Arquitectura híbrida de propulsión solar fotónica–plasmática con cosecha energética activa Resumen ejecutivo (abstract técnico) HelioSpace – IPSS es un sistema de propulsión espacial sin propelente que integra en una única arquitectura: Vela fotónica (presión de radiación solar) Vela de plasma (interacción electromagnética con el viento solar) Cosecha activa de energía del plasma Reinyección direccional de momento (modo boost) El sistema permite empuje, frenado, control orbital y generación energética continua, usando exclusivamente flujos solares naturales (fotones + plasma), eliminando la dependencia de combustible químico y reduciendo drásticamente la masa seca de misión. 1. Marco físico fundamental 1.1 Radiación solar (componente fotónica) A 1 UA: Flujo solar: Φ≈1361 W/m2\Phi \approx 1361 \ \text{W/m}^2Φ≈1361 W/m2 Presión de radiación (vela reflectiva ideal): Pγ=2Φc≈9 μN/m2P_\gamma = \frac{2\Phi}{c} \approx 9 \ \mu\text{N/m}^2Pγ=c2Φ≈9 μN/m2 👉 Empuje estable, continuo y predecible, dominante por unidad de área física. 1.2 Viento solar (componente plasmática) Valores típicos a 1 UA: Densidad: n∼5–10 iones/cm3n \sim 5\text{–}10 \ \text{iones/cm}^3n∼5–10 iones/cm3 Velocidad: v∼400–800 km/sv \sim 400\text{–}800 \ \text{km/s}v∼400–800 km/s Presión dinámica: Psw≈1–3 nPaP_{sw} \approx 1\text{–}3 \ \text{nPa}Psw≈1–3 nPa 👉 Débil por m² físico, pero potencialmente enorme por área efectiva electromagnética. 2. Concepto clave: Área efectiva inflada (A_eff ≫ A_física) El núcleo del IPSS no es competir con la presión fotónica, sino multiplicar el área de interacción con el plasma mediante: Tethers cargados (E-sail) Campos magnéticos (magsail / aro superconductivo) La interacción no ocurre en la estructura sólida, sino en la plasma sheath inflada:Aeff=πRplasma2conRplasma≫RestructuraA_{eff} = \pi R_{plasma}^2 \quad \text{con} \quad R_{plasma} \gg R_{estructura}Aeff=πRplasma2conRplasma≫Restructura 👉 Es aquí donde el sistema rompe la escala clásica. 3. Arquitectura IPSS – Nivel de sistema 3.1 Subsistemas principales A. Vela fotónica ultraligera Mylar, Kapton, grafeno metalizado Control de actitud por reflectividad diferencial B. Sistema E-sail / magsail Tethers conductores (decenas de km) Potenciales: +10 a +30 kV (iones) Alternativa: aro superconductivo (campo B) C. Cosecha energética de plasma Corrientes inducidas por flujo iónico Rectificadores + PPU Supercapacitores / baterías buffer D. Etapa de re-aceleración iónica Rejillas electrostáticas (tipo ion thruster) Usa iones capturados, no propelente propio E. Control de plasma y carga Gestión de sheath Prevención de arcos Control dinámico de potenciales 4. Definición formal de “Propulsión Inversa” 4.1 Modo Brake (IPSS-B) Se extrae energía cinética del viento solar, produciendo: Corriente eléctrica útil Incremento de transferencia de momento opuesto Frenado electromagnético controlado Formalmente:Δpplasma→Pel+Fdrag\Delta p_{plasma} \rightarrow P_{el} + F_{drag}Δpplasma→Pel+Fdrag 👉 Frenar = generar energía👉 No existe equivalente químico a esto. 4.2 Modo Boost (IPSS-A) Parte de la energía cosechada se usa para: Re-acelerar iones interceptados Expulsarlos direccionalmente Empuje:F=m˙ions⋅ΔvF = \dot{m}_{ions} \cdot \Delta vF=m˙ions⋅Δv Pero: m˙ions\dot{m}_{ions}m˙ions no proviene de tanques Proviene del flujo solar incidente 👉 Es un ram-augmented electric propulsion solar, sin masa almacenada. 5. Modos operativos integrados ModoFunciónConsumoUso típicoCruiseVela fotónica + E-sail pasivoMínimoTránsitos largosBrakeCosecha + drag plasmático0 propelenteInserciones, rendezvousBoostRe-aceleración iónicaEnergía cosechadaAjuste orbital activoParkEquilibrio empuje/frenoAutoestableObservación solar 6. Órdenes de magnitud (guía conceptual) Ejemplo híbrido Vela fotónica: 1 km² → ~9 N E-sail con R_eff = 10 km: A_eff ≈ 300 km² Empuje plasmático regulable: ~0.1–1 N Potencia eléctrica: decenas a cientos de W 👉 No compite con la vela: la complementa y controla. 7. Comparación con tecnologías existentes SistemaPropelenteEmpuje continuoFrenado activoEnergía propiaQuímicoSíNoNoNoIon clásicoSíSíLimitadoPanelesSolar sailNoSíNoNoE-sailNoSíParcialNoIPSS HelioSailNoSíSíSí 👉 IPSS es una clase nueva, no incremental. 