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jl032
航天器
轨道
机动
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钻研
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【JL032】航天器轨道机动研究,jl032,航天器,轨道,机动,研究,钻研
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毕业论文英文翻译 专业名称 自动化 学生姓名 党 炫 学 号 103589 班 号 191002 指导老师 谭明虎 英文原文：The spacecraft orbit maneuver With the development of space technology, power that spacecrafts require is increasing.Searching for solar array of larger power, higher reliability, longer life-span and lower cost is always one of the urgent requirements. In recent years, our country is engaged in developing satellites of large power for navigation and communication, with the problem of how to improve performances of the power system on board. Solar panel is widely used to provide energy for satellites.Orientation and sun tracking methods of solar panel of satellites in different orbits were discussed in this thesis, in favor of power system designation. Open-closed loop controlling was often used for sun tracking of solar panel of satellites in sun synchronous orbits, which keeps driving solar panel in a certain constant speed. The influence of sun movement and drag of atmosphere on the tracking error was analyzed, and a corresponding sun tracking method is derived. Yaw motion is a significant sun tracking method for satellites in a general inclined orbit with solar panels with single degree of freedom. A useful scheme which replaced the ideal yaw angle profile by a square wave has a great advantage for certain applications. The yaw angle is thus maintained constant for large parts of the orbit. An analytical formula of the constant optimal yaw angle as a function of the angle between the sun and the orbit was derived through polynomial curve fitting without incurring more power loss. Fixed solar panel can be used in satellites with low power, short life span and special application. A method for figuring out fixed solar arrays optimal orientation is proposed in this paper for satellites in elliptic orbits, so that a maximum energy can be provided to the satellite. A theorem is proved, that is, the optimal orientation is in the direction of the centroid of the upper portion of the sun track cirque in the celestial sphere. With the theorem, the optimal orientation can be approximated by iteratively locating the corresponding centroid. This method is suitable for satellites in orbits of different eccentricities. Numerical simulations have demonstrated the effectiveness of the approach proposed.Orbital maneuver is refers to the spacecraft, the initiative to change the orbit. Here pointed out that the three layers of meaning, respectively illustrates the purpose of the orbital maneuver, process and properties. First of all, it is active behavior of the spacecraft to orbit maneuver, there is a purpose, application oriented flight, that rules out some interference factors caused by drift orbit changes; Second, the orbit maneuver is to change the orbit, i.e. the spacecrafts flight maneuver flight to break the existing inertia, no longer comply with Keplers laws; Finally, the orbit maneuver is a process, is one of the spacecraft flight course, different from pulse change track.The basic knowledge of the spacecraft orbit maneuver is mainly two body orbital mechanics, Hohmann transfer and Lambert transfer, involving thermal control technology, jet propulsion technology, energy technology, space communication technology and the launch of the spacecraft, return and in-orbit technology, etc. Today, the space technology of the worlds political, economic, military, science and technology and all aspects of human life had a profound impact. Spacecraft