;

[0011] Figure 5 is a perspective view of a base station with a deployable satellite being ejected in accordance with the present disclosure;

[0012] Figure 6 is a Sample Based Model Predictive Optimization flow diagram in accordance with the present disclosure; and

[0013] Figure 7 is a tasking architecture activity diagram in accordance with the present disclosure.DETAILED DESCRIPTION

[0014] Persons skilled in the art will readily appreciate that various aspects of the present disclosure can be realized by any number of methods and systems configured to perform the intended functions. Stated differently, othermethods and systems can be incorporated herein to perform the intended functions. It should also be noted that the accompanying drawing figures referred to herein are not all drawn to scale but may be exaggerated to illustrate various aspects of the present disclosure, and in that regard, the drawing figures should not be construed as limiting. Finally, although the present disclosure can be described in connection with various principles and beliefs, the present disclosure should not be bound by theory.

[0015] The present disclosure relates to spacecraft systems, methods and devices (for ease of reference, collectively, “spacecraft system” or “spacecraft systems”) comprising satellite upgrade modules or hosted payload modules that facilitate the deployment of small, deployable satellites from a base station that perform space domain awareness (SDA) missions and other missions to inspect and characterize objects in orbit. At various points in the present disclosure, SDA missions and related assets may be referenced specifically, though it should be appreciated that other missions are also contemplated herein and this disclosure should not be construed as limited to SDA related missions and assets.

[0016] The spacecraft systems contemplated herein are able to characterize on-orbit objects via deployment of SDA assets to anywhere within the Geostationary Earth Orbit (GEO) belt in under 24-hours. Currently, defensive space operations asset owner / operators, such as the United States government, must decide between consuming resources to inspect RSOs at the cost of reducing mission lifetime, or doing nothing. The spacecraft systems contemplated herein are a low-cost alternative to capabilities like Geosynchronous Space Situational Awareness Platform (GSSAP), providing operators the ability to conserve fuel on high-value assets while rapidly responding to emerging defensive space operation needs. When prepositioned in GEO, the spacecraft systems contemplated herein will complementexisting SDA assets like GSSAP by providing operators with a low-cost, low-resource characterization capability within 24-hours of an identified RSO - conserving GSSAP resources.

[0017] Within the context of RSO characterization, the spacecraft systems provide the following value:• Use-case flexibility - the spacecraft systems support multiple missions including detect and tracking of far-field RSOs, characterization and identification of near-field RSOs, self-inspection, observation, and anomaly resolution.• Pre-positioned - the spacecraft systems can be staged on-orbit at strategic locations and on strategic assets, allowing near zero response time for strategic GEO locations, and within 24-hours anywhere else in GEO belt.• Multiple deployment channels - the spacecraft systems enable rapid proliferation via three (3) deployment channels including pre- and postinstall onto a high value asset (HVA), as well as deployment on Orbit Transfer Vehicles (OTV).

[0018] The above being noted, spacecraft systems system in accordance with the present disclosure comprise a microsatellite that includes a base station and at least one deployable satellite, for example, as illustrated in Figure 1 though, as illustrated in Figure 2, multiple deployable satellites may be deployed, each enabling execution of the entire SDA mission. The spacecraft systems contemplated herein may use electro-optical (EO) sensors to detect RSOs > 1 ,500 km away from its orbital slot and characterize RSOs via 100-m Rendezvous and Proximity Operations (RPO) using EO and infrared (IR) sensors on the deployable satellite (see Figure 1 ).The base station may comprise a modular host-vehicle interface based on, for example, the three variants described in Table 1 below.Table 1

[0019] The Staged and Integrated variants may be integrated on the ground with an adaptable interface to accommodate universal interfaces, such as Lockheed Martin’s Augmentation System Port Interface (ASPIN). The on-orbit upgrade version may use attachment mechanisms such as the Client Attachment System (CAS) available from Katalyst Space Technologies, LLC, a retrofit interface for unprepared client satellites that attaches to the launch adaptor ring on the client vehicle.

[0020] In accordance with various aspects of the present disclosure, the deployable satellites contemplated herein may have maneuverability (e.g., via cold gas) and range (e.g., monopropellant) to support a variety of mission sets withapproximately 160 m / s of total AK. This allows access to the entire GEO belt in under 24-hours and supports multiple RSO circumnavigation cycles during RPO to support tracking, characterizing, and identifying the RSO. The deployable satellites are capable of maneuvering to standoff ranges less than 100-meters during safe-assured RSO inspection. For inspection, the deployable satellites may employ an EO / IR sensors payload, packaged with edge-processing software. Pre-trained machine learning (ML) models may deliver pose estimation and feature extraction reports to derive RSO identity, intent, and capability.