8. Desafíos técnicos (reales y abordables) 8.1 Plasma & carga Arcos eléctricos Sputtering Inestabilidades sheath ✔ Solución: control adaptativo + materiales avanzados 8.2 Materiales Tethers ultraligeros y resistentes Superconductores (opcional) Recubrimientos anti-erosión 8.3 Control dinámico Torque fotónico vs torque plasmático Necesita GNC híbrido (campo + vela) 8.4 Variabilidad solar CME Turbulencia plasma ✔ Convertido en ventaja: más energía y empuje si se gestiona bien 9. Hoja de ruta tecnológica Fase A — Validación física CubeSat Mini E-sail Medición corriente vs drag Fase B — IPSS funcional 10–20 kg Re-aceleración iónica <200 W Cambio orbital medible Fase C — Vela híbrida 50–100 m Maniobras combinadas Parking solar estable Fase D — Operativa Misiones científicas Asteroides Observatorios solares Logística interplanetaria lenta pero permanente 10. Definición final (síntesis conceptual) HelioSpace IPSS no “usa” el Sol.Aprende a dialogar con él. No es una vela pasiva.No es un motor clásico.Es un sistema de intercambio inteligente de energía y momento con el entorno solar. Nombre final recomendado IPSS HelioSail™ Inverse-Propulsion Solar SailCapture. Convert. Maneuver. HelioSpace — IPSS (Inverse-Propulsion Solar Sail) Arquitectura híbrida de propulsión solar fotónica–plasmática con cosecha energética activa Resumen ejecutivo (abstract técnico) HelioSpace – IPSS es un sistema de propulsión espacial sin propelente que integra en una única arquitectura: Vela fotónica (presión de radiación solar) Vela de plasma (interacción electromagnética con el viento solar) Cosecha activa de energía del plasma Reinyección direccional de momento (modo boost) El sistema permite empuje, frenado, control orbital y generación energética continua, usando exclusivamente flujos solares naturales (fotones + plasma), eliminando la dependencia de combustible químico y reduciendo drásticamente la masa seca de misión. 1. Marco físico fundamental 1.1 Radiación solar (componente fotónica) A 1 UA: Flujo solar: Φ≈1361 W/m2\Phi \approx 1361 \ \text{W/m}^2Φ≈1361 W/m2 Presión de radiación (vela reflectiva ideal): Pγ=2Φc≈9 μN/m2P_\gamma = \frac{2\Phi}{c} \approx 9 \ \mu\text{N/m}^2Pγ=c2Φ≈9 μN/m2 👉 Empuje estable, continuo y predecible, dominante por unidad de área física. 1.2 Viento solar (componente plasmática) Valores típicos a 1 UA: Densidad: n∼5–10 iones/cm3n \sim 5\text{–}10 \ \text{iones/cm}^3n∼5–10 iones/cm3 Velocidad: v∼400–800 km/sv \sim 400\text{–}800 \ \text{km/s}v∼400–800 km/s Presión dinámica: Psw≈1–3 nPaP_{sw} \approx 1\text{–}3 \ \text{nPa}Psw≈1–3 nPa 👉 Débil por m² físico, pero potencialmente enorme por área efectiva electromagnética. 2. Concepto clave: Área efectiva inflada (A_eff ≫ A_física) El núcleo del IPSS no es competir con la presión fotónica, sino multiplicar el área de interacción con el plasma mediante: Tethers cargados (E-sail) Campos magnéticos (magsail / aro superconductivo) La interacción no ocurre en la estructura sólida, sino en la plasma sheath inflada:Aeff=πRplasma2conRplasma≫RestructuraA_{eff} = \pi R_{plasma}^2 \quad \text{con} \quad R_{plasma} \gg R_{estructura}Aeff=πRplasma2conRplasma≫Restructura 👉 Es aquí donde el sistema rompe la escala clásica. 3. Arquitectura IPSS – Nivel de sistema 3.1 Subsistemas principales A. Vela fotónica ultraligera Mylar, Kapton, grafeno metalizado Control de actitud por reflectividad diferencial B. Sistema E-sail / magsail Tethers conductores (decenas de km) Potenciales: +10 a +30 kV (iones) Alternativa: aro superconductivo (campo B) C. Cosecha energética de plasma Corrientes inducidas por flujo iónico Rectificadores + PPU Supercapacitores / baterías buffer D. Etapa de re-aceleración iónica Rejillas electrostáticas (tipo ion thruster) Usa iones capturados, no propelente propio E. Control de plasma y carga Gestión de sheath Prevención de arcos Control dinámico de potenciales 4. Definición formal de “Propulsión Inversa” 4.1 Modo Brake (IPSS-B) Se extrae energía cinética del viento solar, produciendo: Corriente eléctrica útil Incremento de transferencia de momento opuesto Frenado electromagnético controlado Formalmente:Δpplasma→Pel+Fdrag\Delta p_{plasma} \rightarrow P_{el} + F_{drag}Δpplasma→Pel+Fdrag 👉 Frenar = generar energía👉 No existe equivalente químico a esto. 4.2 Modo Boost (IPSS-A) Parte de la energía cosechada se usa para: Re-acelerar iones interceptados Expulsarlos direccionalmente Empuje:F=m˙ions⋅ΔvF = \dot{m}_{ions} \cdot \Delta vF=m˙ions⋅Δv Pero: m˙ions\dot{m}_{ions}m˙ions no proviene de tanques Proviene del flujo solar incidente 👉 Es un ram-augmented electric propulsion solar, sin masa almacenada. 