An adaptive interstellar optimal navigation orbit and fingerprinting system based on celestial dynamic operation

Abstract

This invention discloses an adaptive interplanetary optimal navigation trajectory and fingerprint protection system based on the dynamic operation of celestial bodies, belonging to the field of aerospace orbit planning and intellectual property protection technology. The invention uses a flat space as the basic space model and constructs a multi-body gravitational vector superposition model based on the real-time dynamic operating parameters of the Sun, Earth, and the target celestial body. For the same target celestial body, multiple traversable paths are enumerated, dividing the trajectory into five levels. Using a straight chord in flat space as the calculation baseline, non-economical paths are allowed in local sections. Combining gravitational gaps and gravitational vortex flow fields, the invention differentially generates fuel-optimal and time-optimal navigation trajectories from a global perspective. Simultaneously, inherent orbital features are extracted to generate unique trajectory fingerprints, establishing a fingerprint database to achieve trajectory monitoring, feature comparison, infringement determination, and evidence preservation. This invention eliminates the limitations of fixed launch windows in traditional interplanetary navigation, achieving global navigation optimization through multi-path selection and combination. It is adaptable to different deep space exploration missions, can coordinate with on-orbit assembly and launch technology from space stations, and is applicable to aerospace engineering applications such as interplanetary exploration and manned interplanetary travel.

Description

Technical Field

[0001] This invention belongs to the fields of aerospace deep space exploration, orbital dynamics, celestial gravitational field analysis and intellectual property protection. Specifically, it relates to a method for orbit planning based on the real-time dynamic orbital trajectory of celestial bodies in the solar system, adaptively calculating dedicated interplanetary routes for different target planets, and without fixed launch windows, as well as a supporting trajectory fingerprinting and infringement protection system. It is applicable to aerospace missions such as interplanetary exploration, manned interplanetary travel, spacecraft, and deep space probes. Background Technology

[0002] Currently, global interplanetary exploration generally employs traditional fixed geodesic orbits, with the Hohmann transfer orbit being the mainstream application. However, this type of orbit has significant technical limitations in practical engineering applications. First, existing navigation routes are fixed arc-shaped orbits, offering strong versatility and typically being directly applied to various planetary exploration missions, making it impossible to customize dedicated routes for different target planets' gravitational environments. Second, the existing orbital system is constructed based on a single gravitational field geodesic theory, requiring missions to wait for planetary rendezvous cycles, resulting in a fixed launch window of approximately twenty-six months. This severely restricts launch time, preventing arbitrary launches. Third, traditional orbit calculation methods mostly use static celestial position parameters, offering only one path selection and lacking the ability to choose the best among multiple paths. This prevents dynamic adjustment of the navigation path based on mission requirements, resulting in travel time and fuel consumption not reaching globally optimal levels.

[0003] Meanwhile, existing aerospace orbital technologies lack dedicated intellectual property protection mechanisms, making original orbital planning schemes easily copied and used without authorization. The industry also lacks unique trajectory identification methods and infringement evidence collection techniques. Furthermore, existing technologies can only perform single-form orbital calculations and have not established a complete navigation system based on the dynamic gravitational superposition of multiple celestial bodies, multi-path optimization, and daily optimization, making it difficult to meet the development needs of high-precision, low-cost, and flexible deep space exploration. This invention relies on the applicant's four prior patents related to the fundamental theories of flat space and optical path deflection, and expands their engineering applications based on their unified theoretical framework, providing an adaptive interplanetary optimal navigation orbit based on celestial dynamic operation and a fingerprint-based rights protection system. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the existing technology and provide an adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on the dynamic operation of celestial bodies. Relying on the real-time dynamic operation trajectory of celestial bodies, it realizes a one-satellite-one-orbit and one-day-one-orbit navigation path planning method, dynamically selects the best among multiple feasible navigation paths, and achieves global navigation optimization; at the same time, it constructs a trajectory fingerprint rights protection system and improves the orbital intellectual property protection architecture. I. Core Technology Principles

[0005] This invention builds a technical system based on the theory of flat space, the principle of dynamic gravitational superposition of celestial bodies, the principle of adaptive positioning in gravitational gaps, and the principle of real-time solution for gravitational vortices: Outer space is flat, without spacetime curvature; the deflection of spacecraft trajectories is caused by the vector effect of celestial gravitational fields. Celestial bodies within the solar system continuously revolve, and the superposition of multiple celestial gravitational vectors, the gravitational gap space, and the gravitational vortex flow field are all dynamically changing; there is no permanently constant gravitational space. For the same target planet, there are numerous traversable paths in space, each with different energy consumption, duration, and attitude. Different target planets exhibit varying gravitational field environments, orbital parameters, and relative positions; independent calculations of flight paths are required for different target planets, and there is no universal fixed flight path. By updating orbital parameters daily based on the dynamic positions of celestial bodies, the limitation of fixed launch windows is eliminated, enabling routine launch scheduling. II. Complete Technical Solution

