Dependent test satellite suitable for deep space exploration flight mission
By designing the Pathfinder Test Star Orbit with low orbit inclination, avoiding the Van Allen radiation belt, the problem of the inconsistency between the existing test star orbit and the deep space environment was solved, and payload verification and cost savings were achieved.
Patent Information
- Application Number
- CN202510415234.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-03
- Publication Date
- 2025-07-18
AI Technical Summary
The orbits of the existing test satellites are affected by the Van Allen radiation belt, resulting in their characteristics being inconsistent with the actual deep space orbit environment, affecting the effectiveness of load function verification and increasing the launch cost.
Design a non-Low Earth orbit Pathfinder test star, adopting low-orbit inclination orbit parameters (15° inclination, orbital height 71,000km), to avoid the influence of the Van Allen radiation belt, and can be launched with GEO or IGSO satellites.
The consistency between the Pathfinder test star orbit and the deep space orbit environment was achieved, the radiation impact of Van Allen belt was reduced, the risk of space collision and launch costs were reduced, and the load function was ensured effectively.
Smart Images
Figure CN120333470A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of satellite control technology, and particularly to a pathfinder test satellite suitable for deep space exploration flight missions.
Background Art
[0002] Detectors for deep space exploration flight missions usually have complex functions and expensive payload single machines, and the total budget for the entire flight mission is huge. Therefore, the project team usually conducts a verification work on a pathfinder test satellite in the initial stage of the deep space exploration project to ensure the functionality and performance completeness of the payload of the deep space exploration project.
[0003] The existing test satellite orbits are usually affected by the Van Allen radiation belt, and some characteristics are inconsistent with the actual deep space orbit environment.
[0004] The Van Allen radiation belt is a region of high-energy particle radiation near the Earth, formed by solar wind charged particles trapped by the Earth's magnetic field, posing a potential threat to spacecraft and astronauts. The Van Allen radiation belt is a high-energy particle radiation belt surrounding the Earth, mainly composed of high-energy electrons (a few megaelectron volts) and protons (a few hundred megaelectron volts) trapped by the Earth's magnetic field, with a small amount of heavy particles.
[0005] Inner belt: Approximately 1,500 - 5,000 kilometers from the Earth's surface, mainly composed of high-energy protons.
[0006] Outer belt: Approximately 13,000 - 20,000 kilometers from the Earth's surface, mainly composed of high-energy electrons.
[0007] Van Allen belt slot: The gap between the inner and outer belts, with less radiation, is the "safe passage" for spacecraft.
[0008] Pathfinder test satellite:
[0009] Space astronomy, an optical telescope with high imaging quality, high stability, and low distortion, including an optical system, a focal plane, a temperature controller, a frequency-stabilized laser, and a data processing system, belonging to the satellite of the Closeby Habitable Exoplanet Survey (CHES); Scientific mission:
[0010] 1. Search for habitable zone terrestrial planets
[0011] Search for terrestrial planets in the habitable zone in the near neighborhood of the solar system (within 10 pc), and expect to be the first in the world to discover terrestrial planets in the habitable zone of nearby solar-like stars.
[0012] 2. Census of nearby planets in the solar system
[0013] Census of exoplanet systems within 10 pc with orbital periods between 30 days and 10 years and more than 1 Earth mass, and comprehensively give the physical parameters and orbital parameters of the planets for the first time. Establish a complete database of nearby exoplanets.
[0014] In view of the technical problem that the satellite orbits of existing test satellites are usually affected by the Van Allen radiation belt and some characteristics are inconsistent with the actual deep-space orbit environment, the present invention has made technical improvements to the pathfinder test satellite suitable for deep-space exploration flight missions.
Summary of the Invention
[0015] The object of the present invention is to propose a pathfinder test satellite suitable for deep-space exploration flight missions, whose satellite orbit is not affected by the Van Allen radiation belt and is consistent with the actual deep-space orbit environment.
