水星環(huán)繞軌道動力學(xué)與控制研究
發(fā)布時間：2018-10-20 10:11
【摘要】：水星探測對研究太陽系演化和生命起源具有重要意義。水星是太陽系最內(nèi)側(cè)的行星，其公轉(zhuǎn)軌道有著不可忽略的偏心率，這就導(dǎo)致環(huán)繞水星的航天器會受到周期時變的太陽引力影響。本文特別針對這種軌道動力學(xué)環(huán)境，對水星環(huán)繞軌道的軌道動力學(xué)和軌道保持控制等問題進(jìn)行研究。 當(dāng)航天器在水星影響球內(nèi)運(yùn)行時，本文考慮了來自太陽的橢圓第三體攝動以及水星非球形攝動中的J2，J3項(xiàng)，對環(huán)繞軌道的動力學(xué)環(huán)境進(jìn)行建模。為研究軌道根數(shù)的長期變化趨勢，本文采用了Lie變換的方法對水星環(huán)繞軌道進(jìn)行雙平均化。平均化后系統(tǒng)降為單自由度系統(tǒng)，此時哈密頓正則方程的平動點(diǎn)即為通常意義上的凍結(jié)軌道。本文探討了航天器偏離目標(biāo)凍結(jié)軌道的軌道修正問題，在二體模型中針對同一軌道上的不同e相點(diǎn)，設(shè)計了轉(zhuǎn)移至新的目標(biāo)凍結(jié)軌道的軌道轉(zhuǎn)移方案，分析了不同相點(diǎn)上向凍結(jié)軌道進(jìn)行軌道轉(zhuǎn)移的可行性和能量消耗，而后將軌道轉(zhuǎn)移方案在攝動條件下加以修正。 凍結(jié)軌道的存在條件有限，不一定能夠滿足實(shí)際任務(wù)的約束。因此，，本文提出了一種基于平均化模型和參數(shù)優(yōu)化的連續(xù)小推力控制律，通過連續(xù)推力調(diào)節(jié)每種攝動的大小以使其符合凍結(jié)軌道的存在條件，實(shí)現(xiàn)水星環(huán)繞軌道的人工凍結(jié)。本文選取了與每項(xiàng)攝動相關(guān)的偽攝動參數(shù)作為待優(yōu)化參數(shù)，并推導(dǎo)了人工凍結(jié)軌道的凍結(jié)條件及約束方程，搜尋最優(yōu)的偽攝動參數(shù)，以使軌控效率達(dá)到最佳。通過大范圍的仿真算例，本文分析了偽攝動參數(shù)隨相關(guān)軌道根數(shù)的演化情況，并對本方法的可行性進(jìn)行評估。 最后，本文研究了環(huán)繞水星的高軌準(zhǔn)周期軌道。這類軌道的尺寸極大且不具有嚴(yán)格意義上的周期性，有些軌道大大超出水星影響球半徑的大小。為此，本文將在太陽-水星系統(tǒng)所對應(yīng)的橢圓限制性三體問題下對高軌準(zhǔn)周期軌道進(jìn)行探討。本文根據(jù)水星動力學(xué)環(huán)境和航天任務(wù)需求，定義了水星高軌準(zhǔn)周期軌道，利用同倫法從圓限制性三體問題中的逆行和順行周期軌道族出發(fā)，逐漸提高橢圓限制性三體系統(tǒng)中的偏心率，最終求得太陽-水星系統(tǒng)中的高軌準(zhǔn)周期軌道。最后，本文研究了這類準(zhǔn)周期軌道較長期運(yùn)行的穩(wěn)定性。
[Abstract]:Mercury exploration is of great significance in studying the evolution of the solar system and the origin of life. Mercury is the innermost planet in the solar system, and its orbit has an unnegligible eccentricity, which causes the spacecraft orbiting Mercury to be influenced by the periodic time-varying solar gravity. In this paper, the orbit dynamics and orbit retention control of Mercury orbit are studied especially in this orbit dynamic environment. When the spacecraft is operating in the sphere of influence of Mercury, the elliptical third body perturbation from the sun and the J _ 2N _ J _ 3 term in the non-spherical perturbation of Mercury are considered in this paper, and the dynamic environment around the orbit is modeled. In order to study the long-term variation trend of orbital root number, the Lie transform is used to double average the orbit around Mercury. When the system is reduced to a single degree of freedom system after averaging, the translational point of the Hamiltonian canonical equation is the frozen orbit in the usual sense. In this paper, the orbit correction problem of spacecraft deviating from the frozen orbit of the target is discussed. For different e phase points in the same orbit in the two-body model, an orbit transfer scheme is designed to transfer to the new frozen orbit of the target. The feasibility and energy consumption of orbit transfer to frozen orbit at different phase points are analyzed, and then the orbital transfer scheme is modified under perturbation condition. The existence condition of frozen orbit is limited, which can not satisfy the constraint of actual task. Therefore, this paper presents a continuous small thrust control law based on averaging model and parameter optimization, which adjusts the size of each perturbation through continuous thrust to make it conform to the existence condition of frozen orbit, and realizes the artificial freezing of Mercury orbit. In this paper, the pseudo-perturbation parameters associated with each perturbation are selected as the parameters to be optimized, and the freezing conditions and constraint equations of the artificial frozen orbit are derived, and the optimal pseudo-perturbation parameters are searched for the optimal orbit control efficiency. In this paper, the evolution of pseudo-perturbation parameters with the root number of related orbits is analyzed by a large range of simulation examples, and the feasibility of this method is evaluated. Finally, the high-orbit quasi-periodic orbit around Mercury is studied. These orbits are large in size and do not have a strict periodicity, and some orbits far exceed the radius of the sphere affected by Mercury. Therefore, in this paper, the quasi-periodic orbit of high orbit is discussed under the elliptic restricted three-body problem corresponding to the sun-Mercury system. According to the dynamic environment of Mercury and the requirements of space mission, the quasi-periodic orbit of Mercury in high orbit is defined in this paper. The homotopy method is used to start from the family of retrograde and anteroposterior periodic orbits in the circular restricted three-body problem. The eccentricity of elliptical restricted three-body system is gradually increased, and the quasi-periodic orbit of high orbit in the Sun-Mercury system is finally obtained. Finally, the stability of this kind of quasi-periodic orbit is studied.
