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The National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) is in the early stages of developing a mission design, project implementation plan, and procurement strategy tha... The National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) is in the early stages of developing a mission design, project implementation plan, and procurement strategy that could potentially lead to an Earth aerocapture technology demonstration mission. NASA LaRC is hereby soliciting information from potential sources with the capabilities to provide spacecraft systems and mission operations for the mission. The mission would demonstrate aerocapture at Earth as a precursor to using the technology for future planetary science missions. Aerocapture technology reduces the required capability and mass of a spacecraft propulsion system, lowering the launch vehicle payload mass or enabling more capacity for science instruments, and is particularly beneficial for missions to the Solar System's ice giant planets [1]. The demonstration mission is intended to focus on key objectives necessary to mature the technological readiness of aerocapture including vehicle aerodynamics, flight dynamics, guidance, navigation and control, and mission operations. Flight data will be acquired during the demonstration and used to improve and validate tools to design and plan future missions. NASA is considering two concepts for the mission, both of which use a small entry capsule (referred to as the Aerocapture Flight System, or AFS) to execute the aerocapture maneuver. The AFS is comprised of an aeroshell, reaction control system, other ancillary systems, and a SmallSat that is released into Earth orbit. The first mission concept utilizes a Geostationary Transfer Orbit (GTO) as an initial state for the AFS, which is deployed into GTO from an Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA). In the second concept, the AFS is released on an Earth intercept trajectory from a spacecraft returning from a lunar mission. A preliminary concept of operations (ConOps) for a GTO-based aerocapture demonstration is illustrated in Figure 1 (attached). Details shown regarding orbit altitudes are for reference only, and will continue to be resolved (TBR) in upcoming design trades. Referring to Figure 1, the preliminary high-level mission ConOps and sequence of events is as follows. The sequence of events is for reference and context only to support the vendors' responses to this request for information, and will continue to be updated as NASA LaRC progresses through the early stages of mission design. The AFS, attached to the port of an ESPA Grande with a separation mechanism, is delivered and released into GTO by the launch vehicle. The AFS continues in GTO while using its reaction control system to maintain attitude during preparations for the aerocapture maneuver. NASA's intention is for the AFS to complete less than two full orbits before beginning the aerocapture maneuver. Near GTO apogee, the AFS reaction control system delivers the delta-V required to divert the capsule along the flight path necessary to intercept the Earth's atmosphere and initialize the aerocapture maneuver. The AFS reaction control system continually adjusts the capsule's attitude, utilizing the vehicle's aerodynamic lift to maintain its flight path inside a pre-planned corridor through the Earth's atmosphere with a periapsis of approximately 65 km (TBR). After completing the atmospheric flight, the AFS exits the Earth's atmosphere in an elliptical orbit with an apoapsis of approximately 500 km (TBR). Within 15 minutes (TBR) after exiting the Earth's atmosphere, the forward heatshield of the AFS aeroshell is jettisoned and a SmallSat is released into the new elliptical orbit. The SmallSat utilizes its attitude control system to attain a stable attitude and prepares for an apogee burn to circularize the orbit. When the SmallSat reaches apogee for the first time, its propulsion system delivers the delta-V necessary to circularize the orbit at an altitude of 500 km (TBR). The SmallSat continues in its circular orbit until the flight data acquired throughout the demonstration has been transmitted to ground stations. Successful transmission of the flight data signifies the end of the demonstration, subject to any spacecraft disposal operations necessary in accordance with NASA orbital debris requirements [2, 3]. The salient features and high-level functional requirements of the AFS that are envisioned to support the mission’s preliminary concept of operations are as follows. Since NASA is in the early stages of mission and system design, these features and requirements are subject to change as the design matures. The information is provided herein as a reference for vendors to consider when evaluating the mission concept and assessing the capabilities that vendors may contribute to the demonstration mission in response to this request for information. AFS Mass and Volume: The AFS shall be a blunt-body capsule with a 60° (TBR) sphere-cone forebody geometry. The aeroshell backshell geometry has not been determined, but must provide the volume to accommodate the SmallSat, the AFS Reaction Control System, wiring harnesses, and ancillary systems required to perform the mission. The AFS shall possess the mass and volume to be accommodated on a single