LEA Flight Test Program: First Step to an Operational Application of High-Speed Airbreathing Propulsion
LEA Flight Test Program: First Step to an Operational Application of High-Speed Airbreathing Propulsion
复制标题
DOI：
10.2514/6.2003-7031
复制
发表时间：
2003-12
期刊：
影响因子：
--
通讯作者：
F. Falempin;L. Serre
中科院分区：
文献类型：
--
作者：
F. Falempin;L. Serre
在过去的 10 年里，MBDA 和 ONERA 领导了大量的研究和技术工作，以开发高速吸气式推进系统的知识并掌握相关技术。高超音速吸气式推进系统的民用或军用应用的发展取决于两个关键点：推进系统燃料冷却结构所需技术的开发、以合理精度进行预测的能力以及优化气动推进平衡（或广义推力-阻力平衡）的能力。大部分技术开发工作可以通过可用的地面测试设施和经典数值模拟（热力学、力学......）来引导。相反，在任何实际应用之前，必须证明我们有能力预测高超音速飞行器的气动推进平衡（广义推力减阻力平衡），为启动昂贵的技术计划提供足够的余量。考虑到这一强制性步骤，MBDA 和 ONERA 正在领导一项名为 LEA 的具体科学计划，其组织如下： • 定义使用地面测试和数值模拟开发高超音速飞行器的方法 • 为此目的开发所需的工具（实验或数值）。 • 将此方法应用于开发简化、科学的实验飞行器 • 通过一系列飞行测试验证该方法 该计划于 2003 年 1 月启动，计划在 4 至 8 马赫数范围内对实验飞行器进行 6 次自主飞行测试后于 2012 年结束。版权所有 © 2003 MBDA France 和 ONERA。由美国航空航天研究所经许可出版。简介 在过去的二十年中，世界各地进行了大量的系统研究，通常基于大型技术开发工作，以评估联合推进（吸气式+火箭）对于太空发射器应用的兴趣。在法国，得益于法国航天局（CNES）八十年代领导的研究，然后在 PREPHA 计划（先进高超音速推进研究与技术计划）的框架下，明确指出，只有吸气模式能够提供总速度增量的后续部分（例如，吸气模式必须确保推进从至少 1.5/2 马赫到 10/12 马赫），组合推进才可能对太空发射器应用感兴趣（参考文献[1]至[7]）。另一方面，高超音速吸气推进器在军事用途上可能有非常有趣的应用。事实上，以非常高的马赫数和高度飞行可以极大地提高突防能力，同时具有较高的平均速度可以应对关键时间目标（参考文献[8]至[10]）。然而，高超音速吸气式推进系统的民用或军用应用的发展取决于两个关键点： • 开发推进系统所需的技术，作为燃烧室的低重量、高鲁棒性燃料冷却结构； • 能够以合理的精度进行预测并优化气动推进平衡（或广义推力-阻力）。技术开发工作 即使技术最终需要经过飞行验证，大部分技术开发工作也可以通过可用的地面测试设施（参考文献[11]）和经典数值模拟（热力学、力学......）来引导。第十二届 AIAA 国际太空飞机和高超音速系统与技术 15 2003 年 12 月 19 日，弗吉尼亚州诺福克 AIAA 2003-7031 版权所有 © 2003 MBDA France 和 ONERA。由美国航空航天研究所经许可出版。
During the 10 last years, a large Research and Technology effort has been led by MBDA and ONERA to develop knowledge on high-speed airbreathing propulsion and master associated technologies. Development of operational, civilian or military, application of the hypersonic airbreathing propulsion depends of two key points : development of needed technologies for the fuel-cooled structure of the propulsion system, capability to predict with a reasonnable accuracy and to optimise the aeropropulsive balance (or generalized thrust-minus -drag balance). The most part of the technology development effort can be led with available ground test facilities and classical numerical simulation (thermics, mechanics ...). On the contrary, before any operational application, it is mandatory to demonstrate our ability to predict the aeropropulsive balance (generalized thrust-minusdrag balance) of a hypersonic vehicle, providing sufficient margins to start a costly technological program. Considering this mandatory step, MBDA and ONERA are leading a specific scientific program, called LEA, organized as follows: • Define a methodology for the development of a hypersonic vehicle using ground tests and numerical simulation • Develop the required tools (experimental or numerical) for this purpose. • Apply this methodology to the development of a simplified, scientific experimental vehicle • Validate this methodology through a series of flight tests Started in January 2003, this program is planned to end in 2012 after 6 autonomous flight tests of the experimental vehicle in the Mach number range from 4 to 8. Copyright © 2003 by MBDA France and ONERA. Published by American Institute for Aeronautics and Aerospace,Inc., with permission. Introduction During the two past decades, a lot of system studies, generally based on large technology development efforts, have been performed around the world to assess the interest of combined propulsion (airbreathing + rocket) for space launcher application. In France, thanks to studies led by the French Space Agency (CNES) during eighties, then in the framework of PREPHA program (Research and Technology Program for Advanced Hypersonic Propulsion), it was clearly established that combined propulsion could have an interest for space launcher application only if airbreathing mode can provide a subsequent part of the total speed increment (e.g. airbreathing mode must ensure propulsion from at least Mach 1.5/2 to Mach 10/12) (Ref [1] to [7]). By another way, hypersonic airbreathing propulsion could have very interesting application for military purpose. As a matter of fact, flying at very high Mach number and altitude can strongly improve the penetration capability while having a high average speed allow to deal with critical time targets (Ref [8] to [10]). Nevertheless, the development of operational, civilian or military, application of the hypersonic airbreathing propulsion depends of two key points : • development of needed technologies for the propulsion system as a low weight, high robustness fuel-cooled structure for the combustor, • capability to predict with a reasonnable accuracy and to optimise the aero-propulsive balance (or generalized thrust-minus -drag). Technology development effort Even if technologies will finally need to be flight proven, a large part of the technology development effort can be led with available ground test facilities (Ref[11]) and classical numerical simulation (thermics, mechanics...). 12th AIAA International Space Planes and Hypersonic Systems and Technologies 15 19 December 2003, Norfolk, Virginia AIAA 2003-7031 Copyright © 2003 by MBDA France and ONERA. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.