System and method enabling accelerated remote interface validation and space platform resource optimization

Abstract

A system is designed for accelerated validation of client hardware intended for integration with space platforms, optimizing resource usage. The system includes a client system, server device, and communication network for bi-directional data exchange. The client system includes the client hardware to be validated, a data protocol adapter to translate between protocols, and a web browser for transmitting and receiving data. The server device features a web server for data transmission, a database for storing hardware and validation data, an application server for running optimization software, a platform emulator to simulate space platform environments, and a file server to store logs and reports generated during validation.

Description

SYSTEM AND METHOD ENABLING ACCELERATED REMOTE INTERFACEVALIDATION AND SPACE PLATFORM RESOURCE OPTIMIZATIONCROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application claims the benefit of U.S. provisional application Serial No. 63 / 540,104 filed September 24, 2023, the disclosure of which is hereby incorporated in its entirety by reference herein.TECHNICAL FIELD

[0002] In at least one aspect, the following relates generally to systems and methods for remote (such as pre-launch or on-orbit pre-connection) integration and validation of a component or payload with a space platform and auto-configuration and optimization of the space platform’s resources to host multiple, concurrent components, payloads (cameras, sensors, processors, memory devices, etc.), manufacturing devices, and robotic elements and manipulation systems.BACKGROUND

[0003] The field of “on-orbit servicing” is growing due to new technology for after-launch modifications and manipulations coupled with lower launch costs from Earth. Today, a satellite or platform is no longer restricted to a certain period of time in orbit after launch but can be re-used, reserviced, or re-supplied via new technology and capabilities. This new capability is opening up the ability for any person, company, organization, or country to begin to evaluate and operate in space through on-orbit test and validation on a short or long-duration platform (such as the Arkisys Port) designed for that purpose.

[0004] Users, developers, experimenters, and vendors wish to evaluate their devices in space as quickly and cheaply as possible prior to the full-scale creation of their own satellites. In the past, this required complicated interfaces, custom designs to connect to a proprietary interface to launch and / or to fly in orbit, and an exceptionally long process to get into a nominal launch cycle on a dedicated platform as a ride-share or hosted pay load on another company’ s platform. The current stateof the art relies heavily on complying with interface requirements documents, which are lengthy and may contain errors. The integration and test cycle is conducted late in the project and often results in costly schedule delays when inconsistencies between the documented interface and the actual space platform are identified. Unmanned space platforms will require much earlier validation using a system that provides both the hardware developer and the space platform provider with simultaneous access to the real-time test environment, making both parties equal partners in the process.

[0005] One platform on which a developer may wish to have their hardware hosted is the Port provided by Arkisys, Inc. The Port is a long-duration stable platform able to operate within any orbit and has multiple berths (or mechanical / electrical interfaces) for components, pay loads, experiments, manufacturing elements, and active devices to connect to it. The Port is one example of a space platform that not only includes multiple mechanical interfaces but is also configured to generate power, communicate bi-directionally with ground stations, station-keep, and orient itself in three axes, and reject waste heat through radiator panels. Its power system can generate, store, and distribute power to each of the mechanical interfaces on board as well as to its own internal systems. The mechanical interface used to attach payloads to the Port is also capable of bi-directional data and power transfer, as well as thermal conduction, eliminating the need for additional interfaces. On the Port, mechanical interfaces include a data interface for coupling on one side to a hardware data interface and on the other side to a data protocol adapter and translator (referred to as an “Applique”), which couples to the network on board the Port.

[0006] Hardware hosted by a Port does not need to be designed with separate solar arrays, batteries, or communications systems in mind, nor do they need to be packaged into arbitrary sizes or volumes of a spacecraft before launch. Pay loads or components or elements on the Port Modules are attached to interfaces (or berths) located on the exterior for easy access by a robotic arm, enabling larger volumes and masses than traditional shared bus providers. This allows developers to focus more on developing and evaluating their payloads rather than developing and integrating all the support hardware to power the device, evaluate it, and transmit the data to the ground.

[0007] Additionally, for payloads that do not have their own enclosure or which do not need a specific enclosure, a standard container that encapsulates the payload is provided by Arkisys on The Port, referred to as “Bosuns Lockers.” These generic enclosures allow hardware developers to encapsulate their hardware if it is not suited for direct exposure to the environment or it does not have suitable structural attachment points to dock to a berthing interface.

[0008] Each Port built on orbit is designed to be fully modular. Every Port is made up of Port Modules, and each Port Module can connect to another Port Module to form a larger structure. A Port is one or more Port Modules in any orbit. As this aggregation occurs, the modules synchronize to share their computing power and resources such that they can function as a single entity acting like a single space platform, sharing duties such as momentum management and station-keeping. The solar arrays and reaction control system modules on board are also modular, such that when any reconfiguration happens, these modules can be moved to a new location on The Port Modules by the robotic arm, maintaining sun-pointing for maximal power generation and RCS control with a new center of gravity and / or moment of inertia.

[0009] Currently, developers of hardware who wish to have that hardware hosted by a space platform during a desired on-orbit window engage in multiple onerous tasks to validate the hardware before launch. These include confirming that a space platform has adequate resources and space available during the desired on-orbit window to host the hardware and to permit the hardware to complete its mission parameters, pre-integration, and then pre-launch hardware testing to ensure mechanical and interface compatibility with the space platform and arranging for launching the hardware. Initially, the developer designs the hardware to conduct the desired mission, and based on that initial design, the number of appropriate space platforms capable of hosting the device is reduced. Once the developer arranges to be hosted on a space platform, they must still validate that the hardware they are developing can connect and provide command and telemetry to the platform. Typically, this can require two or three trips to the space platform provider’s facilities to get it right. Also, the flight hardware must be sent to the platform provider to be fit-checked at least once and then sent again to be integrated, where it gets evaluated again. Then, the flight hardware goes an environmental testwith the hosting platform. If something goes wrong with this test, the developer’s hardware must be de-integrated from the platform and fixed, whereupon the test process starts. Developers would appreciate a system and method to reduce the time and effort required to complete this process.SUMMARY

[0010] In at least one aspect, a system for accelerated remote interface validation and space platform resource optimization is provided. The system includes a client system, a server device, and a communication network configured to facilitate bi-directional data exchange between the client system and the server device. The client system includes client hardware to be validated. The client hardware is configured for eventual integration with a space platform. The client system further includes a data protocol adapter and translator configured to convert data from a protocol utilized by the client hardware to a platform-native protocol. The client system further includes a client device with a web browser for transmitting data related to the client hardware to the server device and receiving telemetry data from the server device. The server device includes a web server configured to interact with the client device to facilitate data transmission and a database server for storing data related to the client hardware, the space platform, and a validation process. The server device can further include an application server running optimization and planning software for validating the compatibility of the client hardware with the space platform. The server device can further include a platform emulator configured to simulate a space platform's environment (including its resources and subsystems) to validate compatibility of the client hardware. The server device can further include a file server for storing logs, reports, and other data generated during the validation process.

[0011] In another aspect, the client system is bi-directionally coupled to the communication network utilizing a network data protocol for transferring data via a client network interface with the client hardware configured to receive commands and send telemetry data utilizing a hardware data protocol.

[0012] In another aspect, a device and method for validating developer client hardware before launch into space is provided. The device and method operate through rapid integration with a dataprotocol adapter and translator (applique), translating any protocol into Port-native protocols through Streamlined Integration Exportable technology to onboard a developer’s hardware. A unique onboarding process is created to allow for “on the ground” testing in a company or organization’s home office or location with the proposed new technology device before it is ready to launch, with a provided set of physical and virtual interfaces (berth and applique) that allows it to be connected to a Port digital twin and pre-validated, to enable its launch to orbit and test in less time than is currently possible, on the order of days instead of months. Advantageously, developers do not need to collocate with the platform provider during integration. This facilitates fast, efficient, and safe integration of a developer’s hardware onto a space platform while simultaneously optimizing the allocation of the space platform’s resources. This method, known as ‘onboarding’, is conducted in the early stages of the hardware development cycle, thus allowing the developer more time to identify and resolve design and interface issues and for the space platform provider to be able to assign a location on the platform to the hardware that will fully support the developer’ s mission obj ectives into a long duration platform (as example The Arkisys Port) in space.