orbit maneuver research promotes the human the progress of science and technology, expanding within the field of human activity from the atmosphere into space. It is a multidisciplinary field of technology, including mechanical, electronic technology, materials science, automatic control, computer, vacuum technology, low temperature technology, semiconductor technology, jet propulsion, medicine, manufacturing technology, and discipline, is the foundation of science and technology integration.1, the aircraft with the main body gravity constitute two body systems, can be regarded as particle, the quality of the aircraft relative to the quality of the gravity of body is negligible, in with the center of the gravity of body OpXpYpZp inertial coordinate system, the equation of motion of aircraft are as follows:If there is a solution of equation, can be written as the following form:The integral constants are given and the location of the aircraft, the relationship between the speed. If you know the t=t0 the position and speed of the aircraft, can uniquely determine the integration constant 。2,Hohmann transfer diagramAbove for the spacecraft from low orbit (1) to (3) high orbit hohmann transfer orbit. Instantaneous acceleration on the spacecraft in orbit (1), into an oval transfer orbit (2). Periapsis start from this elliptical orbit spacecraft, after arriving at the far point of arch and instantaneous acceleration, into another circular orbit (3), this is the target orbit. Note that the three rail orbit semimajor axis is bigger and bigger, so the two engine propulsion is accelerated, the total energy increases with the entered the track of higher (semimajor axis is bigger). Hohmann transfer orbit, in turn, can also be sent a spacecraft to a lower orbit, but is rather than speed up twice to slow down. Hohmann transfer orbit two accelerated hypothesis is instantaneous, but actually accelerate takes time, so need extra fuel to compensate. Use extra high thrust engine fuel is lesser, was also to control the propulsion thrust engines with low time, gradually improve the orbit to approximate hohmann transfer orbit. So V will be bigger than assumption is, in effect, and spend more time.Always equal to body in orbit of gravitational and kinetic energy and, and is always equal to the gravitational potential energy (orbit radius gravitational potential energy of orbit semimajor axis) half:Unknown equations for speed and get the orbital energy balance equation is:The energy transfer orbit is greater than the inside track (= r1), less than the outer rail (= r2). The speed of the transfer orbit in the perigee and apogee by conservation of energy:Assuming that orbit around the earth, replaced by , g is the acceleration of gravity of the earths surface, R is the radius of the earth. and is the speed of the circular orbit, so hohmann to transfer the required two (assuming the speed change is a moment) : and were originally circular orbit with the target of the radius of the circular orbit, including large (small) corresponding to the hohmann transfer orbit far apse (periapsis) distance.No matter to higher or lower orbit, according to Keplers third law, hohmann transfer the time it takes for:(that is, half of the elliptical orbit cycle), which is hohmann transfer orbit semimajor axis.3, lambert problem described as: elliptic arc on the flight time between two points and ，t depends only on the elliptical semimajor axis , arc the sum of the distance to the focus on two arc two points on the chord length and connection.When flight time known, lambert problem can be described as: if a given aircraft run vector (,), initial and final position of the corresponding flight time and