[0021] The spacecraft systems contemplated herein may be platformagnostic, providing the ability to launch deployable satellites from many types of systems, including three variants (see Table 1 above). Spacecraft systems in accordance with the present disclosure are specifically designed to leverage these channels to accomplish affordable proliferation faster than any single method.

[0022] In accordance with the present disclosure, various methods for rapidly deployable and maneuverable satellites within a space domain are provided, which allow deploying at least one deployable satellite in response to a command to maneuver the at least one deployable satellite to a RSO target orbit to collect observations. In this regard, additional aspects of spacecraft systems follow.

[0023] For example, the spacecraft system may be in a staged orbit for performing rapid RPO around a RSO in response to a deployment command.

[0024] In accordance with various aspects, the base station comprises various components, including an SDA subsystem, a bus structure with embedded computational subsystems, power subsystems, and communications subsystems. The base station may also comprise any variety of electro-optical sensor payloads, infrared sensor payloads, radiofrequency sensor payloads, and LIDAR sensorpayloads to provide local situational awareness and far-field resident space object detection from a staging orbit.

[0025] Additionally, the base station may comprise an interface for attaching the base station to a host satellite such as described above or other applicable, now known or as yet unknown attachment interfaces. For example, the base station may comprise various modular mechanical, electrical, or thermal interfaces that are configured to attach to a satellite prior to launch during assembly or via a retrofit interface for attaching the base station to a satellite while on-orbit, via either a prepared or unprepared interface. Additionally, the base station may comprise one or more robotic interfaces for stowage and manipulation to enable retrieval and installation onto a host satellite by a satellite servicing vehicle.

[0026] In accordance with various aspects of the present disclosure, the base station may comprise an actuator to enable the deployment of the deployable satellites. For example, a spring-loaded actuator may be used to deploy the deployable satellites housed within the satellite deployment subsystem. Further, in accordance with various aspects of the present disclosure, the base station may be configured to allow each deployable satellite that has been deployed to later re-dock with the base station. Similarly, the base station may be configured to allow a satellite servicer vehicle to resupply the base station with new deployable satellites.

[0027] In accordance with various aspects, the base station comprises a satellite deployment subsystem containing at least one deployable satellite capable of carrying out at least one RPO missions. In accordance with various aspects, each deployable satellite may comprise a deployable unit subsystem comprising a bus structure with among others, embedded computational subsystems, power subsystems, and communications subsystems. In accordance with some aspects, forexample, the base station houses two 8U deployable satellites (see Figure 2). While stowed, the base station provides power and data to maintain deployment readiness. The deployment system may be rail-based and make up the structure of the base station. The avionics and bus structures for both the base station and deployable satellites may be provided by any conventional CubeSat component manufacturers and may include a variety of custom design features, such as cold gas propulsion systems and dispenser designs.

[0028] In accordance with various aspects of the present disclosure, each deployable satellite may comprise at least one of an electro-optical sensor payload, an infrared sensor payload, a radiofrequency sensor payload, and a LIDAR sensor payload. Additionally, in accordance with some aspects of the present disclosure, each deployable satellite may comprise additional components such as propellant systems, reaction wheels, control moment gyroscopes, or multi-thruster cold gas systems. In accordance with some aspects, the cold gas system may comprise an eight-thruster configuration to provide attitude-independent three degree of freedom translational control.

[0029] In accordance with various aspects of the present disclosure, the base station and / or the deployable satellite(s) may comprise various optical fiducials to support relative positioning of each deployable satellite. The optical fiducials may comprise at least one of active fiducials, such as LEDs, or passive fiducials, such as visual markings.

[0030] In accordance with various aspects of the present disclosure, the base station and the deployable satellites may communicate with each other. For example, the base station and the deployable satellites may communicate using an ultra-high frequency (UHF) link, optical inter-satellite link (OISL), or other suitablecommunication means.

[0031] In accordance with various aspects of the present disclosure, the base station may further comprise a guidance navigation and control (GNC) subsystem for controlling, among others, the propulsion, navigation and attitude control of the base station. In accordance with various aspects of the disclosure, the deployable unit subsystem runs the GNC subsystem control algorithms which comprise, among others, trajectory planning, perception and relative navigation, and control with configurable parameters to accomplish at least one of avoid operator- defined keep-out zones, and approach in a passively safe manner.