[0013] In another aspect, a server device, referred to as the "HarborMaster," hosts multiple components that can optionally be implemented in software, including a web server, database server, application server, and file server, which collectively work with other system components to enable remote validation of the interface between a developer's hardware and the space platform, as well as automatic optimization of the platform's resources. The HarborMaster includes a web server that manages the content and format of the developer's web portal. Through this portal, developers can create accounts, input specifications for their hardware (such as dimensions, mass, power, operating temperature, commands and telemetry, data protocol, and interfaces, etc.), and define their mission requirements (such as time of arrival, pointing accuracy, untethered operations, ground communications contact frequency, etc.). Once the developer submits their data via the portal, it is securely stored in the HarborMaster's database. This database also contains information about the space platform's configuration, resources, operating environment, and other client requests for hosting services. A universal data protocol adapter and translator (an example of which is known as the “Applique”) is a device consisting of a microcontroller or microprocessor, firmware, andmultiple connector types for transmitting and receiving data between the developer’s hardware and the space platform emulator.

[0014] In another aspect, the space platform emulator (e.g., the “Digital Twin”) includes a software program and web interface executing on one or more computing devices. The software program includes digital representations of the on-orbit functionality of the space platform’s resources and subsystems (e.g., power and thermal control systems, onboard data processing and distribution, command and data handling, attitude determination, and control), operating environment (orbit and rotational dynamics, atmospheric drag, magnetic field, aerodynamic torques) and disturbances created during docking and robotic manipulator operations. The space platform’s flight software is derived from the same models underlying the platform emulator (e.g., the Digital Twin).

[0015] In another aspect, a method for integrating and testing client hardware prior to rendezvous with a space platform. This method involves validating the client hardware's operation using a platform emulator that simulates the space platform while in orbit. The method includes the steps of: providing a data protocol adapter and translator to a developer of client hardware; processing command and telemetry data generated by the client hardware through the data protocol adapter and translator from any protocol to Ethernet; providing a physical berth interface the developer of the client hardware to be coupled to the data protocol adapter and translator and the client hardware to validate that the client hardware meets the interface requirements of the space platform, prior to rendezvous of the client hardware with the space platform; and validating the operation of the client hardware that is not co-located with the platform emulator on the ground through Ethernet-based control.

[0016] In another aspect, a method for integrating and testing client hardware before its rendezvous and connection with a space platform is provided. The method includes a step of providing a hardware developer with a data protocol adapter and translator configured to process command and telemetry data generated by the client hardware and convert data from any data protocol to Ethernet. A physical berth interface is provided to the hardware developer. The physicalberth interface is configured to connect the data protocol adapter and translator to the client hardware. The method also includes a step of validating operation of the client hardware with a platform emulator that simulates the space platform in orbit. Finally, it is ensured that the client hardware meets interface requirements of the space platform prior to rendezvous and connection with the space platform.

[0017] In another aspect, the disclosed system and method provide a ground-based Internet- accessible display to the hardware developer for real-time validation of the device on the space platform via a data protocol adapter and translator having an Internet connection with a platform emulator, eliminating the need for co-location of the client hardware with the space platform.

[0018] The foregoing summary is illustrative only and is not intended to be in any way limiting. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description.BRIEF DESCRIPTION OF THE DRAWINGS

[0019] For a further understanding of the nature, objects, and advantages of the present disclosure, reference should be made to the following detailed description, read in conjunction with the following drawings, wherein like reference numerals denote like elements and wherein:

[0020] For a more complete understanding of the present invention and the advantages thereof, reference is now made to the following description taken in connection with the accompanying drawings in which:

[0021] FIGURE 1 is a block diagram of a system enabling accelerated client hardware interface validation and space platform resource optimization with environmental matter shown in dotted lines;

[0022] FIGURE 2 is a block diagram of a single standalone computer implementation running web server software that communicates with the database server to store and retrieve data specified by the developer and that communicates with the file server to store and retrieve files generated from the application server running optimization software and a space platform emulator and that communicates with the space platform emulator to send and receive data during interface validation testing with the developer’s hardware;

[0023] FIGURE 3 is a schematic representation of an overview of data flow originating with inputs from the customer, vendor, and public repositories that are collected in a database which is queried by software programs to generate actionable information for the platform operator and the developers of the hardware to be attached to the platform;

[0024] FIGURE 4 is an illustrative example screenshot of a data entry graphical user interface displayed on a client device generated by the HarborMaster of a web server for client data entry;

[0025] FIGURE 5 is an illustrative example screenshot of a service selection graphical user interface (GUI) screen displayed on a client device generated by a web server and a query widget generated by the web server in response to the selection of one option provided on the graphical user interface screen;

[0026] FIGURE 6 is a diagram representing data entry via the GUI illustrated in Figure 4 is processed by a HarborMaster web server, database server, and optimization software programs interoperating to generate information displayed on ta graphical user interface screen located on the client device;

[0027] FIGURE 7 is an example of the components of the HarborMaster Agent resource optimization and planning software and how the space platform operational data is aggregated with the hardware developer’s input from the web interface to compute (as an example) scheduling options on the server;

[0028] FIGURE 8 is a diagram representing illustrative examples of internal functions of the HarborMaster Agent, which, as an example, combines external and environmental data about the spacecraft and pay loads and aggregates this with user inputs to feed into the systems analysis tools for end-to-end simulations of a maneuver or scenario using the space platform emulator;

[0029] FIGURE 9 is a flow diagram of the initialization of data parameters generated in response to entries into the query widget of Fig. 5 into a Digital Twin of the platform emulator;

[0030] FIGURE 10 is a block model of examples of subsystems embodied in a Digital Twin of the platform emulator;

[0031] FIGURE 11A is a block diagram of a communications overview between the platform emulator and hardware components, the web interface on the client device and sensors, manipulator and docking mechanism components during interface validation and testing;

[0032] FIGURES 11B and 11C illustrate the functions of the interface validation system and process are closely tied to the functions of the on-orbit space platform, thereby providing the hardware developer with a high-fidelity system that is used to validate their interfaces early in their development cycle;

[0033] FIGURE 12 is a top view of a data protocol adapter and translator (e.g., an Applique) coupled to a hardware data interface and an Ethernet cable;

[0034] FIGURE 13 is a flow diagram of a command path from the developer’s web portal to the web server to the platform emulator, which forwards the command over the Internet to the data protocol adapter and translator to the developer’s hardware; and,

[0035] FIGURE 14 is a flow diagram of a telemetry path from the hardware through the data protocol adapter and translator to the platform emulator (Digital Twin) to the web server that serves the telemetry to the developer’s web browser via the Internet.

[0036] FIGURE 15 is a flowchart of a method for integrating and testing hardware before its rendezvous and connection with a space platform.DETAILED DESCRIPTION

[0037] Reference will now be made in detail to presently preferred embodiments and methods of the present invention, which constitute the best modes of practicing the invention presently known to the inventors. The Figures are not necessarily to scale. However, it is to be understood that the disclosed embodiments are merely exemplary of the invention that may be embodied in various and alternative forms. Therefore, specific details disclosed herein are not to be interpreted as limiting but merely as a representative basis for any aspect of the invention and / or as a representative basis for teaching one skilled in the art to variously employ the present invention.

[0038] It is also to be understood that this invention is not limited to the specific embodiments and methods described below, as specific components and / or conditions may, of course, vary. Furthermore, the terminology used herein is used only for the purpose of describing particular embodiments of the present invention and is not intended to be limiting in any way.

[0039] It must also be noted that, as used in the specification and the appended claims, the singular form "a," "an," and "the" comprise plural referents unless the context clearly indicates otherwise. For example, reference to a component in the singular is intended to comprise a plurality of components.

[0040] The term “comprising” is synonymous with “including,” “having,” “containing,” or “characterized by.” These terms are inclusive and open-ended and do not exclude additional, unrecited elements or method steps.

[0041] The phrase “consisting of” excludes any element, step, or ingredient not specified in the claim. When this phrase appears in a clause of the body of a claim, rather than immediately following the preamble, it limits only the element set forth in that clause; other elements are not excluded from the claim as a whole.

[0042] The phrase “consisting essentially of” limits the scope of a claim to the specified materials or steps, plus those that do not materially affect the basic and novel characteristic(s) of the claimed subject matter.