【學(xué)位授予單位】：清華大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2013
【分類號】：P173
本文編號：2282831
[Abstract]:Mercury exploration is of great significance in studying the evolution of the solar system and the origin of life. Mercury is the innermost planet in the solar system, and its orbit has an unnegligible eccentricity, which causes the spacecraft orbiting Mercury to be influenced by the periodic time-varying solar gravity. In this paper, the orbit dynamics and orbit retention control of Mercury orbit are studied especially in this orbit dynamic environment. When the spacecraft is operating in the sphere of influence of Mercury, the elliptical third body perturbation from the sun and the J _ 2N _ J _ 3 term in the non-spherical perturbation of Mercury are considered in this paper, and the dynamic environment around the orbit is modeled. In order to study the long-term variation trend of orbital root number, the Lie transform is used to double average the orbit around Mercury. When the system is reduced to a single degree of freedom system after averaging, the translational point of the Hamiltonian canonical equation is the frozen orbit in the usual sense. In this paper, the orbit correction problem of spacecraft deviating from the frozen orbit of the target is discussed. For different e phase points in the same orbit in the two-body model, an orbit transfer scheme is designed to transfer to the new frozen orbit of the target. The feasibility and energy consumption of orbit transfer to frozen orbit at different phase points are analyzed, and then the orbital transfer scheme is modified under perturbation condition. The existence condition of frozen orbit is limited, which can not satisfy the constraint of actual task. Therefore, this paper presents a continuous small thrust control law based on averaging model and parameter optimization, which adjusts the size of each perturbation through continuous thrust to make it conform to the existence condition of frozen orbit, and realizes the artificial freezing of Mercury orbit. In this paper, the pseudo-perturbation parameters associated with each perturbation are selected as the parameters to be optimized, and the freezing conditions and constraint equations of the artificial frozen orbit are derived, and the optimal pseudo-perturbation parameters are searched for the optimal orbit control efficiency. In this paper, the evolution of pseudo-perturbation parameters with the root number of related orbits is analyzed by a large range of simulation examples, and the feasibility of this method is evaluated. Finally, the high-orbit quasi-periodic orbit around Mercury is studied. These orbits are large in size and do not have a strict periodicity, and some orbits far exceed the radius of the sphere affected by Mercury. Therefore, in this paper, the quasi-periodic orbit of high orbit is discussed under the elliptic restricted three-body problem corresponding to the sun-Mercury system. According to the dynamic environment of Mercury and the requirements of space mission, the quasi-periodic orbit of Mercury in high orbit is defined in this paper. The homotopy method is used to start from the family of retrograde and anteroposterior periodic orbits in the circular restricted three-body problem. The eccentricity of elliptical restricted three-body system is gradually increased, and the quasi-periodic orbit of high orbit in the Sun-Mercury system is finally obtained. Finally, the stability of this kind of quasi-periodic orbit is studied.
【學(xué)位授予單位】：清華大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2013
【分類號】：P173
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