5. Modos operativos integrados ModoFunciónConsumoUso típicoCruiseVela fotónica + E-sail pasivoMínimoTránsitos largosBrakeCosecha + drag plasmático0 propelenteInserciones, rendezvousBoostRe-aceleración iónicaEnergía cosechadaAjuste orbital activoParkEquilibrio empuje/frenoAutoestableObservación solar 6. Órdenes de magnitud (guía conceptual) Ejemplo híbrido Vela fotónica: 1 km² → ~9 N E-sail con R_eff = 10 km: A_eff ≈ 300 km² Empuje plasmático regulable: ~0.1–1 N Potencia eléctrica: decenas a cientos de W 👉 No compite con la vela: la complementa y controla. 7. Comparación con tecnologías existentes SistemaPropelenteEmpuje continuoFrenado activoEnergía propiaQuímicoSíNoNoNoIon clásicoSíSíLimitadoPanelesSolar sailNoSíNoNoE-sailNoSíParcialNoIPSS HelioSailNoSíSíSí 👉 IPSS es una clase nueva, no incremental. 8. Desafíos técnicos (reales y abordables) 8.1 Plasma & carga Arcos eléctricos Sputtering Inestabilidades sheath ✔ Solución: control adaptativo + materiales avanzados 8.2 Materiales Tethers ultraligeros y resistentes Superconductores (opcional) Recubrimientos anti-erosión 8.3 Control dinámico Torque fotónico vs torque plasmático Necesita GNC híbrido (campo + vela) 8.4 Variabilidad solar CME Turbulencia plasma ✔ Convertido en ventaja: más energía y empuje si se gestiona bien 9. Hoja de ruta tecnológica Fase A — Validación física CubeSat Mini E-sail Medición corriente vs drag Fase B — IPSS funcional 10–20 kg Re-aceleración iónica <200 W Cambio orbital medible Fase C — Vela híbrida 50–100 m Maniobras combinadas Parking solar estable Fase D — Operativa Misiones científicas Asteroides Observatorios solares Logística interplanetaria lenta pero permanente 10. Definición final (síntesis conceptual) HelioSpace IPSS no “usa” el Sol.Aprende a dialogar con él. No es una vela pasiva.No es un motor clásico.Es un sistema de intercambio inteligente de energía y momento con el entorno solar. Nombre final recomendado IPSS HelioSail™ Inverse-Propulsion Solar SailCapture. Convert. Maneuver. PATENT DRAFT — IPSS HelioSail Title Inverse-Propulsion Solar Sail System with Plasma Energy Harvesting and Directed Momentum Exchange Technical Field The present invention relates to space propulsion systems, and more particularly to non-propellant spacecraft propulsion, combining solar radiation pressure, solar wind plasma interaction, electromagnetic energy harvesting, and active momentum redirection. Background of the Invention Conventional spacecraft propulsion systems rely on stored propellant, resulting in limited mission duration, increased mass, and constrained maneuverability. Existing alternatives include: Solar sails, which exploit photon pressure but lack active braking or energy generation capability. Electric propulsion systems, which require stored propellant and external power sources. Electric solar sails (E-sails) and magnetic sails (magsails), which interact with the solar wind plasma but are typically passive and do not harvest energy for active thrust modulation. None of the existing systems provide a unified architecture capable of: harvesting energy from the solar wind, producing controllable braking forces, generating active thrust without onboard propellant, and dynamically managing momentum exchange with the heliospheric environment. Summary of the Invention The invention discloses an Inverse-Propulsion Solar Sail System (IPSS), herein referred to as HelioSail, which integrates: A photonic solar sail for continuous radiation-pressure propulsion. An electromagnetic plasma-interaction structure (electric sail, magnetic sail, or hybrid). A plasma energy harvesting subsystem converting induced plasma currents into electrical energy. A power processing and storage unit. An active ion re-acceleration and expulsion subsystem for directed momentum exchange. By extracting kinetic energy from the solar wind plasma, the system generates electrical power while simultaneously increasing momentum transfer opposing the plasma flow, producing a controlled inverse propulsion (braking) effect. The harvested energy may be selectively reused to actively re-accelerate captured ions, producing directed thrust without onboard reaction mass. Brief Description of the Drawings (indicative – drawings may include) Fig. 1: Overall architecture of the IPSS HelioSail spacecraft Fig. 2: Plasma interaction region and effective area inflation Fig. 3: Energy harvesting and power processing subsystem Fig. 4: Brake mode operation (inverse propulsion) Fig. 5: Boost mode operation (active plasma re-acceleration) Detailed Description of the Invention 1. Photonic Sail Subsystem A lightweight reflective membrane configured to generate thrust via solar radiation pressure. The sail may include variable reflectivity regions for attitude and torque control. 