[0043] With respect to the terms “comprising,” “consisting of,” and “consisting essentially of,” where one of these three terms is used herein, the presently disclosed and claimed subject matter can include the use of either of the other two terms.

[0044] It should also be appreciated that integer ranges explicitly include all intervening integers. For example, the integer range 1-10 explicitly includes 1, 2, 3, 4, 5, 6, 7, 8, 9, and 10. Similarly, the range 1 to 100 includes 1, 2, 3, 4. . . . 97, 98, 99, 100. Similarly, when any range is called for, intervening numbers that are increments of the difference between the upper limit and the lower limit divided by 10 can be taken as alternative upper or lower limits. For example, if the range is 1.1. to 2.1 the following numbers 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9, and 2.0 can be selected as lower or upper limits.

[0045] When referring to a numerical quantity, in a refinement, the term “less than” includes a lower non-included limit that is 5 percent of the number indicated after “less than.” A lower nonincludes limit means that the numerical quantity being described is greater than the value indicated as a lower non-included limited. For example, “less than 20” includes a lower non-included limit of 1 in a refinement. Therefore, this refinement of “less than 20” includes a range between 1 and 20. In another refinement, the term “less than” includes a lower non-included limit that is, in increasing order of preference, 20 percent, 10 percent, 5 percent, 1 percent, or 0 percent of the number indicated after “less than.”

[0046] With respect to electrical devices, the term “connected to” means that the electrical components referred to as connected to are in electrical communication. In a refinement, “connected to” means that the electrical components referred to as connected to are directly wired to each other. In another refinement, “connected to” means that the electrical components communicate wirelessly or by a combination of wired and wirelessly connected components. In another refinement,“connected to” means that one or more additional electrical components are interposed between the electrical components referred to as connected to with an electrical signal from an originating component being processed (e.g., filtered, amplified, modulated, rectified, attenuated, summed, subtracted, etc.) before being received to the component connected thereto.

[0047] The term “electrical communication” means that an electrical signal is either directly or indirectly sent from an originating electronic device to a receiving electrical device. Indirect electrical communication can involve processing of the electrical signal, including but not limited to, filtering of the signal, amplification of the signal, rectification of the signal, modulation of the signal, attenuation of the signal, adding of the signal with another signal, subtracting the signal from another signal, subtracting another signal from the signal, and the like. Electrical communication can be accomplished with wired components, wirelessly connected components, or a combination thereof.

[0048] The term “one or more” means “at least one” and the term “at least one” means “one or more.” The terms “one or more” and “at least one” include “plurality” as a subset.

[0049] The term “substantially,” “generally,” or “about” may be used herein to describe disclosed or claimed embodiments. The term “substantially” may modify a value or relative characteristic disclosed or claimed in the present disclosure. In such instances, “substantially” may signify that the value or relative characteristic it modifies is within ± 0%, 0.1%, 0.5%, 1%, 2%, 3%, 4%, 5% or 10% of the value or relative characteristic.

[0050] The term “electronic component” refers is any physical entity in an electronic device or system used to affect electron states, electron flow, or the electric fields associated with the electrons. Examples of electronic components include, but are not limited to, capacitors, inductors, resistors, thyristors, diodes, transistors, etc. Electronic components can be passive or active.

[0051] The term “electronic device” or “system” refers to a physical entity formed from one or more electronic components to perform a predetermined function on an electrical signal.

[0052] It should be appreciated that in any figures for electronic devices, a series of electronic components connected by lines (e.g., wires) indicates that such electronic components are in electrical communication with each other. Moreover, when lines directed connect one electronic component to another, these electronic components can be connected to each other as defined above.

[0053] The processes, methods, or algorithms disclosed herein can be deliverable to / implemented by a processing device, controller, or computer, which can include any existing programmable electronic control unit or dedicated electronic control unit. Similarly, the processes, methods, or algorithms can be stored as data and instructions executable by a controller or computer in many forms including, but not limited to, information permanently stored on non-writable storage media such as ROM devices and information alterably stored on writeable storage media such as floppy disks, magnetic tapes, CDs, RAM devices, and other magnetic and optical media. The processes, methods, or algorithms can also be implemented in a software executable object. Alternatively, the processes, methods, or algorithms can be embodied in whole or in part using suitable hardware components, such as Application Specific Integrated Circuits (ASICs), Field- Programmable Gate Arrays (FPGAs), state machines, controllers, or other hardware components or devices, or a combination of hardware, software and firmware components.

[0054] Abbreviations:

[0055] "CG" means center of gravity.

[0056] "EO" means ethylene oxide.

[0057] "EPS" means electrical power system.

[0058] "GNC" means guidance, navigation, and control.

[0059] "GUI" means graphical user interface.

[0060] "IP" means internet protocol.

[0061] "I&T" means integration and testing.

[0062] "LV" means launch vehicle.

[0063] "MCU" means microcontroller unit.

[0064] "MOI" means moment of inertia.

[0065] "OTV" means orbital transfer vehicle.

[0066] "POSITIVE" means platform operating system for integrated telemetry and instrumentation, validation, and evaluation.

[0067] "RCS" means reaction control system.

[0068] "SQL" means structured query language.

[0069] "SW" means software.

[0070] "UDP" means user datagram protocol.

[0071] "VPN" means virtual private network.

[0072] "XML" means extensible markup language.

[0073] As shown in Figure 1 , a system for integrating a client’s hardware into a space platform is provided. System 10 interacts with client system 12 enabling accelerated validation of client hardware 14 in client system 12 and space platform resource optimization. Client system 12 includes client hardware 14 to be validated, data protocol adapter and translator 18, client device 20 hosting the web browser 22, physical interface 24 (i.e., connector 24), and internal router 26, as described below in more detail. Client hardware 14 is configured for eventual integration with a space platform. Data protocol adapter and translator 18 is configured to convert data from a protocol utilized by the client hardware 14 to a platform-native protocol. Client device 20 includes a web browser 22 fortransmitting data related to the client hardware 14 to the server device and receiving telemetry data from the server device 30.

[0074] System 10 also includes a server device 30 that hosts a suite of interoperating software 32. In a refinement, the server device 30 is configured to execute a server application and is in bidirectional communication with a server network interface coupled to the communication network. Server device 30 includes subsystem 34 for executing the suite of interoperating software 32. These components of the suite of interoperating software 32 include a web server 36, a database server 38, an application server 40 running optimization and planning software 42 (e.g., HarborMaster Agent’s platform configuration software), a file server 44, and a space platform emulator 46. Web server 36 is configured to interact with the client device 20 to facilitate data transmission. In a refinement, the database server 38 is configured to be in bi-directional communication with the web server 36. Similarly, the web server 36 is configured to be in bi-directional communication with the application server 40. The web server 36 can be further configured to generate portal pages for transfer over the communication network (see below) for display by the web browser 22 on the client device, thereby permitting a developer to input data to and receive data from the web server. Advantageously, web server 36 is configured to interact with the client device 20 to facilitate data transmission. The web server 36 can be further configured to provide a graphical user interface (GUI) accessible via the client device for a developer to input hardware specifications and mission requirements and display telemetry and command data from the hardware during the validation process, enabling real-time monitoring and adjustment. Examples of specifications for the hardware include dimensions and mass properties, power requirements, operating temperature requirements, and commands and telemetry requirements.

[0075] As set forth below in more detail, the data protocol adapter and translator 18 can be configured for bi-directional communication with the client hardware 14 utilizing a hardware data protocol and configured for bi-directional communication through a network interface and over the communication network to the web server 36 utilizing a network data protocol. The data protocol adapter and translator 18 can be further configured to translate data received in the hardware dataprotocol from the client hardware into data for transmitting in the network data protocol for transmitting to the web server 36 and to translate data received in network data protocol from the web server 36 into data for transmitting in the hardware data protocol for transmitting to the client hardware. In a refinement, data protocol adapter and translator 18 are further configured to encrypt and decrypt data transmitted between the client system and the server device and to validate data packet integrity before forwarding them to the client hardware or the server device.