[0016] To achieve the above object, the technical solution adopted by the present invention is a pathfinder test satellite suitable for deep-space exploration flight missions. The satellite orbit of the pathfinder test satellite is a non-low-Earth orbit that avoids the influence of the Van Allen radiation belt and is a low orbit inclination that is protected from strong space radiation.
[0017] Preferably, the satellite orbit of the pathfinder test satellite has an orbit inclination of 15° and an orbit altitude of 71,000 km.
[0018] Preferably, the deep-space exploration flight mission is a search flight mission for Earth-like planets in the habitable zone and / or a census flight mission for nearby planets in the solar system.
[0019] Preferably, the pathfinder test satellite suitable for deep-space exploration flight missions is launched by piggybacking with other GEO or IGSO satellites.
[0020] The pathfinder test satellite suitable for deep-space exploration flight missions of the present invention has the following beneficial effects: 1. The orbit of the pathfinder test satellite has the advantage of not being affected by the Van Allen belt radiation; 2. The orbit of the pathfinder test satellite is consistent with the characteristics of the space radiation environment of the deep-space orbit that is not affected by the Van Allen belt radiation, which is conducive to carrying out effective payload function and performance verification; 3. It can be launched by piggybacking with GEO or IGSO satellites, and the launch cost is relatively economical; 4. It minimizes the risk of space collisions.
Brief Description of the Drawings
[0021] Figure 1 It is a schematic diagram of a pathfinder test satellite suitable for deep-space exploration flight missions.
[0022] Figure 2 It is a schematic diagram of the electron distribution of the radiation belt of the satellite orbit of a pathfinder test satellite suitable for deep-space exploration flight missions.
[0023] Figure 3 It is a schematic diagram of the proton distribution of the radiation belt of the satellite orbit of a pathfinder test satellite suitable for deep-space exploration flight missions.
[0024] Figure 4 It is a schematic diagram of the solar proton distribution of the satellite orbit of a pathfinder test satellite suitable for deep-space exploration flight missions.
[0025] Figure 5 It is a schematic diagram of the solar plasma distribution in the orbit of the pathfinder test star satellite suitable for deep space exploration flight missions.
[0026] Figure 6 It is a schematic diagram of the cosmic ray particle distribution in the orbit of the pathfinder test star satellite suitable for deep space exploration flight missions.
[0027] Figure 7 It is a schematic diagram of the total radiation dose curve in the orbit of the pathfinder test star satellite suitable for deep space exploration flight missions.
Specific implementation manners
[0028] The present invention will be further described below in conjunction with embodiments and with reference to the accompanying drawings.
[0029] Embodiment 1
[0030] This embodiment realizes a pathfinder test star suitable for deep space exploration flight missions.
[0031] The orbit where the deep space detector is located usually needs to avoid being covered by the Van Allen radiation belt, that is, to minimize the influence of the Earth's radiation belt.
[0032] Figure 1 It is a schematic diagram of a pathfinder test star suitable for deep space exploration flight missions. As Figure 1 shown, in order to ensure the effectiveness of the verification of the pathfinder test star, the working orbit of the pathfinder test star is selected to avoid the influence of the Van Allen radiation belt as much as possible in this embodiment. The Van Allen belts are two huge concentric circles surrounding the Earth, running through the space range approximately 1600 km to 32000 km above the Earth's surface, and the covered latitude range is roughly between 40° and 50° north and south latitudes. Considering that the near-Earth space of the Earth has been covered by a large number of commercial satellites, in the near-Earth space orbit, each spacecraft will almost every day encounter the embarrassing situation of a space target approaching within 5 km, and there is a huge risk of space collision. Therefore, the working orbit of the pathfinder test star is preferably selected as a non-near-Earth orbit as much as possible in this embodiment. This embodiment proposes a satellite orbit of a pathfinder test star suitable for deep space exploration flight missions from the characteristics of deep space exploration spacecraft and in combination with the distribution characteristics of current space vehicles to ensure the verification effectiveness of the pathfinder test star.