2. Plasma Interaction Subsystem The system includes one or more of the following: Electrically charged tethers extending radially from the spacecraft (electric sail). A current-carrying loop or superconducting ring generating a magnetic field (magnetic sail). Hybrid configurations combining electric and magnetic plasma interaction. These elements create an expanded plasma interaction sheath with an effective area significantly greater than the physical structure. 3. Plasma Energy Harvesting Subsystem As solar wind ions and electrons interact with the plasma sheath, electrical currents are induced. These currents are collected through: charge collectors, rectifiers, and controlled discharge paths, and converted into usable electrical power. 4. Power Processing and Storage Unit (PPU) The harvested energy is conditioned and routed to: onboard loads, energy storage devices (batteries or supercapacitors), plasma interaction control systems, and the active ion acceleration subsystem. 5. Active Ion Re-Acceleration Subsystem A portion of intercepted solar wind ions is selectively accelerated using electrostatic or electromagnetic acceleration grids and expelled in a controlled direction. The resulting momentum exchange produces net thrust aligned with the desired trajectory vector. 6. Operating Modes Cruise Mode Passive solar radiation and plasma interaction provide continuous thrust with minimal power consumption. Brake Mode (Inverse Propulsion) Energy is extracted from the incident plasma flow, increasing momentum transfer opposing spacecraft motion and producing controlled deceleration while generating electrical power. Boost Mode Stored or harvested energy is used to re-accelerate plasma ions, producing thrust without onboard propellant. Station-Keeping Mode Balanced photonic and plasma forces enable quasi-stationary positioning relative to the Sun. Advantages of the Invention Propellant-free thrust generation Active braking without fuel expenditure Onboard energy generation from solar wind plasma Reduced spacecraft mass Extended mission duration Enhanced orbital maneuverability Scalable architecture suitable for small satellites to deep-space probes Claims Claim 1 (Independent) A spacecraft propulsion system comprising: a photonic solar sail, an electromagnetic plasma interaction structure, a plasma energy harvesting subsystem, a power processing and storage unit, and an ion re-acceleration subsystem, wherein kinetic energy from solar wind plasma is converted into electrical energy and selectively redirected into controlled momentum exchange to produce propulsion or braking without onboard propellant. Claim 2 The system of claim 1, wherein the plasma interaction structure comprises electrically charged tethers forming an electric solar sail. Claim 3 The system of claim 1, wherein the plasma interaction structure comprises a magnetic field generated by a current-carrying loop or superconducting ring. Claim 4 The system of claim 1, wherein plasma energy harvesting increases momentum transfer opposing the plasma flow, producing an inverse propulsion braking force. Claim 5 The system of claim 1, wherein harvested energy is used to re-accelerate intercepted plasma ions to generate thrust in a selected direction. Claim 6 The system of claim 1, wherein operating modes include cruise, brake, boost, and station-keeping modes selectable during flight. Claim 7 The system of claim 1, wherein the effective plasma interaction area exceeds the physical sail area by at least one order of magnitude. Claim 8 The system of claim 1, wherein the system operates without stored reaction mass. Abstract An inverse-propulsion solar sail system integrates photonic propulsion, plasma interaction, plasma energy harvesting, and active