[0076] In another aspect, the database server 38 can be further configured to receive and store data entered in a web portal page and to send data to the web portal page and other server applications. Advantageously, the application server 40 is configured to host software programs, scripts, and executables that receive data from the database server and act upon the data to optimize resources of the space platform, generate cost and schedule reports, and initialize a platform emulator based upon aggregated properties. Typically, the application server 40 runs optimization and planning software to validate the compatibility of the hardware with the space platform. In some variations, the platform emulator 46 is configured in bi-directional communication with a web interface and the server application (and / or the application server) with a network data protocol. The platform emulator 46 can be configured to simulate the space platform, including on-orbit functionality of a space platform’s resources and subsystems (e.g., a navigational subsystem and a control subsystem) to validate compatibility of the hardware; . The communication network can the Internet, a server network interface can be a router, a client network interface can be a router, and the network data protocol can be Ethernet. In a refinement, platform emulator 46 includes a digital twin of the space platform. In this regard, the digital twin, includes software representations for subsystems of the space platform, including power generation, thermal control, data processing, and attitude control. In a further refinement, a simulation of an operating environment of the space platform includes orbital dynamics, atmospheric drag, and magnetic fields to validate client hardware functionality in a realistic orbital scenario. In a refinement, outputs from a platform emulator’s simulation are utilized to automatically optimize allocation of a space platform's resources to support multiple concurrent hardware components or payloads. File server 44 is used for storing logs, reports, and other data generated during the validation process.

[0077] In another aspect, system 10 and its associated methods are described in the context of an automated space platform designed to host various types of hardware. This hardware can be docked to a berth, handled by a robotic manipulator, stored in a compartment attached to the space platform, or otherwise connected. However, the invention is also applicable to manned space platforms. The term "hardware," as used here, includes a wide range of items the space platform might host. This includes payloads, components like sensors and actuators that can be integrated into the platform, docking mechanisms for orbital transfer vehicles, and components used in assembly, service, or manufacturing on the platform. Additionally, the term "hardware" covers payloads, vehicles, containers, and their sub-components that developers may wish to dock or operationally connect to a space platform. An illustrative example of an automated space platform is The Port, developed by Arkisys, Inc. and modular components thereof. Scalable platforms are generated utilizing multiple ports and components and / or other hardware docked or coupled thereto. The Port, its modules, and several currently envisioned scalable configurations are described briefly in the Background and Summary above and incorporated herein by reference.

[0078] In another aspect, the disclosed system and method primarily focus on remote client hardware interface validation and space platform optimization because the current approach involves developing hardware on Earth, launching it into space, and then having it operate independently or interact with an existing space platform. However, in the future, hardware may be developed in space or on other extraterrestrial bodies and intended to interact with a space platform. Therefore, unless explicitly stated otherwise, the term "pre-launch," as used here in relation to interface validation and space platform optimization, refers to the validation and optimization processes before the hardware is hosted by the space platform, regardless of whether the hardware is developed on Earth, in space, or on an extraterrestrial body.

[0079] Referring to Figure 1, the server device 30 is designed to connect to a communications network 50, allowing it to send and receive data using a network transfer protocol over the network 50. This data exchange occurs between the server device 30, a client device 20 (and therefore, client system 12), and the data protocol adapter and translator 18, all configured to use the same networktransfer protocol for communication over the network 50. The client device 20, which can be a computing device, has a web browser 22 installed that serves as a software interface. This interface allows the client to send data related to client hardware 14, including its physical parameters, mission requirements, and commands, to the server device 30. The client device 20 can also receive simulated telemetry generated by the platform emulator 46 from the server device 30. In a further refinement, the server device 30 hosts a web server 36 that delivers scripts, stylesheets, and markup language code over the network 50 (e.g., the Internet) when the web browser 22 on the client device 20 accesses the URL or IP address of the server device 30. In this scenario, the network transfer protocol can be the Ethernet transfer protocol. Additionally, as shown in Figure 1, a physical interface 24 is provided to the developer. This physical interface 24 replicates the physical interface found at a berth on the space platform, which secures the client's hardware to the platform and supplies it with power resources. This physical interface 24 is coupled to the client hardware during on-ground development and testing.

[0080] As previously described with regard to the Port, a space platform may be equipped with systems and software that perform various functions, including power generation, bi-directional communication with ground stations, station-keeping and orientation in three axes, and waste heat rejection through radiator panels. The platform's power system is capable of generating, storing, and distributing power to both the internal systems and the interfaces at each berth. The mechanical interface used to attach payloads to the space platform may also support bi-directional data and power transfer, as well as thermal conduction, thereby eliminating the need for additional interfaces, as implemented on the Port.

[0081] Referring to Figs. 1 and 2, one configuration of the server device 30 is shown, communicating bi-directionally over the Internet (serving as the network 50) through a network interface, which in this case is implemented using a network router 51. In one variation, the server device 30 is depicted as a stand-alone computer loaded with server software, though it should be noted that the server device 30 could also be implemented using two or more networked computers or other devices. In a refinement, the space platform emulator 46 is simulation software that is storedon and executed from an application server 40, designed for rapid integration, testing, and risk reduction. The space platform emulator 46 communicates bi-directionally with the web server 36. It is configured to receive simulation initialization parameters from the optimization and planning software 42 (such as the HarborMaster Agent’s platform configuration software) and to send simulation output logs to the file server 44. Those skilled in the art will recognize that, although the variation illustrated in Fig. 2 shows all components of the disclosed system implemented on a single computer device configured with software to function as a web server, database server, application server, and file server, these components can be implemented in various ways. For instance, the web server 36, database server 38, application server 40, and file server 44 could each reside on one or more networked devices, appropriately configured to perform their respective functions. Additionally, as illustrated later in Fig. 11 , many of these components may be hosted on data centers (‘in the cloud’) servers.

[0082] Referring to Figure 3 , the data flow involved in the onboarding, integration, and testing process is illustrated. The Extended Markup Language (XML) data schema and Fusion Engine 52 can play a central role in this process. They receive several key inputs: orbit conditions data 54, customer (or developer) specifications data 56, and component vendor specifications data 58. The orbit conditions data 54 is also sent to the remote / pre-launch integration and testing (I&T) simulations 62, which can communicate bi-directionally with the XML data schema and Fusion engine 52. Additionally, the XML data schema and Fusion engine 52 are connected bi-directionally with the mission operations and scheduling module 64 and the systems analysis and aggregation tool 66. Both of these modules are configured to receive a visiting vessel and resupply properties data 60 as inputs. The outputs from the XML data schema and Fusion engine 52 feed into several other components: the launch resupply manifesting module 68, operations apps (flight software) 70, POSITIVE on-board software 72, and the on-board software manifesting module 74. The XML schema, managed by the XML data schema and Fusion engine 52, defines the critical information needed for evaluation, analysis, and port operations. The schema categorizes data into several top-level categories, such as identifiers, mass properties, guidance and navigation control (GNC) properties, connecting properties, thermal properties, electrical properties, and radio frequency (RF) properties. In summary,this configuration illustrates how various types of data — ranging from environmental conditions to specific hardware requirements — are integrated, processed, and used to ensure the hardware is properly prepared for its mission on the space platform. The XML schema and Fusion engine 52 are advantageous for organizing and managing this data flow.

[0083] In another aspect, the categorization of data types involves several top-level categories, each designed to capture specific attributes of the object (i.e., the hardware integrated into a space platform) described by the XML schema. The "Identifiers" category includes tags that specify the type of object, the unit format of the data, and other key identifiers. For example, the "Mass Properties" category details the primary mass and inertial characteristics of the object, including its mass, center of mass, and moment of inertia tensor. The "GNC (Guidance, Navigation, and Control) Properties" category identifies the locations and characteristics of components such as reaction wheels or attitude control thrusters. The "Connecting Properties" category lists the number of connecting adapters (or "connecting interfaces") on the object, along with each object's physical and data protocol specifications. The “Thermal Properties” category describes the thermal characteristics of the object, while the "Electrical Properties" category includes details such as power generation, voltage lines, maximum current capacities, and the expected surface charge of the object upon capture. Lastly, the "RF Properties" category identifies the number and characteristics of RF devices (such as transmitters and receivers) on the object. It should be noted that this data is stored in relation to the space platform, the client hardware 14 intended to be hosted by the platform, and any hardware already hosted by the platform.