port of an ESPA Grande [4]. AFS Aeroshell: The aeroshell shall be comprised of a forebody heatshield structure and a backshell structure with mechanical provisions to separate the two structures after completion of the aerocapture maneuver. The backshell structure shall accommodate a separation ring to attach and release the AFS from the ESPA Grande port. Either structure shall incorporate the mechanical interface to attach and release the SmallSat after the aeroshell structures are separated. The backshell shall incorporate external mechanical interfaces for ground support equipment (GSE) and electrical connections for battery charging and functional tests prior to launch. Devices to sever wiring harnesses between the SmallSat and AFS systems will be required, and depending on the SmallSat's telecommunications configuration, an antenna(s) mounted to the backshell structure may also be needed. Aerodynamic Lift Provisions: The AFS will control its flight path during the aerocapture maneuver by modulating the magnitude and/or direction of the entry capsule's aerodynamic lift vector (e.g., bank angle modulation). The vehicle's aerodynamic lift is envisioned to be produced by the capsule flying at an angle-of-attack induced by either a center-of-gravity (CG) offset or an asymmetric aerodynamic device such as a trim tab. NASA's near-term trade studies will evaluate the different methods of producing aerodynamic lift considering system mass, technological readiness, complexity, and risk. Thermal Protection Systems: The aeroshell forebody heatshield and backshell shall include Government-furnished thermal protection systems (TPS) to protect the AFS from the aerothermal environments produced during the aerocapture maneuver. The TPS will be designed to accommodate the Entry System Instrumentation (ESI) described below and other ancillary systems and interfaces that require TPS penetrations for installation and/or operation. Entry System Instrumentation: The Government will furnish ESI to be incorporated into the aeroshell heatshield and backshell. The ESI will be comprised of thermocouples and pressure transducers, the quantities and locations of which have not been determined, to measure the AFS entry environments during the aerocapture maneuver. A Flight Data System residing on the SmallSat shall provide power to the ESI and record and store the ESI data that will be transmitted to ground stations near the conclusion of the demonstration. AFS Reaction Control System: The AFS shall incorporate a reaction control system with the capability to correct for launch vehicle orbit insertion dispersions, deliver the delta-V to divert the AFS into the intended Earth atmosphere interface conditions for aerocapture, and maintain AFS attitude as required from GTO insertion through the aerocapture maneuver to the point when the aeroshell separates and the SmallSat is released. AFS SmallSat: The preliminary demonstration mission concept of operations requires the AFS SmallSat to be operational for the full duration of the technology demonstration timeline. The SmallSat shall provide power, avionics and flight instrumentation including an inertial measurement unit (IMU), command and data handling (C&DH), attitude determination and control, and communications for all mission phases from GTO insertion to data download and orbital debris mitigation (as required). The SmallSat is required to interface with external systems, such as the AFS reaction control system and ESI, to support the mission through the aerocapture maneuver, and then operate in a stand-alone configuration after being released from the aeroshell. To aid in continuing the formulation of a mission design and developing a procurement strategy to implement the mission, NASA LaRC is conducting market research seeking sources with demonstrated experience to provide the following capabilities to support the demonstration mission. Design and Delivery of the AFS: Design, fabricate, integrate, and test the AFS including the aeroshell, reaction control system, SmallSat, separation systems, and Government-furnished TPS and ESI. Deliver the AFS to the launch provider and support assembly, test, and launch operations (ATLO). Mission Design and Navigation: Design of the orbital mechanics and navigation from the point the AFS is released into GTO to end-of-mission. Mission design will be supplemented by Government-furnished guidance, navigation and control (GNC) software to control the AFS during the aerocapture maneuver. Capabilities shall include experience with mission design and navigation for high-energy Earth orbits and missions returning from lunar environs. Mission Operations: Establish a ground operating system and conduct mission operations for all phases of the demonstration from launch to mission termination. NASA LaRC is seeking capability statements from all interested parties, including all socioeconomic categories of Small Businesses and Historically Black Colleges and Universities (HBCU)/Minority Institutions (MI), and members of the underserved communities as defined by Executive Order 13985, Advancing Racial Equity And Support For Underserved Communities Through The Federal Government, for the purposes of determining the appropriate level of competition and/or small business subcontracting goals for the Earth Aerocapture Technology Demonstration mission. The Government