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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->Aerospace Mission Design Industrial Software ATK]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Development progress and technical breakthroughs of space mission design industrial software ATK 3.0]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250401]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Space mission design software spans the entire lifecycle of space missions and is regarded as the cornerstone of the aerospace industrial software system. Leveraging nearly three decades of technical expertise in the field of manned spaceflight, the research team from the National University of Defense Technology initiated the development of the independent industrial software ATK（aerospace tool kit） in 2020. By the end of 2024, the ATK 3.0 version was officially released, encompassing 5 major categories and 21 functional modules, including standard platform, visibility and coverage analysis, mission analysis, orbital design, and secondary development. The development of ATK has been deeply and continuously supported by China Manned Space Engineering exploring a collaborative research and development model characterized by "engineering-driven demand+centralized academic development".  This software has had a significant impact in aerospace engineering, space security, and academic education, marking a solid first step toward replacing STK. The development history of ATK was reviewed, and the functional features was elaborated on.  Focuses on analyzing its core technologies breakthroughs of ATK, such as large-scale software architecture design, computational kernel development, and orbital maneuver planning were selective analysed. While ATK faces challenges in enhancing its functionality and building its application ecosystem, its future development roadmap and strategic objectives were outlined.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[LUO Yazhong, YANG Zhen, WANG Hua, ZHOU Jianping]]></author>
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<atom:name>LUO Yazhong, YANG Zhen, WANG Hua, ZHOU Jianping</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[General orbital maneuver planning design for space mission design industrial software ATK]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250402]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Orbital maneuver planning is an important part of the design of complex space missions such as rendezvous and docking, lunar exploration, etc. However, the varying configuration requirements of different missions for orbit transfer positions, maneuver magnitudes, and targeting parameters pose significant challenges to the generalized modeling and solution of maneuver planning. Regarding this problem, a generalized orbital maneuver planning modeling method based on orbital segments was proposed, which abstracts the maneuver requirements of different scenarios into orbital segments, stopping conditions, and constraints, forming a building-block spacecraft mission description model. The orbital maneuver requirements were converted into a unified nonlinear programming problem, which was subsequently solved by employing three distinct methods: differential correction, sequential quadratic programming, and intelligent optimization algorithms. A software module ATK. Astromaster was developed as a core module for ATK(aerospace tool kit) software. Simulation results show that the proposed method can achieve general orbit maneuver modeling and solving in different scenarios.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[YANG Zhen, JIN Ke, GUO Xiang, WANG Hua, LUO Yazhong]]></author>
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<atom:name>YANG Zhen, JIN Ke, GUO Xiang, WANG Hua, LUO Yazhong</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250402]]></guid><cfi:id>6</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mission planning and independent software design of spacecraft rendezvous and proximity operations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250403]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the lack of universal software for spacecraft RPO (rendezvous and proximity operations) mission planning, the RPO planning model and software were studied. The concept of RPO element was proposed, and an element system, which consists of four categories (rendezvous, proximity, companion flight, and departure) was constructed. RPO missions can be formed by combining multiple elements. A mission planning model for RPO elements was established. Calculation formulas for the mission control segments, stop conditions, control parameters, and constraints were provided. Based on the ATK (aerospace tool kit), a RPO mission planning tool was designed and implemented. Simulations were conducted using examples of GEO rendezvous and sun synchronous fly around, and the results show that the established RPO elements and software can effectively design RPO missions.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[WANG Hua, HUO Chengyi, HE Junhua, YU Dateng, FANG Xuankun]]></author>
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<atom:name>WANG Hua, HUO Chengyi, HE Junhua, YU Dateng, FANG Xuankun</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250403]]></guid><cfi:id>5</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Intention recognition for forced motion of space non-cooperative targets based on BiGRU network]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250404]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the problem that it is difficult to identify the forced motion intention of non-cooperative targets, an intention recognition method based on BiGRU(bi-directional gated recurrent unit) network was proposed. The non-cooperative target was categorizes into five forced motion intentions: "forced round fly-around""forced drip-drop fly-around""fixed-point oscillating""line approach" and "hop approach", and the forced motion intention maneuver information dataset of the non-cooperative target was established. Based on the maneuver time series information of the non-cooperative target after entering the observation range of our spacecraft, the BiGRU network was utilized to train on the potential correlation between the time series data and the forced motion intention, so as to realize the intention recognition of the non-cooperative target. The simulation results demonstrate that the detection accuracy of the BiGRU network-based forced motion intention recognition method for non-cooperative targets achieve 98.35%. This method can improve the ability to identify the intentions of non-cooperative targets and provide a technical reference for the safety of our spacecraft in orbit.