[0084] Referring to Figure 4, a screenshot of an example data entry graphical user interface (GUI) screen 80 is shown on the display of the client device 20, accessed via the web browser 22 (as seen in Fig. 1). This GUI screen 80 is created by the web server 36 on the server device 30 to assist the developer in entering details about the services they require from the space platform provider, as well as the desired timeline for hosting their client hardware 14 on the platform. Based on the information entered by the developer on this screen, the space platform provider uses the HarborMaster Agent’s optimization and planning software 42 to generate a service quote.

[0085] Figure 5 is a screenshot of an illustrative service selection graphical user interface screen 82 displayed via a web browser 22 on the display of a client device 20. The graphical user interface screen 82 is generated by the web server 36 on the server 30. A query widget 84 is shown that is generated by the web server 36 on server 30 in response to the selection of one option provided on the service selection graphical user interface screen 82.

[0086] Figure 6 is a diagram representing a method for data entry via the GUI illustrated in Figure 4 is processed by the HarborMaster software suite 32 residing on the server device 30 and comprised of a web server 36, database server 38, application server 40 hosting the HarborMaster Agent’s optimization and planning software programs 42 and file server 44. The web server 36 generates a graphical user interface screen 88 displayed via the web browser 22 on a display of the client device 20. The illustrative graphical user interface screens 80, 82, and 88 are examples of screens generated by the web server 36 during an early contact by a developer of client hardware for display on the client device 20 to facilitate remote entry of pertinent information required to generate a quote for requested services. Much of the information provided by the developer at this early stage is not only utilized to generate a quote but is also utilized to properly model the configuration of the space platform at some future time when the client hardware 14 is hosted by the space platform. Thus, when information is provided by the developer, which includes data that may be useful in implementing additional features and functions of the disclosed system and method, such data is stored in a database, thereby updating the database. Whenever the database is updated or new entries are created, a series of scripts (known as the “HarborMaster Agent”) are automatically executed. These scripts aggregate all the information as inputs to optimization algorithms to match the developer’s requirements against the space platform’s resources that would be available during the requested timeframe. Once the developer agrees to have their client hardware 14 hosted by the space platform, the HarborMaster Agent scripts generate an initialization script for the space platform emulator (the “Digital Twin”) 14 and allocates a data protocol adapter and translator 18 that is shipped to the developer for remote / pre-launch interface validation. Once the interface validation process is in place, the HarborMaster web server 36 provides the developer with a link to the web page that is the front end to the space platform emulator 46. At the conclusion of the validation process, thedeveloper and space platform provider continue to use the HarborMaster web server 36 for additional planning and on-orbit operations visibility. Most of the HarborMaster’s underlying scripts and database structures are also used on the space platform for on-orbit planning and resource optimization.

[0087] Referring to Figure 7, once a solution is obtained based on customer input 122, the HarborMaster Agent scripts 42 generate and email a Sales Quote 124 to the developer listing the cost and berth assignment and confirmation of resource availability during the requested timeframe or generates an email 126 offering alternative timeframes if resources are not available during the original requested dates. The client logs into their web portal generated by the HarborMaster web server 36 to accept or reject the Sales Quote or modify entries to request a new Sales Quote.

[0088] As shown in Figure 7, the HarborMaster Agent is an encompassing autonomous agent that aggregates all analysis functions into a single toolkit. The agent takes inputs from multiple sources (e.g., the developer, other hosted customers, vendors, etc.) and converts them into a data format that can be accessed for analysis by all persons authorized to access the web interface.

[0089] The agent enables multiple functions including but not limited to examples of the development of viable mission timelines, Launch Vehicle (LV) manifests, space platform systems compatible with the developer’s needs, real-time cost analysis and resource management, and state- of-platform predictions utilizing a Port (“platform”) Aggregation Tool, a Multi-Variable Manifest / Placement Optimizer tool, an LV Trade Analysis tool, a Cost Analysis and Prediction Tool and an Attitude / Momentum Tool.

[0090] In another aspect, the Port (“platform”) Aggregation Tool of the of the HarborMaster Agent function defines the state of the platform in various configurations by updating the platform configuration for various time periods based on the hosted client hardware, other hosted customer’s devices, platform resources and components to allow for a very quick technical assessment of a current design of the space platform. This aids in the rapid development process for a developer’shardware and allows the developer and platform provider to address various “what if' s” that can only be uncovered with an aggregated view of the platform while hosting the client hardware 14.

[0091] An example of the (“platform”) Aggregation Tool, as described, is shown in Figure 8. In this illustrated example, the tool receives external inputs 92 from the developer, other hosted customers’ and components’ XML files 94 stored in the HarborMaster database, orbital conditions 96 data, and attitude 98 data from the appropriate systems of the platform or from those modules of the platform emulator 46 that simulate those systems. The platform aggregation tool includes a database through an SQL Database 100 and an illustrative example Python GUI application 102. The SQL database 100 receives the developer’s, other hosted customers’, and components’ XML files 94 stored in the HarborMaster database and converts that into data for outputting to the Python GUI Application 102. The Python GUI application 102 receives user inputs 104 that incorporate Port configuration 106 data and incoming / outgoing assets 108 data. The Python GUI application 102 utilizes the data it receives to output data for systems analysis 110 by, as an example function, the thermal analysis 112, station keeping 114, stability analysis 116, and momentum management 118 functions of the space platform and of the platform emulator 46 that simulates those system analysis 110 functions. The Python GUI application 102 facilitates quick and interactive systems analysis 110. XML generation has been integrated directly to a preferred drawing product, SolidWorks for convenient XML property updates when the platform emulator 46 CAD model is updated.

[0092] In another aspect, the Multivariable Inventory Optimization Tool of the HarborMaster Agent function addresses concerns arising when inventory is depleted or relocated aboard the space platform and when new inventory is supplied to the platform. When sending a resupply mission to a space platform, the platform provider is not so much concerned with where inventory is stored onboard but rather that the inventory is balanced for the center of gravity (“CG”) and moment of inertia (“MOI”) purposes. The same concerns regarding platform center of gravity (“CG”) and moment of inertia (“MOI”) purposes arise when the developer’s hardware is docked to the station for hosting. These concerns are resolved using multivariable optimization implemented by the Multivariable Optimizer Tool through the utilization of a manipulator, such as a robotic arm, toreposition the inventory and hardware to attain the desired CG and MOI properties for the platform. Multivariable Inventory Optimization Tool is included as part of the HarborMaster Agent and can interact with the platform emulator to facilitate the onboarding of a developer’s software.

[0093] In another aspect, the Launch Vehicle (“LV”) Trade Analysis Tool of the HarborMaster Agent function is utilized for resupply cargo launch scheduling and processing and for evaluating launch opportunities for a developer’s hardware. Resupply mission cargo and developer hardware is assessed with respect to mass, volume and required delivery date. Examples of options for cargo and resupply and hardware delivery to the space platform are as examples, Piggyback launch off of an ISS resupply or a dedicated Small LV from Earth. For ISS Piggyback Launch special handling or specific dates potentially need premium services and potentially a dedicated launch. Standard cargo and or developer’s hardware is assigned to the closest ISS resupply mission launch date with available mass and volume to accommodate the cargo and / or hardware. Limited options exist for dedicated small LV launches, however more options are expected to arise in the near future. This tool can also be used to assess orbital transfer vehicle (OTV) cargo transfer, as cargo can come from orbit.

[0094] In another aspect, a Cost Analysis / Resource Prediction Tool of a representative HarborMaster Agent function is instantiated as an Excel-based tool utilized to roll up quarterly revenue and expenses for all platform services by taking into account the required onboard resources for each quarter. The Cost Analysis / Resource Prediction Tool communicates with a Python script to tie in another HarborMaster agent, the Aggregation Tool, to enable accurate power, mass, and momentum calculations in real-time. The Cost Analysis / Resource Prediction Tool is also able to tie into the HarborMaster front to display service availability to prospective hardware developers on the web interface. The Cost Analysis / Resource Prediction Tool tracks all resources and keeps inventory over time. A predictive capability is incorporated by another HarborMaster agent function, integrating the Port Aggregation tool into the cost analysis performed by the Cost Analysis / Resource Prediction Tool. The Cost Analysis / Resource Prediction Tool loads in the developer’s mission set per Quarter and can specify for each developer or other customer what services are required for each quarter. TheCost Analysis / Resource Prediction Tool then determines what additional resources need to be added to the platform in prior quarters to achieve this inventory which translates to a cost estimate for platform operations to support new missions and informs pricing presented to the customer. As shown, for example, in Figure 8, the HarborMaster Agent evaluates resources required, Launch Opportunities, and service enhancements for each customer in Real-time.