ion re-acceleration to provide propellant-free thrust, braking, and energy generation. The system converts solar wind kinetic energy into electrical power and directed momentum exchange, enabling long-duration, fuel-free spacecraft navigation. SpaceArch Patent PATENT DRAFT — SATELLITE PATENT 02 Title Plasma Sheath Control and Solar Station-Keeping System for Non-Propellant Spacecraft Technical Field The present invention relates to spacecraft guidance, navigation, and control (GNC) systems, and more specifically to active plasma interaction control, solar station-keeping, and non-Keplerian orbit stabilization for spacecraft operating without onboard propellant. Background of the Invention Spacecraft operating near the Sun or in heliocentric orbits are subject to continuous perturbations caused by: solar radiation pressure, solar wind plasma variability, Coronal Mass Ejections (CMEs), electromagnetic interactions with the heliospheric environment. Existing station-keeping methods rely on: chemical thrusters, electric propulsion with stored propellant, or passive balancing of forces (e.g., classical solar sails). No known system provides adaptive, real-time control of the plasma interaction sheath surrounding a spacecraft to achieve stable or semi-stable station keeping using only ambient solar flux. Summary of the Invention The invention discloses a Plasma Sheath Control and Station-Keeping System (PSC-SKS) for spacecraft, particularly suited for integration with inverse-propulsion solar sail architectures. The system dynamically controls: electric potentials of charged tethers, magnetic field strength and topology, ion/electron collection and emission rates, to modulate the shape, density, and orientation of the plasma sheath, thereby producing controlled forces and torques that enable: solar station keeping, non-Keplerian hovering, precision orbital trimming, attitude stabilization without propellant expenditure. Brief Description of the Drawings (indicative) Fig. 1: Plasma sheath deformation under controlled electric potential gradients Fig. 2: Force vector balancing for solar station keeping Fig. 3: Adaptive control loop for plasma–spacecraft interaction Fig. 4: Response to solar wind variability and CME events Detailed Description of the Invention 1. Plasma Sheath Formation and Control The spacecraft generates an extended plasma sheath through one or more plasma interaction elements, including: electrically charged tethers, magnetic field generators, hybrid electro-magnetic structures. The spatial extent and geometry of the sheath are functions of: applied voltage, current flow, ambient plasma density and velocity. 2. Active Sheath Modulation The system includes a Plasma Control Unit (PCU) configured to: dynamically adjust tether voltages, modulate magnetic field intensity and orientation, bias ion/electron collection asymmetrically, thereby producing anisotropic plasma pressure around the spacecraft. This anisotropy results in net controllable forces and torques. 3. Solar Station-Keeping Mode In station-keeping mode, the system balances:Fphoton+Fplasma+FEM≈FgravityF_{\text{photon}} + F_{\text{plasma}} + F_{\text{EM}} \approx F_{\text{gravity}}Fphoton+Fplasma+FEM≈Fgravity By continuously adjusting plasma sheath parameters, the spacecraft maintains a quasi-stationary position relative to the Sun or along selected heliocentric vectors. 4. Non-Keplerian Orbit Stabilization The invention enables sustained trajectories that do not conform to classical Keplerian motion, including: artificial Lagrange-like points, displaced solar orbits, hovering at constant heliocentric distance. 5. Adaptive Control Loop The system operates within a closed-loop control architecture comprising: plasma sensors (density, velocity, temperature), electric and magnetic field sensors, onboard prediction algorithms, real-time actuation of plasma interaction parameters. This allows compensation for: solar wind fluctuations, transient plasma events, long-term drift. 