[0032] In accordance with various aspects of the present disclosure and in addition to the above, and with reference now to the diagrams of Figures 6 and 7, a spacecraft command and control system for a vehicle may further comprise an operator-interface that uses a generalized path planning algorithm based upon active satellite telemetry to identify optimal rendezvous and proximity operations around an RSO and generate necessary satellite commands. In this regard, the system may receive operator-configurable mission parameters and priorities for operations including, among others, an RSO state, an RSO form, a speed of mission completion, a fuel usage, required viewing angles, a relative position with respect to celestial bodies, a relative position with respect to the RSO, and a keep out zone.

[0033] In accordance with various aspects of the present disclosure, mission scheduling may be resolved through the sequencing of locally optimal trajectories pursuant to a mission goal which is optimized against an operator informed global objective function. Local maneuver optimization may be executed using model based predictions and heuristic assisted sampling. In this regard, heuristic assisted sampling may be within a multidimensional search space which addresses directionand magnitude of a maneuver and a time of flight. Furthermore, the heuristic assisted sampling may be based upon prioritization of exploration, exploitation, and a gradient of identified operator informed global objective function sample results.

[0034] In accordance with various aspects of the present disclosure, global optimization may be determined through a Markov Decision Process of various optimal local maneuvers that are constrained by operator informed boundary conditions for time and state of trajectory transitions. Optimal local maneuvers are determined by using model based predictions and heuristic assisted sampling which may be within a multidimensional search space addressing direction and magnitude of maneuver, and probability of transition to subsequent trajectory.

[0035] In accordance with various aspects of the present disclosure, the spacecraft command and control system may be used for autonomous guidance of the vehicle to any of a target vehicle, an RPO, effects delivery, and egress or transition to additional target vehicles. The RPO may be a natural motion circumnavigation or a forced motion circumnavigation. The effects delivery may comprise any of inspection, sensing, jamming, anti-jamming, occluding, and interception.

[0036] In accordance with various aspects of the present disclosure, an on-orbit computation may be determined by pre-defined local optimization frameworks and configurable global optimization objectives about any of a unique approach constraint, a target vehicle state, a target vehicle form, a target vehicle point of interest, and / or a keep out zone.

[0037] In accordance with various aspects of the present disclosure, the operator-interface is capable of displaying user-defined and entered parameters and priorities in a graphical user-interface for the operator-configurable parameters,and after entering the user-defined parameters and priorities, the operator is presented with a plurality of candidate trajectory solutions and a comparison of each candidate trajectory solution against the user-defined parameters and priorities to enable the operator to make an informed selection of a specific candidate trajectory solution.

[0038] The base station may include three optics to provide local awareness at the staging location or when integrated on a satellite. Each deployable satellite includes a hybrid propulsion architecture using a chemical monopropellant and a cold gas system to maximize response and mobility. The 2U COTS monopropellant system produces 150 m / s of AK at high thrust (0.5 N) to provide tactical mobility, enabling the deployable satellite to quickly travel along the GEO belt and to safely transition to a graveyard orbit after completion of its mission in compliance with standard satellite end-of-life (EOL) disposal practices. The system is 2 -axis thrust vectoring, assisting in deployable agility, and uses LMP-103S, a high- performance green propellant that allows for safe operation near optical systems and proximate operations to the base station, client vehicle, and target RSO. The nitrogen cold gas Reaction Control System (RCS) provides an additional approximately 13 m / s of AK for close-in RPO. The eight-thruster configuration enables spacecraft systems in accordance with the present disclosure to provide attitude-independent 3 degree- of-freedom (DOF) translational control and a COTS reaction wheel module provides the rotational control to enable agile maneuverability needed for close-proximity RPO and, in future iterations, support docking (RPOD) mission sets, deployable satellites contain a COTS EO / IR sensor payload for RSO inspection.

[0039] The GNC control algorithms running onboard the deployable satellites are designed to provide responsive RPO inspection capabilities of unknown assets. The deployable satellites approach the target RSOs avoiding operator definedkeep out zones on a passively safe safety-ellipses to prevent unintended collisions. Machine learning (ML) is used for relative pose estimation of the target RSO through convolutional neural networks (CNNs). The three major GNC elements are (1 ) trajectory planning, (2) perception and relative navigation, and (3) control. Each element presents unique considerations across the three reference mission stages: (1 ) rendezvous, (2) approach / ingress, and (3) proximity operations. If required, rendezvous covers the orbital transfer to the vicinity of the target RSO. Ingress includes the approach to the target RSO, defined as the start of relative orbital dynamics being used by the onboard controller. Once at the target RSO, the deployable satellite begins proximity operations to maintain relative position and attitude and collect key characterization data. This process is reversed for egress.