[0095] Referring to Figure 9, a flow diagram illustrates the process of initializing data parameters generated from entries made into the query widget in Figure 5, which are then integrated into the web interface 16 on server 12. A hardware developer utilizing a client device 20 operating browser software 22 communicates with the server 12 and is presented with a graphical user interface screen 82 containing query widget 84 regarding the properties of their hardware, including the type of hardware and the physical and angular units utilized to provide the information. Among the properties requested by the query are docking properties and mass properties, including mass, center of mass, and moments of inertia in various axes relative to the center of mass. The entries into query widget 84 are automatically converted into XML data format 134, which is converted into a text file for transfer to the platform emulator 46. The parameters in the text file are loaded into the simulation data store. When the simulation runs, it uses the information in the data store to update parameters within the related subsystem models.

[0096] Referring to Figure 10, a block model of example subsystems of the platform emulator 46 is shown. The platform emulator 46 is implemented utilizing simulation software, for example, graphical simulation software such as SimuLink or SystemBuild, which includes subsystems that may be designated as Discrete, Procedures, or Triggered models. In a variation of the platform emulator 46, a simulation is generated utilizing a hierarchical model that represents communications between the space platform and ground-based operators, the orbital environment, and the platform combined in a top-level discrete superblock 142. Screenshot 144 represents the expansion of the platform superblock shown in 142 into models of the platform’s hardware and onboard software components. The platform hardware discrete superblock 146 is expanded to show the sensors and actuators of the platform. The actuators discrete superblock 148 is expanded to show the reaction wheels and thrustersused to change the attitude and position of the platform. The three thick arrows shown in Figure 10 represent the expansion of a superblock into its lower-level components. The thin lines between superblocks at the same level represent internal inputs and outputs between the blocks, while the numbered lines show inputs from and outputs to higher-level superblocks. The inputs and outputs shown at the top-level discrete superblock 142 are inputs to and outputs from external programs, such as scripts, graphical user interfaces, and databases.

[0097] A variation of the top-level discrete superblock 142 is implemented using a command and telemetry block 150, environment block 152 and a Port block 154. The vessel block 156 is a pictorial representation of the space platform and does not provide any functionality to the simulation. The command and telemetry block 150 receives the feedback of the output vector of Port block 154 as its input vector. The output vector of the command and telemetry block 150 acts as one of two input vectors to the environment block 152 and as one of two input vectors to the Port block 154. The second of two input vectors to the environment block 152 is the feedback of the output vector of the Port block 154. The output vector of environment block 152 acts as the second of two input vectors to Port block 154 and is also a top-level output vector to external programs outside the platform emulator 46. The output vector of the Port block 154, in addition to being a feedback input vector for the command and telemetry block 150 and the environment block 152 serves as a top-level output vector to external programs. The platform discrete superblock is implemented using a Port hardware block 158, a Spacecraft-to-software (SW) interface block 160, a GNC block 162, and a SW-to- Spacecraft interface block 164. One illustrated input vector to the Port hardware block 158 is the output vector of the SW to spacecraft interface block 164, while the other illustrated input vector is a flow down of inputs to the upper-level port superblock 154. The output vector of the Port hardware block 158 acts as an input vector to the Spacecraft-to-SW interface block 160 and is also provided as an output vector flowing up to the output vector of the top-level Port superblock 164. The output vector of the Spacecraft-to-SW interface block 160 is provided as an input vector to the GNC block 162 and is also provided as an output vector flowing up to the output vector of the top-level Port superblock 164. The output vector of the GNC block 162 acts as an input to the SW-to-spacecraft interface block 164. The platform hardware discrete superblock 146 is implemented using anactuators block 166, a sensor block 168, a manipulator block 172 and an electrical power system (EPS) block 170. The actuators discrete superblock 148 is implemented using a reaction wheel (RW) block 174 and a thrusters block 176.

[0098] When the developer logs into the web portal to access the port emulator’s web page that represents a “Ground Operator’s Console” for viewing telemetry and issuing commands, the platform emulator 46 automatically queries the HarborMaster for the configuration file that adjusts the emulated mass and inertial properties, the mission mode controller for arrival and docking procedures including rotation of the platform to align with, as an example, an orbital transfer vehicle (OTV) delivering client hardware 14 to the space platform, the engagement of a docking mechanism, the switching on of power relays and onboard processing resources and triggering the correct processing of telemetry coming from the client hardware 14 via the data protocol adapter and translator 18 and commands selected by the developer on the web portal to be sent to the client hardware 14 via the data protocol adapter and translator 18. The platform emulator is a full 6- Degree- of-Freedom simulator that provides the developer and the space platform operator with a closed-loop simulation of the interactions between the space platform and the developer’s hardware. As the hardware automatically sends commands to the platform emulator (“Digital Twin”) 14, a model of the space platform’s hardware, software and operating environment is simulated to emulate what the client hardware 14 would experience on orbit. Since in one disclosed variation, the space platform’s flight software is derived from the same models underlying the Digital Twin emulator 46, the platform emulator 46 can also be used during on-orbit operations as a telemetry simulator for detecting, isolating and planning recovery from faults onboard the space platform.

[0099] Figure 11A provides a block diagram illustrating the communication overview between the platform emulator 46 and the developer’s client hardware 14, which may include payloads, manipulators, sensors, and docking mechanisms to be attached to the space platform. Multiple developers can access the platform emulator 46 simultaneously, as separate instances can be run on different cores of the server device’s processor 30. Each developer logs into their account via the web portal 22 and is served a customized web page displaying their unique list of commandsand widgets to monitor telemetry. Block 30 represents the server device that hosts the web server 36, which defines the content and layout of the developer’s web portal 22, the database server 38, the application server 40 hosting the HarborMaster Agent 42 scripts for analysis, optimization, configuration, planning, and quote generation, and the file server 36, which stores log files, quotes, and reports generated by the application server 40. These files are served to the client via the web portal 22. The space platform emulator 46 is also hosted on the server device 30. Block 180 represents the connection between the server(s) in block 30 and the Internet router in block 51. The components shown in blocks 30, 180, and 51 are located at the space platform provider’s facilities and / or data center. At the developer’s facility, the client’s Internet router is shown in block 26, the Applique is in block 18, the developer’s data connector that mates with the Applique is in block 24, the developer’s hardware is shown in block 14, and the web client used to access the space platform provider’s server and applications in block 30 via the Internet 50 is shown in block 22.

[0100] Prior to shipping the Applique shown in block 18 to the developer’ s facility, the public IP address or dynamic DNS address and an open port number on the space platform provider’s Internet router 51 and the public IP address or dynamic DNS address and open port of the client’s Internet router 26 are programmed onto the Applique 18 as the remote and local server / ports, respectively. Block 30 represents examples of the different types of data connectors and protocols used to connect the Applique in Block 18 to the client’s hardware in Block 14.

[0101] Figures 11B and 11C illustrates the Arkisys onboarding process, which uses a digital twin, the HarborMaster toolkit, and Applique devices to simulate the flight operations of a payload connected to a spacecraft in orbit. Figure 11 A shows the ground onboarding process, where customer payloads and other devices 182 are physically connected to an Applique device. These Applique devices 184 communicate over a secure VPN connection 186 with a digital twin of the spacecraft, which can be hosted either in the cloud or on-site at Arkisys. This digital twin, also known as the spacecraft emulator, along with the HarborMaster Toolkit, which processes data from the Appliques to the digital twin, is shown in yellow in the figure. Figure 11C illustrates the corresponding process when the spacecraft is in orbit, which the onboarding process on the ground is designed to emulate.In orbit, the customer payloads and other devices 188 will be hosted on one of the six bays of the Arkisys Port Module, a hexagonal spacecraft (with bays labeled Alpha, Bravo, Charlie, etc.). Each bay interfaces with the spacecraft’s flight computer through an Applique device. The spacecraft’s core operating functions are managed by the flight software, which corresponds to the Digital Twin shown in the top half of the figure. Following the onboarding process depicted in the upper figure, the integration of spacecraft components and customer payloads, as shown in the lower figure, becomes seamless, as the ground and orbital configurations are electrically and digitally identical..