6. CME Response and Safety Mode During extreme solar events, the system enters a protective modulation mode, altering plasma interaction geometry to: reduce structural loads, dissipate excess charge, maintain controllability. Advantages of the Invention Continuous station keeping without propellant Fine orbital control using ambient plasma Extended mission lifetime Compatibility with inverse-propulsion solar sail systems Scalable to various spacecraft sizes Enhanced resilience to solar variability Claims Claim 1 (Independent) A spacecraft control system comprising: a plasma interaction structure, a plasma sheath control unit, and a dynamic control loop, wherein spacecraft position and attitude are controlled by actively modulating plasma sheath geometry using ambient solar wind plasma without onboard propellant. Claim 2 The system of claim 1, wherein plasma sheath modulation is achieved by asymmetric voltage control of electrically charged tethers. Claim 3 The system of claim 1, wherein magnetic field topology is dynamically altered to shape plasma interaction forces. Claim 4 The system of claim 1, wherein the spacecraft maintains a non-Keplerian heliocentric position through continuous plasma force balancing. Claim 5 The system of claim 1, wherein the system compensates for solar wind variability and coronal mass ejections through adaptive sheath control. Claim 6 The system of claim 1, wherein the control system operates independently or in conjunction with an inverse-propulsion solar sail system. Claim 7 The system of claim 1, wherein no onboard propellant is consumed during station keeping operations. Abstract A plasma sheath control and station-keeping system enables spacecraft to maintain stable or quasi-stable heliocentric positions without onboard propellant by dynamically modulating plasma interaction forces using ambient solar wind. The system provides adaptive orbital and attitude control suitable for long-duration solar and deep-space missions. PATENT DRAFT — SATELLITE PATENT 03 Title Hybrid Photonic–Plasma Attitude and Torque Control System for Propellant-Free Spacecraft Technical Field The present invention relates to spacecraft attitude determination and control systems (ADCS), and more specifically to propellant-free attitude, torque, and rotational stability control using combined photonic radiation pressure and plasma interaction forces. Background of the Invention Conventional spacecraft attitude control relies on: reaction wheels, control moment gyroscopes, magnetic torquers, chemical or electric thrusters. These systems introduce limitations including: mechanical wear, saturation effects, mass and volume penalties, reliance on propellant or planetary magnetic fields. Solar sail spacecraft and plasma-interacting spacecraft typically lack fine, continuous, propellant-free torque control, especially under variable solar and plasma conditions. No known system provides integrated, continuous attitude and torque control by jointly modulating solar radiation pressure and plasma interaction asymmetries. Summary of the Invention The invention discloses a Hybrid Photonic–Plasma Attitude and Torque Control System (HPATCS) that enables continuous, precise, and propellant-free control of spacecraft attitude and rotational dynamics. The system exploits: asymmetric modulation of solar sail reflectivity, differential plasma sheath shaping, controlled electric and magnetic field gradients, to generate net torques and stabilizing moments about one or more spacecraft axes. The system may operate independently or in conjunction with inverse-propulsion solar sail and plasma station-keeping systems. Brief Description of the Drawings (indicative) Fig. 1: Photonic torque generation via variable reflectivity regions Fig. 2: Plasma-induced torque via asymmetric sheath modulation Fig. 3: Combined torque vectors and control axes Fig. 4: Closed-loop hybrid attitude control architecture Detailed Description of the Invention 1. Photonic Torque Generation Subsystem The spacecraft includes a photonic sail subdivided into multiple controllable regions having: variable reflectivity, variable absorptivity, or adjustable orientation. Differential radiation pressure across these regions generates controllable photonic torque. 2. Plasma-Induced Torque Generation Subsystem The spacecraft further includes plasma interaction elements configured to produce asymmetric plasma forces, including: differential voltage bias on individual tethers, asymmetric magnetic field configurations, controlled ion/electron emission or collection. These asymmetries result in net rotational moments acting on the spacecraft. 