A debris shield may include one or more microfoam units, the one or more microfoam units comprising internal voids. The debris shield may include one or more phase change materials positioned within the internal voids. The debris shield may include an advanced composite material layer positioned over a surface of the one or more microfoam units.

A debris shield may include one or more microfoam units, the one or more microfoam units comprising internal voids. The debris shield may include one or more phase change materials positioned within the internal voids. The debris shield may include an advanced composite material layer positioned over a surface of the one or more microfoam units.

In a space traffic management system (500), space traffic management devices (100) individually mounted in a plurality of mega-constellation business devices and in a debris removal business device (45) are connected to each other via a communication line (200). The debris removal device (45) performs Active Debris Removal (ADR) against debris formed by a satellite managed by a first mega-constellation business operator. The debris removal device (45) acquires real-time high-accuracy orbital information of a satellite group of a second mega-constellation business operator in a timeframe in which a debris removal satellite, during orbital descent, passes through an orbital altitude region where the satellite group of the second mega-constellation flies, the debris removal satellite passing through the satellite group while ensuring flight safety.

In a space traffic management system (500), space traffic management devices (100) individually mounted in a plurality of mega-constellation business devices and in a debris removal business device (45) are connected to each other via a communication line (200). The debris removal device (45) performs Active Debris Removal (ADR) against debris formed by a satellite managed by a first mega-constellation business operator. The debris removal device (45) acquires real-time high-accuracy orbital information of a satellite group of a second mega-constellation business operator in a timeframe in which a debris removal satellite, during orbital descent, passes through an orbital altitude region where the satellite group of the second mega-constellation flies, the debris removal satellite passing through the satellite group while ensuring flight safety.

A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

Systems and methods for two-axis pointing of payloads are provided. A two-axis pointing system includes a pedestal, a support plate mounted to the pedestal by a connection which allows movement of the support plate in at least two rotational degrees of freedom, a payload mounted to the support plate, a first rotary actuator physically connected to the support plate and operable to move the support plate along a first of the rotational degrees of freedom, a second rotary actuator physically connected to the support plate and operable to move the support plate along a second of the rotational degrees of freedom, a baseplate, wherein the pedestal, the first rotary actuator, and the second rotary actuator are fixed to the baseplate, a plurality of harnesses for supplying at least one of power and telemetry for actuation of the system, and a thermal control system integrated with the support plate.

Systems and methods for two-axis pointing of payloads are provided. A two-axis pointing system includes a pedestal, a support plate mounted to the pedestal by a connection which allows movement of the support plate in at least two rotational degrees of freedom, a payload mounted to the support plate, a first rotary actuator physically connected to the support plate and operable to move the support plate along a first of the rotational degrees of freedom, a second rotary actuator physically connected to the support plate and operable to move the support plate along a second of the rotational degrees of freedom, a baseplate, wherein the pedestal, the first rotary actuator, and the second rotary actuator are fixed to the baseplate, a plurality of harnesses for supplying at least one of power and telemetry for actuation of the system, and a thermal control system integrated with the support plate.

The disclosed embodiments describe an integrated aerial exploration system for deployment on a planetary surface, the system including: a rotorcraft configured for flight in a low-density atmosphere and adapted to carry a scientific payload; an enclosure housing the rotorcraft during launch, transit, and landing, the enclosure including a mounting interface for attachment to a host vehicle and a cover movable to provide an opening for deployment of the rotorcraft; and a deployment mechanism configured, upon activation, to move the rotorcraft from within the enclosure to a position outside the enclosure through said opening; where activation of the deployment mechanism automatically releases the rotorcraft from the enclosure and deploys one or more stowed components of the rotorcraft into a flight-ready configuration for aerial operation.

The disclosed embodiments describe an integrated aerial exploration system for deployment on a planetary surface, the system including: a rotorcraft configured for flight in a low-density atmosphere and adapted to carry a scientific payload; an enclosure housing the rotorcraft during launch, transit, and landing, the enclosure including a mounting interface for attachment to a host vehicle and a cover movable to provide an opening for deployment of the rotorcraft; and a deployment mechanism configured, upon activation, to move the rotorcraft from within the enclosure to a position outside the enclosure through said opening; where activation of the deployment mechanism automatically releases the rotorcraft from the enclosure and deploys one or more stowed components of the rotorcraft into a flight-ready configuration for aerial operation.