[0102] Figure 12 is a top view of the data protocol translator and adapter 18, which is shown connected to a client’s hardware data interface in block 12 and to an Ethernet network in block 196.The device uses a microcontroller (MCU) in block 190 and firmware that contains drivers for the integrated circuits 192 and 194 on the device. These components support the various interface protocols transmitted through the connector in block 12. The firmware also includes instructions for identifying the source and destination of incoming and outgoing data, encrypting and decrypting the data, packetizing and depacketizing data for transport layer formatting, and performing a checksum operation to validate data integrity.

[0103] The connection between the data protocol adapter and translator 18 and the client hardware 14 is made using a physical connector that matches the specifications that the developer initially entered on the HarborMaster web portal. The data protocol adapter and translator’s firmware receive data that represents the hardware’s output (“telemetry”), converts the data stream to a transport layer packet, for which an example is the User Datagram Protocol (“UDP”), and transmits the data to the space platform emulator’s IP address and specified port via the data protocol adapter and translator’s RJ45 connector and Ethernet cable attached to an Internet router at the developer’s site. The developer uses the HarborMaster link to the space platform emulator’s web page designed to function as the developer’ s Ground Operations console to view the telemetry and to select and send commands from the space platform emulator to the client hardware. The command is sent as a UDP packet to the specified IP address and port on the developer’s Internet router which then forwards the commands across its network to the data protocol adapter and translator’s RJ45 Ethernet connector.The data protocol adapter and translator’s firmware receives the UDP packet, performs any required translations and validation of the command and then forwards the command to the developer’s hardware via the developer specified connector. The data protocol adapter and translator used in the pre-launch or pre- connection interface validation is an engineering unit with the same functionality as the data protocol adapter and translators used onboard the space platform with the only differences being the microcontrollers / microprocessors onboard the space platform are designed for Space.

[0104] Referring to Fig. 13, a flow diagram illustrates the command path from the space platform emulator 46 through the data protocol adapter and translator 18 to the client hardware 14. The process begins when the developer logs into their web portal 22 and accesses a webpage displaying a list of commands that were specified during the account setup and initial inquiry phase. The developer selects a command in block 210 on the web portal 22, which is then transmitted (block 210) from their device 14 to the web server 36 and the space platform emulator 46. The emulator 46 encapsulates the command into a transport layer protocol, such as UDP, and then sends the command (block 1303) through the Internet router 51 to the public IP address and port number configured on the developer’s Internet router 26. This router forwards the command to the Applique data protocol adapter and translator 18. The Applique’s firmware validates and converts the UDP packet into the developer- specified protocol, performs any necessary decryption (block 216), and then transmits the converted packet (block 218) to the client hardware 14 via the connector 24. Finally, the client hardware 14 executes the selected command, completing the "Device Takes Action" step in block 220.

[0105] Referring to Figure 14, a flow diagram illustrates the telemetry path from the client hardware 14 through the data protocol adapter and translator 18 to the platform emulator 46. The process begins with client hardware 14 sending a message to the interface connector 24 of the data protocol adapter and translator 18 or controller, as shown in the "Send Reply" step 230. The data protocol adapter and translator 18 or controller then perform an "Encode Telemetry" step 232, where the telemetry message is encapsulated into a UDP packet. Next, in the "Send Telemetry" step 234, the data protocol adapter and translator 18 or controller sends the UDP packet to the IP address andport number assigned to the platform provider’s Internet router 51 via the developer’s Internet router 26 and the public Internet 18. The platform provider’s Internet router 51 then forwards the telemetry to the server device 30 and ultimately to the platform emulator 46, as shown in block 236. The emulator validates and decodes the UDP packet in step 238 and sends the converted data to the web server 36. The web server 36 then serves the data to the developer’s web portal 22, where the telemetry is displayed in various formats, such as text, digital displays, and instrument readings, completing the "Telemetry Displayed" step 240.

[0106] In another aspect, a method is provided for integrating and testing client hardware before its rendezvous and connection with a space platform using the system described in Figures 1 and 2. This method validates the operation of the client hardware with a platform emulator that simulates the space platform in orbit. A data protocol adapter and translator is supplied to the client hardware developer, allowing command and telemetry data generated by the client hardware to be processed and converted from any data protocol to Ethernet. Additionally, a physical berth interface is provided to the developer, which connects to the data protocol adapter, translator, and the client hardware itself. This setup ensures that the client hardware meets the interface requirements of the space platform before the actual rendezvous and connection. Typically, this testing occurs while the client hardware is still on the ground and in the development stage. The client hardware's operation, even when it is not co-located with the platform emulator, is validated through Ethernet-based control while it remains on the ground.

[0107] In another aspect, the method includes encrypting data that is transmitted between the data protocol adapter and translator and networked devices. This applies to data exchanged with a router connected to the data protocol adapter and translator, a network, a remotely located router connected to the network, and a server device hosting a web server that communicates with either a platform emulator simulating the space platform or with the space platform itself.

[0108] In another aspect, a method is provided to accelerate the remote integration (such as pre-launch or pre-connection) between a space platform and a developer’s hardware. This method automates the developer support cycle from the initial inquiry through to the completion of the on-orbit mission. It optimizes the allocation of space platform resources to meet the developer’s needs while allowing both the space platform provider and the developer to have simultaneous visibility into the interface validation and the anticipated performance of the space platform. This method includes one or more of the following steps, either individually or in combination.

[0109] In another aspect, the method includes providing a hardware developer with a data protocol adapter and translator configured to transmit and receive data using a specific transfer protocol, converting the data to a protocol compatible with the developer's hardware. The process also involves using a server with platform modeling software to generate a platform emulator, which receives data in the transfer protocol from the client hardware. The received data is then entered into the modeling software to determine its effect on the platform, generating effect data that is sent back to the hardware developer through the data protocol adapter and translator. The method uses the Internet to transfer data between the hardware developer and the server, where the data link layer of the transfer protocol is Ethernet, and the transmission protocol is UDP. Additionally, the process includes receiving physical parameters of the client hardware, modifying the platform modeling software to represent the client hardware as docked to the platform, and transferring compatibility data back to the client hardware developer. Throughout this process, data is encrypted during transmission. The method also includes providing the client hardware developer with a physical interface designed to connect both to the client hardware and the data protocol adapter and translator, ensuring secure and efficient data transfer.

[0110] Referring to Figure 15, a flowchart of a method for integrating and testing client hardware before its rendezvous and connection with a space platform is provided. In step a), a hardware developer is provided with a data protocol adapter and translator 18 configured to process command and telemetry data generated by the client hardware and convert data from any data protocol to Ethernet. In step b), a physical berth interface 24 is provided to the hardware developer. In a refinement, the server device 30 is configured to generate a physical berth interface for prelaunch testing. The physical berth interface can be configured to replicate mechanical and electrical connections available on the space platform for validation purposes. In particular, the physical berthinterface 24 is configured to connect the data protocol adapter and translator 18 to the client hardware 14. In step c), the operation of client hardware 14 is validated with a platform emulator that simulates the space platform in orbit. In step d), the client hardware 14 is ensured to meet the interface requirements of the space platform prior to rendezvous and connection with the space platform.

[0111] In another aspect, the method further includes step e), in which the data that is transmitted between the data protocol adapter and translator and networked devices is encrypted. Characteristically, the data is exchanged with a router connected to the data protocol adapter and translator, a network, a remotely located router connected to the network, and a server device hosting a web server that communicates with either a platform emulator simulating the space platform or with the space platform itself.

[0112] In another aspect, the method further includes step f) of automating a developer support cycle from initial inquiry through to completion of an on-orbit mission. In step g), an allocation of space platform resources is optimized to meet a developer’s requirements. In step h), simultaneous visibility for both a space platform provider and the hardware developer is enabled into interface validation and an anticipated performance of the space platform.

[0113] In another aspect, the method further includes step i) in which the data protocol adapter and translator 18 is further configured to receive data using a specific transfer protocol and convert the data to a protocol compatible with the client hardware 14.