3. Hybrid Torque Vector Synthesis A Hybrid Attitude Control Unit (HACU) computes required torque vectors and allocates control authority between: photonic torque, plasma-induced torque, based on: environmental conditions, control authority availability, energy constraints. 4. Continuous Attitude Stabilization The system provides: three-axis stabilization, continuous torque without saturation, elimination of momentum buildup typical of reaction wheels. 5. Adaptive Control and Damping The system incorporates adaptive control laws to: damp oscillations, counteract external disturbances, compensate for solar wind variability and transient plasma events. 6. Safe Mode and Redundancy In the event of subsystem degradation, the system may: revert to photonic-only control, revert to plasma-only control, enter passive stabilization mode. Advantages of the Invention Propellant-free attitude control No moving mechanical parts No momentum saturation Continuous torque generation Long operational lifetime Compatibility with solar sail and plasma-based propulsion systems Scalable to various spacecraft sizes Claims Claim 1 (Independent) A spacecraft attitude and torque control system comprising: a photonic radiation pressure modulation subsystem, a plasma interaction modulation subsystem, and a hybrid control unit, wherein spacecraft attitude and rotational dynamics are controlled by coordinated asymmetric modulation of photonic and plasma forces without onboard propellant. Claim 2 The system of claim 1, wherein photonic torque is generated by variable reflectivity regions of a solar sail. Claim 3 The system of claim 1, wherein plasma-induced torque is generated by asymmetric voltage control of plasma interaction elements. Claim 4 The system of claim 1, wherein control authority is dynamically allocated between photonic and plasma torque sources. Claim 5 The system of claim 1, wherein the system provides three-axis attitude stabilization without reaction wheels. Claim 6 The system of claim 1, wherein the system operates continuously without momentum saturation. Claim 7 The system of claim 1, wherein the system is integrated with an inverse-propulsion solar sail system. Abstract A hybrid photonic–plasma attitude and torque control system enables continuous, propellant-free spacecraft attitude stabilization by coordinated asymmetric modulation of solar radiation pressure and plasma interaction forces. The system eliminates mechanical actuators and momentum saturation while providing long-duration, adaptive control in variable solar environments. PATENT DRAFT — SATELLITE PATENT 04 Title AI-Based Predictive Plasma–Photon Control Architecture for Autonomous Propellant-Free Spacecraft Technical Field The present invention relates to autonomous spacecraft control systems, and more specifically to artificial intelligence–driven predictive control of plasma interaction, photonic forces, attitude, propulsion, and station keeping in propellant-free spacecraft. Background of the Invention Spacecraft operating with solar radiation pressure and plasma interaction are subject to: stochastic solar wind variability, delayed sensor feedback, non-linear plasma–field coupling, transient extreme events (e.g., CMEs). Conventional feedback control systems are reactive, relying on local measurements and linearized models, resulting in: suboptimal control, delayed response, limited stability margins, inability to exploit forecastable heliospheric dynamics. No known system provides a predictive, learning-based control architecture capable of anticipating plasma and photonic force variations and proactively adjusting spacecraft interaction parameters. Summary of the Invention The invention discloses an AI-Based Predictive Plasma–Photon Control Architecture (AIPPCA) that enables autonomous, anticipatory control of spacecraft propulsion, braking, attitude, and station keeping. The system integrates: real-time plasma and photonic sensors, heliospheric data streams, onboard predictive AI models, adaptive control allocation across photonic and plasma subsystems. The architecture forecasts near-future environmental conditions and computes pre-emptive control actions, optimizing momentum exchange, stability, and energy harvesting without onboard propellant. Brief Description of the Drawings (indicative) Fig. 1: AI-based predictive control architecture Fig. 2: Sensor fusion and environmental forecasting pipeline Fig. 3: Predictive allocation of photonic vs plasma control authority Fig. 4: Autonomous response to CME and solar wind gradients Detailed Description of the Invention 1. Sensor Fusion Layer The system collects data from: plasma density, velocity, and temperature sensors, electric and magnetic field sensors, solar irradiance and spectral sensors, inertial and attitude sensors. These data streams are fused into a state vector representing the spacecraft–heliosphere interaction. 