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[HUANG Hexiang, YANG Zhen, LI Jiasheng, LUO Yazhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Hexiang, YANG Zhen, LI Jiasheng, LUO Yazhong</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250404]]></guid><cfi:id>4</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization design of emergency observation constellation: application of ATK secondary development technology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250405]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Due to the limitations of the number of satellites, scale and manoeuvrability, it is difficult for the existing earth observation constellations to respond quickly to emergency needs of a high degree of randomness. In order to meet the demand for rapid design of emergency earth observation constellations, an emergency earth observation constellation design method was proposed. Based on the secondary development and coverage analysis function of the ATK（aerospace tool kit),a one-dimensional data hierarchical clustering method was adopted to group ground targets, and then the differential evolution algorithm was appliedto optimize the restricted Walker subconstellation configuration for the target groups, and finally the restricted hybrid Walker earth observation constellation was generated . Simulation results demonstrate that the method can rapidly generate emergency constellations compared with conventional Walker constellations and violent optimisation results, and minimize satellite deployment quantity while ensuring the effective completion of the earth observation mission.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[LI Mingming, GUO Shuai, ZHU Yuehe, LIANG Yangang, DONG Min, XU Xiaosheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Mingming, GUO Shuai, ZHU Yuehe, LIANG Yangang, DONG Min, XU Xiaosheng</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250405]]></guid><cfi:id>3</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[ATK-driven HEO satellite synchronous belt surveillance mission architecture and orbital maneuver co-design]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250406]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A non-coplanar flyby is recognized as an effective method for monitoring high-value target satellites in geosynchronous orbit. Taking the scenario of patrolling the geosynchronous belt with an elliptical orbit as an example, a method for solving the minimal orbital intersection distance between any two elliptic orbits was proposed, and it was proven that the optimal flyby point for the patrolling satellite is the ascending node. ATK（aerospace tool kit）was used to model the mission scenario, investigating the variations in the optimal flyby point position in J2 gravitational model. The variation law in terminal constraints (e.g., relative distance and sun phase angle at the flyby point) were studied under different local times and flyby directions. Aoptimal fuel transfer strategy satisfying the maximum transfer time and terminal constraints was proposed, and mission parameters for the mission under different gravitational model assumptions were solved by using the maneuver planning module in ATK. Mission parameters corresponding to different true anomaly angles in the two-body model were analyzed, the effectiveness of the strategy was validated, and a basis for planning multiple patrol sequences was provided.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[LI Linhong, LIANG Yangang, LI Kebo, WANG Jiaxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Linhong, LIANG Yangang, LI Kebo, WANG Jiaxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250406]]></guid><cfi:id>2</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dual-path neural network learning method for free-return orbit integrating dynamic characteristics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250407]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The free-return orbit serves as the preferred orbital scheme for crewed spacecraft in earth-moon transfers, yet its design involves stringent constraints and significant initial-value dependency in existing algorithms. The earth-moon transfer trajectory planning for manned lunar exploration was addressed by proposing a dual-path neural network learning method to optimize free-return orbit initialization. A dynamic model of the free-return orbit was established to analyze the characteristics of the near-earth orbital solution space. Integrating the spatial partitioning characteristics of ascending and descending orbital phase in solution spaces, a dual-path neural network architecture designed via parameter-correlated transformation was proposed to ensure the completeness of orbital solutions. Utilizing ATK.Astromaster, the earth-moon free-return orbit planning under the dual-path network learning-based initialization method was implemented and validated through simulation. The results provide an effective reference for mitigating initial-value dependency in manned lunar mission orbit design.]]></description>
<pubDate>2025/7/23 0:00:00</pubDate>
<category><![CDATA[Aerospace Mission Design Industrial Software ATK]]></category>
<author><![CDATA[ZHU Binyu, LI Haiyang, YANG Zhen, HE Junhua, LU Lin, ZHANG Yuhang]]></author>
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<atom:name>ZHU Binyu, LI Haiyang, YANG Zhen, HE Junhua, LU Lin, ZHANG Yuhang</atom:name>
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