reserves the right to consider a Small, 8(a), Women-owned (WOSB), Service Disabled Veteran (SD-VOSB), Economically Disadvantaged Women-owned Small Business (EDWOSB) or HUBZone business set-aside based on responses received. No solicitation exists; therefore, do not request a copy of the solicitation. If a solicitation is released, it will be synopsized on SAM.gov. Interested firms are responsible for monitoring this website for the release of any solicitation or synopsis. Interested firms possessing one or more of the capabilities described above should submit a capability statement of no more than 20 pages (excluding cover page and table of contents) indicating the ability to perform these aspects of the demonstration mission. Please include the following elements in the capability statement. Mission ConOps Assessment: The preliminary mission ConOps described herein was formulated to advance the technology readiness level (TRL) of aerocapture and enable its infusion into future planetary missions. The ConOps includes multiple events requiring mechanical separations and severing of wiring harnesses, and relies on a SmallSat capable of controlling a flight system in two different configurations (AFS and stand-alone SmallSat). Provide an assessment of the preliminary ConOps identifying design drivers and risks relative to existing state-of-the-art systems and your capabilities and experience. Please include an evaluation of the potential mass and volume of the AFS relative to the ESPA Grande accommodation requirements. Suggest changes in the ConOps or the AFS configuration that would substantially reduce risk and cost without significantly compromising the demonstration objectives. Describe your organization's capability and experience to provide a SmallSat spacecraft and flight software that meets the mission requirements. Due to the anticipated fast-paced implementation of the mission, SmallSats that are nearly "off-the-shelf" are considered to be advantageous to mission success. Include information on the SmallSat form factor, mass, accommodation requirements, and operational heritage. Describe the SmallSat capability to interface and manage external systems such as the AFS reaction control system, and explain how the SmallSat would accommodate the changes in the flight system configuration that occur during the mission. Describe your organization's capability and experience to design and provide the AFS aeroshell. Provide examples of aeroshells of similar scale and mass utilized for Earth atmospheric entry in previous missions. Describe the basic aeroshell structural architecture and any unique features required by the mission that introduce substantial risk and cost. Discuss the provisions necessary to implement the three separation events required for the mission ConOps: 1) separation of the AFS from the ESPA Grande, 2) separation of the AFS forebody heatshield, and 3) separation of the SmallSat from the aeroshell. Describe your organization's capability and experience to plan and conduct the AFS integration and testing. Include a description of facilities, ground support equipment, and capabilities for AFS environmental testing. Include a description of previous experience integrating thermal protection systems onto blunt-body aeroshells and the installation of thermocouple and pressure transducer instrumentation. Describe your organization's capability and experience to design missions and navigation strategies for spacecraft in high-energy Earth orbits or returning from the Moon. Include information on analysis tools and methods and highlight any previous missions with a concept of operations similar to the aerocapture demonstration mission. Describe your organization's capability to establish a ground operating system and conduct mission operations. Include information on existing infrastructure that would be leveraged for the mission including telecommunications ground stations, mission operating centers, and ancillary hardware and software. Describe your plans for partnering with other organizations to provide any of the aforementioned capabilities for the mission. All responses shall be submitted electronically via NASA’s Enterprise File Sharing and Sync Box (EFSS Box), FedRAMP Moderate certified platform, no later than January 15, 2025. Electronic submissions shall not contain hidden formulas, tables, be locked, be password protected, or contain links to data not included in the electronic copy. Please reference the synopsis number and “Earth Aerocapture Demonstration RFI” in any response. All responses shall be submitted to: https://nasagov.app.box.com/f/7cf6c2fec43e4f7b8d1dff31208c6be9. If you have any trouble submitting your response via EFSS Box, please contact Stacy Hollis at stacy.m.hollis@nasa.gov. This synopsis is for information and planning purposes only and is not to be construed as a commitment by the Government nor will the Government pay for information solicited. Respondents will not be notified of the results of the evaluation. References: [1] "Uranus Flagship-class Orbiter and Probe using Aerocapture," AIAA 2024-0714, AIAA SciTech Forum, Orlando, Florida, January 2024. [2] "Process for Limiting Orbital Debris," NASA-STD-8719.14C , November 5, 2021. [3] "Orbital Debris Mitigation," NASA-NPR-8715.6E, April 18, 2024. [4] "ESPA User's Guide, the EELV Secondary Payload Adapter," Moog, Incorporated.