[0040] The deployable satellite monopropellant and cold gas system is designed for all three mission stages, demanding precise actuation systems, long range, and motion planning that meets safety requirements. The orbital positioning thruster provides a minimum of 150 m / s of AK at 0.5 N with a sufficient reserve for end-of-life disposal procedures. Eight (8) 0.1 N R-134a cold gas thrusters provide attitude-independent translational control with 13 m / s of AK. This configuration decouples maneuvers from attitude constraints to meet mission needs such as payload, ground communication, and solar pointing requirements to enable complex RPOD maneuvers. Figure 4 illustrates and summarizes integrated multi-parameter systems engineering optimization to meet these requirements.

[0041] The spacecraft systems may have multiple layers of safety built in to ensure safe RPO maneuvers nearby host satellites and RSOs. The base station includes light emitting diodes (LEDs) and markings for optical fiducials visible to the deployable satellite optics for redundant methods of relative positioning forautonomous safe operation. A local ultra-high frequency (UHF) link provides communication between the base station and deployable satellites for cooperative state estimation.

[0042] The spacecraft systems may support the entire SDA process across detection, tracking, characterization, and identification. The base station performs passive local awareness for RSO detection and tracking via a triaxial optical assembly (FOV 20°, 71 arcsec / pixel spatial resolution), nominally positioned to point in the positive velocity, negative velocity, and anti-nadir directions for maximum coverage. Detection range is a function of the angle between the sun, target, and observer. For example, with reference to Figure 3, analysis shows at a sun angle of 45° the base station detects a Boeing 702HP satellite bus and a 16U CubeSat at 2,000 km and 40 km, respectively.Benefits and Advantages

[0043] Commercial GEO satellite owner / operators would be very interested in spacecraft systems in accordance with the present disclosure. While commercial GEO operators need to have revenue assurance for their enterprise valuation, there are currently no responsive and inexpensive ways to obtain the information to support their needs. At the fleet level, commercial operators desire to create a GEO belt awareness data stream so that transient characteristics or anomalous events can be flagged early, and actions taken, to preserve the life of the satellites.

[0044] Commercial operators will find spacecraft systems in accordance with the present disclosure to be valuable to their insurance providers so that in the event there is a deployment of new technologies or an out-of-class anomaly, the ability to diagnose root cause in a timely fashion creates a new avenue for claim resolution. Historically, GEO operators have had no way to discover “What is preventing the arraydeployment?", or "Why are the solar arrays degrading more rapidly than predicted?" Spacecraft systems in accordance with the present disclosure offer an affordable and responsive path to diagnose anomalies and return to profitable operations. We believe this is a solid business with today’s over 560 and tomorrow’s growing number of GEO satellites.

[0045] Operators can also host spacecraft systems in accordance with the present disclosure on their platforms as a reseller of obtained SDA data into marketplaces such as the Global Data Marketplace.

[0046] Spacecraft systems in accordance with the present disclosure provide free-flying inspections aligning with key objectives for civil space application such as future NASA applications for human space flight and larger scale discovery class missions. Spacecraft systems in accordance with the present disclosure can be attached to, or staged around, HVAs such as the Artemis Lunar Gateway to provide monitoring, inspection, and anomaly resolution services. NASA has sought advanced robotic free flyers for this purpose inside the International Space Station such as Astrobee.

[0047] Other solutions are being developed for Low-Earth Orbit (LEO) to address the active debris removal (ADR) market, while Katalyst aims to offer services in GEO and other high-altitude orbits. Key differentiators include:• Deployment Versatility - Spacecraft systems in accordance with the present disclosure can be deployed as a hosted payload on a HVA (pre- or post-launch) or as a stand-alone asset positioned at strategic orbital locations. This lowers the barrier for such spacecraft systems to proliferate and enhances the likelihood that the systems will be on-target in much less than 24-hours. Each new system becomes part of anetwork of heterogeneous, responsive on-orbit SDA assets.• Multi-Agent Mission Management - Once multiple spacecraft systems in accordance with the present disclosure systems are on-orbit, a cooperative architecture emerges that enables enhanced mission-level performance via cooperative, multi-agent mission execution managed by distributed networking software. This has benefits including faster RSO identification and response, and improved resiliency to attrition compared with tasking individual SDA assets.