[0033] In view of the distribution characteristics of the Van Allen radiation belts: the altitude is approximately 1600 km to 32000 km, and the latitude is roughly from 40° to 50° north and south. At the same time, considering that a low orbital inclination is beneficial to avoiding strong space radiation, therefore, the satellite orbit of the pathfinder test satellite preferably selects a geosynchronous orbit with a low inclination. The specific orbital parameters include: the orbital inclination is 15°; the orbital altitude is 71000 km. The advantages of the pathfinder experimental satellite in this embodiment are: it can be launched together with other GEO or IGSO satellites to save the launch cost; secondly, no deorbiting operation is required at the end of the satellite's life; since the satellite uses a high-orbit with a low inclination, the orbital position resources are abundant; in addition, the space environment where this orbit is located basically avoids the direct radiation effect of the Van Allen belts.
[0034] Taking the epoch of 0:0:0:0 UTC on January 1, 2028 as an example, considering the test satellite's life span of 2 years, the SPENVIS software was used to perform simulation calculations on the space environment of the pathfinder test satellite in this embodiment.
[0035] Figure 2 It is a schematic diagram of the electron distribution in the radiation belts of the satellite orbit of the pathfinder test satellite suitable for deep space exploration flight missions. Figure 3 It is a schematic diagram of the proton distribution in the radiation belts of the satellite orbit of the pathfinder test satellite suitable for deep space exploration flight missions. Figure 4 It is a schematic diagram of the solar proton distribution in the satellite orbit of the pathfinder test satellite suitable for deep space exploration flight missions. Figure 5 It is a schematic diagram of the solar plasma distribution in the satellite orbit of the pathfinder test satellite suitable for deep space exploration flight missions. Figure 6 It is a schematic diagram of the cosmic ray particle distribution in the satellite orbit of the pathfinder test satellite suitable for deep space exploration flight missions. Figure 7 It is a schematic diagram of the total radiation dose curve of the satellite orbit of the pathfinder test satellite suitable for deep space exploration flight missions. As Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 、 Figure 6 、 Figure 7 shown, the simulation results of the space environment characteristic parameters of the pathfinder test satellite in this embodiment within 2 years are given respectively. Among them Figure 2 、 Figure 3 confirm that the satellite orbit selected for the pathfinder test satellite in this embodiment has completely avoided the radiation effect of the Van Allen belts, which is consistent with the characteristics of the space environment where deep space detectors are actually located and is not affected by the Van Allen radiation belts.
[0036] The innovation of the pathfinder experimental satellite in this embodiment lies in:
[0037] The satellite orbit of the pathfinder test satellite in this embodiment has the advantage of not being affected by the radiation of the Van Allen belts;
[0038] In this embodiment, the space radiation environment of the Pathfinder test satellite's orbit and deep space orbit is consistent with the characteristic of being unaffected by the Van Allen belt radiation, which is conducive to carrying out effective payload function and performance verification;
[0039] In this embodiment, the Pathfinder test satellite can be launched by piggybacking on a GEO (Geostationary Orbit) or IGSO (Inclined Geosynchronous Orbit) satellite, and the launch cost is relatively economical;
[0040] Minimize the risk of space collisions.
[0041] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art of this technology, without departing from the principle of the present invention, several improvements and supplements can still be made, and these improvements and supplements should also be regarded as the protection scope of the present invention.
Claims
1. A pathfinder test satellite suitable for deep space exploration flight missions, characterized in that: The satellite orbit of the Pathfinder test satellite is a non-low Earth orbit that avoids the influence of the Van Allen radiation belt and a low orbit inclination that is immune to strong space radiation.
2. The pathfinder test satellite suitable for deep space exploration flight missions according to claim 1, characterized in that: The satellite orbit of the Pathfinder test satellite has an orbit inclination of 15° and an orbit altitude of 71,000 km.
3. The pathfinder test satellite suitable for deep space exploration flight missions according to claim 1, characterized in that: The deep space exploration flight mission is a search flight mission for Earth-like planets in the habitable zone and / or a census flight mission for nearby planets in the solar system.
4. The pathfinder test satellite suitable for deep space exploration flight missions according to claim 1, characterized in that: It is launched piggyback with other GEO or IGSO satellites.