2. Predictive Modeling Layer An onboard AI module implements one or more of: machine learning regression models, recurrent neural networks, physics-informed neural networks (PINNs), hybrid AI–physics models. The module predicts future plasma and photonic force distributions over defined time horizons. 3. Control Policy Generation Based on predicted states, the AI generates optimized control policies for: tether voltages, magnetic field configurations, photonic sail reflectivity distribution, ion collection and emission rates. 4. Adaptive Learning and Update The system continuously compares predicted vs observed outcomes and updates internal models, improving accuracy over mission lifetime. 5. Autonomous Safety and Resilience Mode In response to predicted extreme solar events, the system preemptively enters protective configurations, redistributing loads and reducing exposure. Advantages of the Invention Anticipatory rather than reactive control Increased stability and efficiency Enhanced energy harvesting optimization Autonomous long-duration operation Reduced ground intervention Robustness against heliospheric variability Claims Claim 1 (Independent) An autonomous spacecraft control system comprising: a sensor fusion subsystem, a predictive artificial intelligence module, and a control allocation unit, wherein spacecraft photonic and plasma interaction parameters are proactively adjusted based on predicted heliospheric conditions without onboard propellant. Claim 2 The system of claim 1, wherein the predictive module incorporates physics-informed neural networks. Claim 3 The system of claim 1, wherein control policies are generated prior to environmental perturbation onset. Claim 4 The system of claim 1, wherein the system optimizes energy harvesting and momentum exchange simultaneously. Claim 5 The system of claim 1, wherein the system operates autonomously for extended mission durations. Abstract An AI-based predictive control architecture enables autonomous, anticipatory management of photonic and plasma interaction forces for propellant-free spacecraft. The system forecasts heliospheric conditions and proactively adjusts control parameters to optimize propulsion, braking, attitude, and station keeping. NUEVAS PATENTES ADICIONALES (ECOSISTEMA COMPLETO) A partir de lo que ya definiste, surgen naturalmente estas patentes nuevas, todas legítimas, no redundantes y altamente defensivas: PATENTE 05 — Plasma–Photon Energy Management OS Foco: sistema operativo energético que prioriza entre: cosecha, almacenamiento, empuje, protección. 👉 Protege el scheduler energético del IPSS. PATENTE 06 — CME-Aware Spacecraft Configuration System Foco: reconfiguración automática de: vela, tethers, campos,frente a CMEs y ráfagas solares. 👉 Muy fuerte para misiones solares cercanas. PATENTE 07 — Non-Keplerian Trajectory Design Using Plasma–Photon Fields Foco: método matemático y computacional para diseñar trayectorias no keplerianas persistentes. 👉 Protege el cómo se planifican las misiones IPSS. PATENTE 08 — Distributed Tether Intelligence Network Foco: tethers “inteligentes” con: sensores locales, control distribuido, comunicación interna. 👉 Cada tether como nodo de control. PATENTE 09 — Plasma-Assisted Formation Flying System Foco: múltiples naves IPSS que: comparten información plasma, se estabilizan mutuamente, vuelan en formación sin propelente. 👉 Ideal para observatorios solares distribuidos. PATENTE 10 — Self-Healing Plasma Interaction Structures Foco: detección y compensación de: roturas de tether, degradación de campo, asimetrías estructurales. 👉 Incrementa vida útil → valor comercial. © 2026 SpaceArch Solutions International, LLC, Miami, Florida, USA. All rights reserved. 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