[0048] As reguired, detailed aspects of the present disclosed subject matter are disclosed herein. However, it is to be understood that the disclosed aspects are merely exemplary of the disclosed subject matter, which may be embodied in various forms. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present disclosed subject matter in virtually any appropriately detailed structure.

[0049] Likewise, numerous characteristics and advantages have been set forth in the preceding description, including various alternatives together with details of the structure and function of the devices and / or methods. The disclosure is intended as illustrative only and as such is not intended to be exhaustive. It will be evident to those skilled in the art that various modifications may be made, especially in matters of composition, ingredients, structure, materials, elements, components, shape, size and arrangement of parts including combinations within the principles of the invention, to the full extent indicated by the broad, general meaning of the terms in which the appended claims are expressed. To the extent that these various modifications do not depart from the spirit and scope of the appended claims, they areintended to be encompassed therein.

Claims

CLAIMSWe claim:

1. A spacecraft command and control system for a vehicle comprising an operator-interface that uses a generalized path planning algorithm based upon active satellite telemetry to identify satellite commands for optimal rendezvous and proximity operations around a resident space object (RSO), wherein the system receives operator-configurable mission parameters and priorities for operations including at least one of an RSO state, an RSO form, a speed of mission completion, a fuel usage, required viewing angles, a relative position with respect to celestial bodies, a relative position with respect to the RSO, and a keep out zone.

2. The spacecraft command and control system for a vehicle of claim 1 , wherein mission scheduling is resolved through sequencing of locally optimal trajectories pursuant to a mission goal optimized against an operator-informed global objective function.

3. The spacecraft command and control system for a vehicle of claim 2, wherein local maneuver optimization is executed using model-based predictions and heuristic assisted sampling.

4. The spacecraft command and control system for a vehicle of claim 3, wherein the heuristic assisted sampling is within a multidimensional search space addressing direction and magnitude of a maneuver and a time of flight.

5. The spacecraft command and control system for a vehicle of claim 3, wherein the heuristic assisted sampling is based upon prioritization of exploration, exploitation, and a gradient of identified operator informed global objective function sample results.

6. The spacecraft command and control system for a vehicle of claim 1 , wherein a global optimization is determined through a Markov Decision Process of optimal local maneuvers constrained by operator informed boundary conditions for time and state of trajectory transitions.

7. The spacecraft command and control system for a vehicle of claim 6, wherein the optimal local maneuvers are determined by using model based predictions and heuristic assisted sampling.

8. The spacecraft command and control system for a vehicle of claim 7, wherein the heuristic assisted sampling is within a multidimensional search space addressing direction and magnitude of maneuver, and probability of transition to subsequent trajectory.

9. The spacecraft command and control system for a vehicle of claim 7, wherein the heuristic assisted sampling is based upon prioritization of exploration, exploitation, and a gradient of identified local objective functions sample results.

10. The spacecraft command and control system for a vehicle of claim 1 , wherein the system is utilized for autonomous guidance of the vehicle to at least one of:a target vehicle, an RPO, effects delivery, and egress or transition to additional target vehicles.11 . The spacecraft command and control system for a vehicle of claim 10, wherein the RPO is a natural motion circumnavigation.

12. The spacecraft command and control system for a vehicle of claim 10, wherein the RPO is a forced motion circumnavigation.

13. The spacecraft command and control system for a vehicle of claim 10, wherein the effects delivery comprises at least one of inspection, sensing, jamming, antijamming, occluding, and interception.

14. The spacecraft command and control system for a vehicle of claim 1 , wherein an on-orbit computation is determined by pre-defined local optimization frameworks and configurable global optimization objectives about at least one of: a unique approach constraint, a target vehicle state, a target vehicle form, a target vehicle point of interest, and a keep out zone.

15. The spacecraft command and control system for a vehicle of claim 1 , wherein the operator-interface displays user-defined parameters and priorities in a graphical user-interface for the operator-configurable parameters.

16. The spacecraft command and control system for a vehicle of claim 15, wherein after entering the user-defined parameters and priorities, an operator ispresented with a plurality of candidate trajectory solutions and a comparison of each candidate trajectory solution against the user-defined parameters and priorities to enable the operator to make an informed selection of a specific candidate trajectory solution.

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