[0006] (I) Basic Navigation Path Layering System This invention establishes five basic navigation paths, clarifies the traffic characteristics of each path, and selects and combines multiple feasible paths to provide hierarchical support for dynamic optimal route planning. 1. Conventional gravitational geodesic orbit: This is an existing general-purpose arc transfer orbit, used only as a reference orbit for performance comparison; 2. Straight-line orbit in flat space theory: This is the shortest geometric path between two points in three-dimensional flat space and is only used as a baseline for orbit calculation. Due to the gravitational deflection of celestial bodies, this orbit is not considered the fuel-optimal orbit. 3. Celestial gravitational gap shortcut orbit: Locate the dynamic gap space formed by the mutual cancellation of the gravity of multiple celestial bodies, weaken the interference of gravitational deflection, and achieve near-straight-line navigation; 4. Multi-gravitational superposition vortex-assisted trajectory: Solve the dynamic gravitational vortex flow field and rely on the natural force of the gravitational field to achieve auxiliary acceleration; 5. Dynamically Coupled Optimal Orbit: Among multiple feasible navigation paths to the same target planet, the system combines and selects straight-line segments, narrow-slit segments, and vortex-assisted segments based on the celestial motion status of the day. It allows for the use of non-economical navigation paths in some sections, prioritizes global mission indicators, distinguishes between fuel-optimal and time-optimal navigation paths, and forms the final execution orbit that adapts to mission requirements.

[0007] (II) Core Calculation Rules 1. Basic parameter calculation: Collect real-time parameters of the target planet, the Sun, and the Earth's celestial mass, orbital coordinates, and orbital velocity, eliminate interference terms from distant weak gravitational objects, calculate the superposition field of the core celestial body's gravitational vector, and express the simplified calculation formula of the gravitational resultant force as: F_resultant = ΣF_gravity of the celestial body's particle.

[0008] 2. Dynamic airspace calculation: Based on the real-time gravitational resultant force calculation results, locate the gap airspace where the gravitational resultant force approaches zero on the day, determine the distribution range of the stable spiral gravitational vortex flow field, and divide multiple passable navigation paths.

[0009] 3. Optimal orbit synthesis calculation: Using a straight chordal orbit in flat space as the calculation benchmark, multiple passable navigation routes are enumerated; combined with the gravitational gap space and gravitational vortex points of the day, the navigation path is selected and matched according to the mission attributes; non-economic chordal paths are allowed in some sections in exchange for the optimal global navigation index; among them, the fuel-optimal orbit is used for material transportation missions, and the time-optimal orbit is used for manned exploration missions.

[0010] (III) Overall System Operation Steps 1. Customized planning for target planets: For different celestial bodies such as the Moon, Mars, Venus, and Jupiter, we independently build gravitational field calculation models, enumerate multiple passable navigation paths, set exclusive calculation constraints, and realize dedicated route planning for a single celestial body.

[0011] 2. Daily dynamic orbit calculation: Collect the real-time coordinates of the core celestial bodies of the solar system on the same day, update the distribution of gravitational gaps and gravitational vortices, filter and combine multiple feasible paths to generate a dedicated flight orbit for the day, eliminating the limitation of fixed launch windows.

[0012] 3. Spacecraft navigation control: Control the spacecraft to enter the optimal dynamic coupling orbit, and make reasonable use of straight chord sections, gap sections, and vortex leverage sections; in order to match the global optimal index, non-economical navigation paths can be used locally, and auxiliary acceleration can be completed by docking with the gravitational vortex at the preset time and space node, reducing active orbit change operations.

[0013] 4. Trajectory fingerprint modeling and rights protection: Extract the geometric curvature, gravitational space entry angle, flight sequence, and vortex docking point features of the optimal dynamically coupled trajectory, solidify and generate a unique trajectory fingerprint, and establish a fingerprint database; collect external flight trajectories through space-based observation systems and ground-based observation systems to complete feature comparison; when the matching degree reaches a preset threshold, it is determined to be an infringement, and the original calculation parameters and trajectory observation data are automatically retained as evidence for rights confirmation.

[0014] 5. Real-time iterative optimization of orbit: As the relative positions of celestial bodies change continuously, the spacecraft periodically updates the parameters of celestial bodies during its journey, fine-tunes the trajectory, and maintains the optimal global navigation state. III. Beneficial Effects of the Invention

[0015] 1. Achieving differentiated flight path planning: This invention independently constructs calculation models for different celestial bodies, enumerates multiple passable paths, forms a one-satellite-one-orbit planning mode, and optimizes the flight path by combining the dynamic position of the celestial body with daily updates of orbital parameters.

[0016] 2. Eliminate fixed launch window constraints: Based on the daily dynamic position of celestial bodies, the navigation trajectory is generated iteratively, and deep space exploration missions can be arranged at any time of the year, improving the flexibility of mission launch.