[0114] In another aspect, the method further includes the following steps: generating a platform emulator using platform modeling software hosted on a server (step j); receiving data with a transfer protocol from the client hardware 14 into the platform modeling software (step k); determining effects of the received data on the space platform modeled in the platform modeling software (step 1); generating effect data based on the determination (step m); and transmitting the effect data to the hardware developer through the data protocol adapter and translator (step n). Characteristically, data transmission between the hardware developer and the server utilizes the Internet, with a data link layer being Ethernet and a transmission protocol. In a refinement, datatransmission between the hardware developer and the server utilizes the Internet, with a data link layer being Ethernet and a transmission protocol being UDP.

[0115] In another aspect, the method further includes receiving physical parameters of the client hardware 14 and modifying the platform modeling software to represent the client hardware 14 as docked to the space platform (step o).

[0116] In another aspect, the method further includes transferring compatibility data from the server to the hardware developer, indicating compatibility of the client hardware with the space platform (step p).

[0117] In another aspect, the method further includes providing the hardware developer with a physical interface designed to connect both to the client hardware 14 and the data protocol adapter and translator, ensuring secure and efficient data transfer (step q). Characteristically, the operation of the client hardware 14 is validated through Ethernet-based control while the client hardware remains on Earth.

[0118] While exemplary embodiments are described above, it is not intended that these embodiments describe all possible forms of the invention. Rather, the words used in the specification are words of description rather than limitation, and it is understood that various changes may be made without departing from the spirit and scope of the invention. Additionally, the features of various implementing embodiments may be combined to form further embodiments of the invention.

Claims

WHAT IS CLAIMED IS:

1. A system for accelerated remote interface validation and space platform resource optimization, comprising a client system, a server device, and a communication network configured to facilitate bi-directional data exchange between the client system and the server device, the client system including: client hardware to be validated, the client hardware configured for eventual integration with a space platform; a data protocol adapter and translator configured to convert data from a protocol utilized by the client hardware to a platform-native protocol; and a client device with a web browser for transmitting data related to the client hardware to the server device and receiving telemetry data from the server device; and the server device including: a web server configured to interact with the client device to facilitate data transmission; a database server for storing data related to the client hardware, the space platform, and a validation process; an application server running optimization and planning software for validating compatibility of the client hardware with the space platform; a platform emulator configured to simulate a space platform's environment, including its resources and subsystems, to validate compatibility of the client hardware; and a file server for storing logs, reports, and other data generated during the validation process.

2. The system of claim 1, wherein the platform emulator comprises: a digital twin of the space platform, the digital twin including software representations for subsystems of the space platform, including power generation, thermal control, data processing, and attitude control; anda simulation of an operating environment of the space platform, including orbital dynamics, atmospheric drag, and magnetic fields, to validate client hardware functionality in a realistic orbital scenario.

3. The system of claim 1, wherein the data protocol adapter and translator is further configured to: encrypt and decrypt data transmitted between the client system and the server device; and validate data packet integrity before forwarding them to the client hardware or the server device.

4. The system of claim 1, wherein the web server is further configured to: provide a graphical user interface (GUI) accessible via the client device for a developer to input hardware specifications and mission requirements; and display telemetry and command data from the client hardware during the validation process, enabling real-time monitoring and adjustment.

5. The system of claim 1, wherein outputs from a platform emulator’s simulation are utilized to automatically optimize allocation of a space platform's resources to support multiple concurrent hardware components or pay loads.

6. The system of claim 1, wherein the server device is configured to generate a physical berth interface for pre-launch testing, the physical berth interface configured to replicate mechanical and electrical connections available on the space platform for validation purposes.

7. The system of claim 1, wherein the client system is bi-directionally coupled to the communication network utilizing a network data protocol for transferring data via a client network interface with the client hardware configured to receive commands and send telemetry data utilizing a hardware data protocol.

8. The system of claim 1, wherein further the space platform has resources and subsystems including a navigational subsystem and a control subsystem.

9. The system of claim 1, wherein the server device is configured to execute a server application and is in bi-directional communication with a server network interface coupled to the communication network.

10. The system of claim 1, wherein the web server is configured to be in bi-directional communication with the application server, the web server configured to generate portal pages for transfer over the communication network for display by the web browser on the client device, thereby permitting a developer to input data to and receive data from the web server.

11. The system of claim 10, wherein the database server is configured to be in bidirectional communication with the web server, the database server further configured to receive and store data entered in a web portal page and to send data to the web portal page and other server applications.

12. The system of claim 11, wherein the application server is configured to host software programs, scripts, and executables that receive data from the database server and act upon the data to optimize resources of the space platform, generate cost and schedule reports, and initialize a platform emulator based upon aggregated properties.

13. The system of claim 12, wherein the file server is configured to receive files generated by the optimization and planning software and the platform emulator.

14. The system of claim 13, wherein the data protocol adapter and translator is configured for bi-directional communication with the client hardware utilizing a hardware data protocol and configured for bi-directional communication through a network interface and over the communication network to the web server utilizing a network data protocol, the data protocol adapter and translator being further configured to translate data received in the hardware data protocol from the client hardware into data for transmitting in the network data protocol for transmitting to the web server and to translate data received in network data protocol from the web server into data for transmitting in the hardware data protocol for transmitting to the client hardware.

15. The system of claim 6, wherein the platform emulator is configured in bi-directional communication with a web interface and a server application with a network data protocol, the platform emulator being configured to simulate the space platform, including on-orbit functionality of a space platform’s resources and subsystems.

16. The system of claim 15, wherein the communication network is the Internet, a server network interface is a router, a client network interface is a router, and the network data protocol is Ethernet.

17. The system of claim 16, wherein pages generated by the web server are Graphical User Interface (GUI) pages.

18. The system of claim 17, wherein specifications for the client hardware include dimensions and mass properties.

19. The system of claim 18, wherein the specifications for the client hardware further include power requirements.

20. The system of claim 19, wherein the specifications for the client hardware further include operating temperature requirements.

21. The system of claim 20, wherein the specifications for the client hardware further include commands and telemetry requirements.

22. The system of claim 21, wherein a developer inputs the specifications for the client hardware utilizing a GUI displayed by the web browser on the client device, and the platform emulator updates a model of the space platform to include the specifications for the client hardware.

23. A method for integrating and testing client hardware before its rendezvous and connection with a space platform, comprising: providing a hardware developer with a data protocol adapter and translator configured to process command and telemetry data generated by a client hardware and convert data from any data protocol to Ethernet; providing a physical berth interface to the hardware developer, the physical berth interface being configured to connect the data protocol adapter and translator to the client hardware; validating operation of the client hardware with a platform emulator that simulates the space platform in orbit; and ensuring that the client hardware meets interface requirements of the space platform prior to rendezvous and connection with the space platform.

24. The method of claim 23, further comprising encrypting data that is transmitted between the data protocol adapter and translator and networked devices, wherein the data is exchanged with a router connected to the data protocol adapter and translator, a network, a remotely located router connected to the network, and a server device hosting a web server that communicates with either a platform emulator simulating the space platform or with the space platform itself.

25. The method of claim 23, further comprising:automating a developer support cycle from initial inquiry through to completion of an on- orbit mission; optimizing an allocation of space platform resources to meet a developer’s requirements; and enabling simultaneous visibility for both a space platform provider and the hardware developer into interface validation and an anticipated performance of the space platform.

26. The method of claim 23, wherein the data protocol adapter and translator is further configured to receive data using a specific transfer protocol and convert the data to a protocol compatible with the client hardware.

27. The method of claim 23, further comprising: generating a platform emulator using platform modeling software hosted on a server; receiving data with a transfer protocol from the client hardware into the platform modeling software; determining effects of the received data on the space platform modeled in the platform modeling software; generating effect data based on the determination; and transmitting the effect data to the hardware developer through the data protocol adapter and translator.

28. The method of claim 27, wherein data transmission between the hardware developer and the server utilizes the Internet, with a data link layer being Ethernet and a transmission protocol being UDP.

29. The method of claim 27, further comprising receiving physical parameters of the client hardware and modifying the platform modeling software to represent the client hardware as docked to the space platform.

30. The method of claim 27, further comprising transferring compatibility data from the server to the hardware developer, indicating compatibility of the client hardware with the space platform.

31. The method of claim 23, further comprising providing the hardware developer with a physical interface designed to connect both to the client hardware and the data protocol adapter and translator, ensuring secure and efficient data transfer.

32. The method of claim 23, wherein operation of the client hardware is validated throughEthernet-based control while the client hardware remains on Earth.

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