Precise orbit determination and astrometric ranging method based on equivalent optical path bending correction of celestial motion point position offset

Abstract

This invention discloses a precise orbit determination and astronomical ranging method based on equivalent optical path bending correction using celestial body motion position offset, relating to the fields of aerospace telemetry and control and astronomical observation technology. This invention is based on the premise that light always travels in a straight line, abandoning the traditional approach of modeling light beams by gravitational self-deflection and spacetime curvature. It utilizes the fixed duration of light propagation, during which high-speed motion of celestial bodies generates misalignment of transmission and reception points, forming a real physical mechanism of equivalent optical path bending at the measurement level. The method models and calculates the offset and time delay corresponding to the equivalent bending, corrects errors in the original measured data, calculates the true absolute position of the target, deduces the orbit, and implements pre-orbit compensation for the satellite. This invention conforms to objective physical laws, has high correction accuracy, significantly reduces the frequency of satellite orbit fine-tuning, saves fuel and manual maintenance costs, requires no hardware modifications, and can be widely applied in aerospace telemetry and control, deep space exploration, and astronomical observation.

Description

Technical Field

[0001] This invention relates to the fields of aerospace telemetry and control, satellite orbit control, deep space exploration and astronomical observation. Specifically, it relates to a method for accurately calculating the absolute position of spacecraft and celestial bodies, predicting long-term orbits, and maintaining stable on-orbit operation by modeling and correcting the equivalent bending deviation caused by the misalignment of the transmitting and receiving points due to the straight-line propagation of light itself. Background Technology

[0002] Currently, in the fields of space launch tracking and control, satellite on-orbit management, deep space probe positioning, and astronomical observation, existing technologies have inherent limitations in both understanding and technology: The prevailing industry understanding and correction logic holds that light is physically deflected and its propagation path is bent by gravity during its propagation, and a fixed constant is used for micro-compensation correction based on the theory of spacetime curvature.

[0003] However, the actual objective laws of physics are as follows: light always travels along a straight trajectory in a vacuum environment, and the propagation path of the photon itself does not bend; due to the extremely high speeds of celestial bodies such as satellites, launch vehicles, stars, and galaxies, there is a finite propagation time from the moment of emission to the moment of reception by the ground or observation end. During this time, the launching carrier itself has undergone spatial displacement along its orbit, resulting in a significant spatial misalignment between the initial emission point and the actual position of the carrier at the moment of reception; when the observation end traces back in the reverse direction from the receiving position, an equivalent bending of the light path is formed at the visual and measurement levels, rather than the light propagation path itself being bent by gravity.

[0004] Existing technologies fail to recognize this physical nature, confusing two completely different mechanisms: "physical deflection of light itself" and "equivalent optical path bending caused by the displacement of celestial bodies' motion points." Directly using uncorrected raw optical and electromagnetic measurement data to calculate positions and orbits will produce systematic measurement biases and will be unable to distinguish between the actual orbital drift of celestial bodies and the virtual observation offset caused by the equivalent optical path bending.

[0005] Due to the aforementioned defects, satellites in orbit need to frequently perform orbital fine-tuning maneuvers, consuming a large amount of on-orbit fuel and shortening their service life. At the same time, a large amount of manpower is required to carry out observation data fitting, deviation identification and correction command compilation, which increases the cost of space operation. In the field of astronomical observation, there are problems such as inaccurate celestial distance measurement, spatial positioning deviation, and distortion of orbital trajectory reconstruction, and there is a lack of a complete equivalent optical path bending correction scheme that fits the real physical mechanism. Summary of the Invention

[0006] Purpose of the invention This invention addresses the cognitive biases and shortcomings of existing technologies by proposing a precise orbit determination and astronomical ranging method based on equivalent optical path bending correction of celestial motion point position offset. Based on the real physical mechanism of light propagating in a straight line and the misalignment of transmitting and receiving points caused by high-speed celestial motion, resulting in equivalent optical path bending, the method models and calculates the measurement deviation caused by equivalent bending and completes the correction of measured data. This yields the true absolute position of the target, enabling long-term accurate orbit prediction and pre-compensation. This reduces the frequency of satellite orbital maneuvers, lowers fuel consumption and manual maintenance inputs, and simultaneously improves the data calculation accuracy of aerospace telemetry and astronomical observations.

[0007] The universe is a flat space, and time follows an absolute time standard; light always maintains its straight-line propagation characteristics in a vacuum environment without interference, and the propagation trajectory of photons does not undergo physical bending or gravitational deflection.

[0008] Celestial bodies, satellites, and detectors all have high-speed operation characteristics, and light has a fixed propagation time. At the moment of light emission, the carrier is at the initial spatial point. By the time the light propagates to the observation and receiving end, the carrier has moved to a new spatial point, and the origin of light emission and the real-time carrier position are spatially misaligned.

[0009] When the observation end uses the reverse tracing of the received signal to locate the source, the spatiotemporal misalignment of the transmitting and receiving points will create an equivalent optical path bending effect at the measurement level. This equivalent bending is the core source of errors in the positioning and ranging system, and is not the bending of the light's own propagation path.

[0010] By modeling and solving the position offset and signal propagation delay corresponding to the equivalent optical path bend, and by correcting the errors in the original measured observation data, the true absolute spatial position and orbit of the carrier or celestial body can be calculated. Specific implementation steps

[0011] The acquisition of fundamental parameters of celestial motion and gravity involves collecting the orbital parameters, linear velocity, spatial orientation, and light propagation distance and duration of the target satellite, rocket, deep space probe, or astronomical object to establish a time-series motion model of the target celestial object.