[0017] 3. Global-dimensional optimization of flight status: Distinguish between fuel-optimal orbits and time-optimal orbits to adapt to different space missions such as cargo transportation and manned exploration; allow non-economical flight paths in local sections, and achieve overall optimization of global energy consumption and duration through path combination and trade-offs.

[0018] 4. Establish a track intellectual property protection system: Set up a track fingerprint solidification mechanism to realize the unique identification of navigation tracks, track comparison, infringement determination and evidence preservation, and protect the rights and interests of original track designs.

[0019] 5. Adaptable to on-orbit launch space system: The navigation trajectory generated by this invention can be adapted to the on-orbit assembly and launch mode of the space station. The spacecraft does not need to pass through the atmosphere and can directly enter the interplanetary navigation trajectory, forming an integrated space architecture of on-orbit assembly, space launch, dynamic navigation and ownership protection. Detailed Implementation

[0020] The present invention will be further described in detail below with reference to specific embodiments: Mars was selected as the target celestial body for exploration. First, the masses, orbital inclinations, and instantaneous spatial coordinates of the Sun, Earth, and Mars were collected to build a dedicated Earth-Mars gravitational field calculation model. Multiple traversable paths between Earth and Mars were enumerated, and real-time operational parameters of the three core celestial bodies were collected on the day of exploration, eliminating gravitational interference from distant planets. The superposition values ​​of gravitational vectors within the navigation airspace were calculated, and the boundaries of gravitational gaps and acceleration points of gravitational vortices were marked. Using a straight chord in flat space as a baseline, paths were selected and combined according to mission requirements. For manned rapid exploration missions, non-economical chordal paths were used locally, increasing the navigation angle and prioritizing docking with high-intensity gravitational vortices to increase speed, synthesizing the time-optimal orbit. For cargo transport missions, navigation was performed close to gravitational gaps, abandoning high-speed paths, and synthesizing the fuel-optimal orbit. The spacecraft was launched from a near-Earth orbit space station and navigated stably along the planned route, with celestial coordinates updated periodically during navigation and the navigation attitude fine-tuned. Orbital features were extracted to generate a trajectory fingerprint, which was encrypted and stored in a database, completing the retention of trajectory ownership.

[0021] Orbit simulations have verified that, compared to the traditional Hohmann transfer orbit, the fuel-optimal mode in this embodiment reduces fuel consumption by more than 60%, and the time-optimal mode shortens the travel period by more than 40%, eliminating the need to wait for planetary rendezvous cycles. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the navigation trajectory hierarchy structure of the present invention; Figure 2This is a general flowchart of the overall workflow of the system of the present invention.

Claims

1. An adaptive interstellar optimal navigation trajectory and fingerprint rights protection system based on celestial dynamics, characterized in that, Includes the following steps: (1) For different target planets, establish independent and exclusive gravitational field calculation models, enumerate multiple passable navigation paths, and realize customized route planning for a single planet; (2) Based on the real-time dynamic coordinates of celestial bodies, calculate the superposition field of the gravitational vector of the core celestial body, locate the dynamic gravitational gap space and gravitational vortex flow field on the same day, and divide multiple passable navigation routes. (3) Based on the straight chord in flat space, multiple navigation paths are selected and combined, allowing non-economic chord paths to be used in local sections. Combined with gravitational gaps and gravitational vortices, fuel-optimal and time-optimal navigation trajectories are generated respectively, without waiting for a fixed launch window. (4) Solidify the unique characteristics of the dynamic optimal trajectory into a dedicated trajectory fingerprint, and realize trajectory comparison, infringement determination and patent protection through aerospace observation; (5) Real-time iterative calculation during navigation, fine-tuning the trajectory to maintain the global optimal navigation state.

2. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, The straight-line spatial chord orbit is only the geometric shortest path baseline. It is affected by the gravitational deflection of celestial bodies and is not a fuel-optimal or time-optimal orbit. It can be selectively used for local navigation segments.

3. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, The dynamically coupled optimal navigation trajectory is calculated independently for each target planet, and navigation trajectories for different planets are not interchangeable, thus achieving one orbit per planet.

4. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, The optimal flight path is updated iteratively every day, generating a new optimal path corresponding to the celestial position of that day, achieving one path per day.

5. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, The core calculations only collect real-time parameters from Earth, the Sun, and the target planet, ignoring interference from distant weak gravitational objects and simplifying the calculation of gravitational vector superposition.

6. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, The trajectory fingerprint includes orbital geometric curvature, gravitational space entry angle, flight sequence, and gravitational vortex docking point, and is unique, and can be used as direct evidence for infringement.

7. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, It can be linked with the gravity-free launch system assembled on the space station to achieve direct launch from space and direct entry into the dynamic optimal orbit of the day.

8. The adaptive interplanetary optimal navigation trajectory and fingerprint rights protection system based on celestial dynamic operation as described in claim 1, characterized in that, The entire voyage selects the best combination of multiple paths, allowing for some non-economical voyage segments, and relies on gravitational vortices to achieve natural boost, optimizing fuel consumption and voyage cycle from a global perspective.

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