flight direction, can determine the orbit of connection and , which determine the speed of the initial and final position vector (,).In two body problem, if the initial position and velocity vector of a moving object is known, then you can use Lagrange coefficient showed any time after the position and speed. That is:Among them, the and as Lagrange coefficient, respectively is:In spacecraft orbit coordinate system, define the direction of axis direction vector for , axis direction vector to , sets the coordinates of the craft to ( ,), then , one of themTherefore,Will type into expression on available,If the introduction of partial close , hasSimilarly, you can obtain other Lagrange coefficient expression：Among them, and respectively orbit semimajor axis and semi orthogonal string, as the center of gravity of body gravity constant.By type available:As you can see, the beginning and end of the beginning and end of the aircraft speed and can be made by location, and Lagrange coefficient , , and said, therefore lambert problem solving can be got by calculating Lagrange coefficient.Spacecraft orbit is widely applied to navigation, communications and weather, and other areas of the closely related to our lives. Therefore, the study of spacecraft orbit maneuver is focus in the study of space on-orbit service technology application object. In view of the spacecraft orbit maneuver space on-orbit service involves widely technical aspect, this article mainly close up strategy and objectives of the early stage of the task to study the relative state. Considering the fuel consumption, we in the line of sight guidance before and added hohmann, hohmann transfer is the most save fuel transfer method. And set under the initial conditions of the simulation in this paper, to join hohmann transfer line of sight guidance to save energy is not much, but hohmann transfer for a long time. Then with Lambert, comparing with previous hohmann transfer, it is concluded that the different between them and the advantages and disadvantages, suitable flexible use. For deep space probe orbit design and optimization of technology conducted in-depth research, and has carried on the track for specific detection task instance design, optimization and simulation.中文译文：航天器轨道机动研究 随着航天技术的发展，飞行器上所需的功率越来越大，发展高功率、高可靠性、长寿命和低成本的空间太阳电池阵始终是航天技术所追求的目标。近年来，我国正积极发展导航，通讯等大功率卫星，如何提高卫星电源系统的性能日渐显得重要。本文以此为背景，研究不同轨道卫星太阳帆板对日定向方法，为我国大功率卫星电源系统的设计提供参考。 太阳同步轨道卫星太阳帆板常用的定向方式是开闭环组合控制。该方式以恒定的跟踪速度驱动太阳帆板对日定向。由于轨道摄动等因素的存在，跟踪误差会逐步扩大而超出容许范围。本文研究了太阳周年视运动和大气阻力对长寿命太阳同步轨道卫星太阳帆板以恒定跟踪速度对日跟踪定向的影响，提出在基本跟踪速度的基础上再进行太阳周年视运动修正和大气影响补偿的跟踪方法。 辅助姿态偏航角是一般倾斜轨道卫星单自由度太阳帆板对日定向的有效方法。辅助固定偏航角的方案对卫星的某些应用很有意义。原方案中偏航角和太阳仰角的关系式的推导有缺陷，本文通过多项式拟合参数法给出了最佳偏航角与太阳仰角的解析表达式，并且减少了原方案的能量损失。非定向式太阳帆板应用于短寿命低功率的某些特殊用途卫星。针对使轨道周期内获得能量最大的非定向式太阳帆板最佳指向问题，本文论证了单位天球中最佳指向必定通过太阳轨迹圆环被太阳帆板平面截得的上方部分的质心的规律，并由此提出了一种逐步迭代修正的方法。该方法适应于椭圆轨道卫星。将其应用于不同偏心率轨道卫星，仿真结果说明该方法能有效解得非定向式太阳帆板的最佳指向。轨道机动是指航天器主动地改变飞行轨道的过程。这里指出了三层含义，分别说明了轨道机动的目的、过程和属性。首先，轨道机动是航天器的主动行为，是有目的的、面向应用的飞行，这就排除了某些干扰因素引起的漂移性轨道变化；其次，轨道机动是要改变飞行轨道的，亦即航天器的机动飞行要打破已有的惯性飞行，不再遵从开普勒定律；最后，轨道机动是一个“过程”，是航天器的一个飞行历程，不同于脉冲变轨。 航天器轨道机动的基础知识主要是二体轨道力学、霍曼转移和兰伯特转移，涉及到热控制技术、喷气推进技术、能源技术、空间通信技术以及航天器的发射、返回和在轨技术等。时至今日，航天技术对世界各国的政治、经济、军事、科技以及人类生活的各个方面产生了深远的影响。航天器轨道机动研究推动着人类科学技术的进步，使人类活动的领域由大气层内扩展到宇宙空间。它是一个多学科领域的技术，包括力学、电子技术、材料学、自动控制、计算机、真空技术、低温技术、半导体技术、喷气推进、医学、制造工艺学等学科，是基础科学和技术科学的集成。1、飞行器与主引力体构成二体系统，均可看作质点，飞行器的质量相对于引力体的质量可以忽略不计，在以该引力体为中心的惯性坐标系OpXpYpZp下，飞行器的运动方程为： 如果方程有解，则可写成如下形式: 上式给出了积分常数和飞行器的位置、速度之间的关系。如果知道了t=t0时刻飞行器的位置和速度,就可以唯一地确定积分常数。 2、 Hohmann转移示意图上图为将太空船从低轨道（1）送往较高轨道（3）的霍曼转移轨道。太空船在原先轨道（1）上瞬间加速后，进入一个椭圆形的转移轨道（2）。太空船由此椭圆轨道的近拱点开始，抵达远拱点后再瞬间加速，进入另一个圆轨道（3），此即为目标轨道。要注意的是，三个轨道的轨道半长轴是越来越大，因此两次引擎推进皆是加速，总能量增加而进入
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