[0012] The calculation of temporal point offset and equivalent optical path characteristic quantity is combined with the light propagation time and the celestial velocity to estimate the initial position of the light emission time and the real-time position of the receiving time, and to calculate the equivalent optical path bending angle, position offset and signal propagation delay caused by the spatiotemporal misalignment of the two points. This step can be implemented by a variety of equivalent technical paths. All technical methods that can realize the above-mentioned temporal point offset estimation and equivalent optical path characteristic quantity calculation are included in the scope of protection of this invention. Exemplary implementation methods include: (1) using Riemannian geometry to model the continuous trajectory of the temporal point connection, fitting the equivalent optical path bending characteristics, and calculating the position offset and delay parameters segment by segment; (2) using classical kinematics combined with plane analytical geometry, calculating the celestial displacement segment by segment according to the light propagation time, and summing to solve the total misalignment of the transmitting and receiving points and the equivalent optical path deviation.

[0013] The original measured data error correction obtains the original measured azimuth, distance, and time data of optical or electromagnetic signals, deducts the position offset and propagation delay caused by the equivalent optical path bend, and eliminates the systematic errors caused by spatiotemporal misalignment to obtain the corrected real observation data.

[0014] Absolute position calculation and orbit pre-compensation are based on corrected real observation data to calculate the absolute spatial position of the target carrier or celestial body and fit and extrapolate the medium- and long-term operating orbits. For satellites in orbit, a one-time pre-compensation is performed based on accurate orbit prediction to reduce the need for subsequent high-frequency small-scale orbit fine-tuning.

[0015] This method can be applied to various engineering scenarios. It is implemented only through the background data calculation algorithm and does not require modification of existing satellite, rocket, or ground telemetry and control hardware. It can be adapted to scenarios such as launch and orbit control of launch vehicles, on-orbit positioning and orbit maintenance of satellites in various orbits, interstellar positioning of deep space probes, and astronomical ranging and trajectory correction of stars and galaxies.

[0016] It fully conforms to the real physical mechanism, abandons the erroneous modeling logic of traditional light deflection due to gravity and spacetime curvature, and takes the straight-line propagation of light + the misalignment of celestial motion points + equivalent light path bending as the core modeling basis, thus eliminating system measurement errors at the source.

[0017] By accurately correcting equivalent optical path deviations and providing advance compensation for long-term orbital predictions, the number of on-orbit orbital maneuvers can be effectively reduced, fuel consumption can be decreased, and the on-orbit service life of the satellite can be extended.

[0018] This simplifies the workload of manual identification, repeated fitting, and deviation correction of ground-based telemetry and control data, streamlines the telemetry and control process, and reduces the cost of manual maintenance and overall operation of spacecraft in orbit.

[0019] The technology upgrade is achieved at the pure algorithm level, without the need to modify existing space payloads, telemetry and control base stations, and observation hardware. It has good adaptability and can be quickly deployed and promoted.

[0020] The solution defines a unique physical mechanism, a complete correction process, and multiple equivalent calculation implementation paths, covering various alternative technical implementation methods under the same principle. Regardless of the mathematical modeling or calculation method used, as long as the temporal point offset estimation and equivalent optical path characteristic quantity calculation defined by this invention are achieved, they are included in the protection scope of this invention. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram illustrating the principle of equivalent optical path bending in an embodiment of the present invention. Figure 2 : This is an overall flowchart of the technical method in the embodiments of the present invention.

Claims

1. A method for precise orbit determination and astrometric ranging based on equivalent optical path bending correction of celestial body motion point position offset, characterized in that, Includes the following steps: (1) Collect the orbital parameters, speed and light propagation path parameters of the target celestial body or spacecraft, and establish a target time-series motion model; (2) Calculate the initial position at the launch time and the real-time position at the receiving time based on the propagation time of the light, and calculate the equivalent optical path bending offset and signal propagation delay caused by the misalignment of the spatiotemporal position; (3) Collect the original measured data of the target's optical or electromagnetic signals, and use the equivalent optical path bending offset and delay to correct the error of the original measured data to obtain the real observation data; (4) Calculate the absolute position of the target in space based on the real observation data, deduce the target's orbit, and perform orbit pre-compensation for the satellite in orbit.

2. The method of claim 1, wherein: In step (2), the equivalent optical path bending offset and propagation delay can be achieved using various technical approaches. All technical methods that can complete the calculation of time-series point offset and the calculation of equivalent optical path characteristic quantities are within the scope of protection of this invention. Specifically, the calculation can be performed using Riemannian geometric continuous trajectory modeling, or by using classical kinematics combined with planar analytical geometry piecewise displacement fitting.

3. The method of claim 1, wherein: Light always travels in a straight line in a vacuum environment, and its own propagation path does not undergo physical bending; the so-called equivalent light path bending is caused by the misalignment of the sending and receiving points in spacetime due to the high-speed motion of celestial bodies within the propagation time of the light, and is not caused by the gravitational deflection of the light itself or the curvature of spacetime.

4. The method of claim 1, wherein: This method is applicable to various scenarios including launch tracking and control of carrier rockets, on-orbit positioning and orbit maintenance of various orbital satellites, interstellar positioning of deep space probes, and ranging and trajectory correction of astronomical objects.

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