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Results of simulation and scaled flight tests performed on a rocket-plane at high angles of attack
Aircraft Engineering and Aerospace Technology ( IF 1.5 ) Pub Date : 2021-04-05 , DOI: 10.1108/aeat-11-2020-0276
Agnieszka Kwiek , Cezary Galinski , Krzysztof Bogdański , Jaroslaw Hajduk , Andrzej Tarnowski

Purpose

According to the study of the space flight market, there is a demand for space suborbital flights including commercial tourist flights. However, one of the challenges is to design a mission and a vehicle that could offer flights with relatively low G-loads. The project of the rocket-plane in a strake-wing configuration was undertaken to check if such a design could meet the FAA recommendation for this kind of flight. The project concept assumes that the rocket plane is released from a slowly flying carrier plane, then climbs above 100 kilometers above sea level and returns in a glide flight using a vortex lift generated by the strake-wing configuration. Such a mission has to include a flight transition during the release and return phases which might not be comfortable for passengers. Verification if FAA recommendation is fulfilled during these transition maneuvers was the purpose of this study.

Design/methodology/approach

The project was focused on the numerical investigation of a possibility to perform transition maneuvers mentioned above in a passenger-friendly way. The numerical simulations of a full-scale rocket-plane were performed using the simulation and dynamic stability analyzer (SDSA) software package. The influence of an elevator deflection change on flight parameters was investigated in two cases: a transition from the steep descent at high angles of attack to the level glide just after rocket-plane release from the carrier and an analogous transition after re-entry to the atmosphere. In particular, G-loads and G-rates were analyzed.

Findings

As a result, it was found that the values of these parameters satisfied the specific requirements during the separation and transition from a steep descent to gliding. They would be acceptable for an average passenger.

Research limitations/implications

To verify the modeling approach, a flight test campaign was performed. During the experiment, a rocket-plane scaled model was released from the RC model helicopter. The rocket-plane model was geometrically similar only. Froude scales were not applied because they would cause excessive technical complications. Therefore, a separate simulation of the experiment with the application of the scaled model was performed in the SDSA software package. Results of this simulation appeared to be comparable to flight test results so it can be concluded that results for the full-scale rocket-plane simulation are also realistic.

Practical implications

It was proven that the rocket-plane in a strake-wing configuration could meet the FAA recommendation concerning G-loads and G rates during suborbital flight. Moreover, it was proven that the SDSA software package could be applied successfully to simulate flight characteristics of airplanes flying at angles of attack not only lower than stall angles but also greater than stall angles.

Social implications

The application of rocket-planes in a strake-wing configuration could make suborbital tourist flights more popular, thus facilitating the development of manned space flights and contributing to their cost reduction. That is why it was so important to prove that they could meet the FAA recommendation for this kind of service.

Originality/value

The original design of the rocket plane was analyzed. It is equipped with an optimized strake wing and is controlled with oblique, all moving, wingtip plates. Its post-stall flight characteristics were simulated with the application of the SDSA software package which was previously validated only for angles of attack smaller than stall angle. Therefore, experimental validation was necessary. However, because of excessive technical problems caused by the application of Froude scales it was not possible to perform a conventional test with a dynamically scaled model. Therefore, the geometrically scaled model was built and flight tested. Then a separate simulation of the experiment with the application of this model was performed. Results of this separate simulation were compared with the results of the flight test. This comparison allowed to draw the conclusion on the applicability of the SDSA software for post-stall analyzes and, indirectly, on the applicability of the proposed rocket-plane for tourist suborbital flights. This approach to the experimental verification of numerical simulations is quite unique. Finally, a quite original method of the model launching during flight test experiment was applied.



中文翻译:

在高攻角下在火箭飞机上进行的模拟和大规模飞行测试的结果

目的

根据对太空飞行市场的研究,对包括商业旅游飞行在内的太空亚轨道飞行有需求。但是,挑战之一是设计一种任务和一种车辆,以提供相对较低的G负荷飞行。进行了平流翼构型的火箭飞机项目,以检查这种设计是否符合美国联邦航空局对此类飞行的建议。该项目的概念假设火箭飞机从缓慢飞行的载机飞机上释放,然后爬升到海拔100公里以上,并使用由机翼机翼构造产生的涡旋升力以滑行飞行返回。这样的任务必须包括在释放和返回阶段的飞行过渡,这可能会让乘客感到不舒服。

设计/方法/方法

该项目的重点是对以乘客友好的方式执行上述过渡演习的可能性进行数值研究。使用仿真和动态稳定性分析器(SDSA)软件包对全尺寸火箭飞机进行了数值仿真。在两种情况下研究了电梯挠度变化对飞行参数的影响:从高攻角的陡峭下降到火箭飞机刚从航母上释放后到水平滑行的过渡,以及在重新进入飞机后的类似过渡。气氛。特别地,分析了G负载和G速率。

发现

结果,发现这些参数的值在分离和从陡降到滑行的过渡过程中满足特定要求。对于普通乘客来说,它们是可以接受的。

研究局限/意义

为了验证建模方法,进行了一次飞行测试活动。在实验过程中,从RC模型直升机上发布了火箭飞机缩放模型。火箭飞机模型仅在几何上是相似的。未使用弗洛德磅秤,因为它们会导致过多的技术复杂性。因此,在SDSA软件包中使用比例模型对实验进行了单独的仿真。该模拟结果似乎可以与飞行测试结果相媲美,因此可以得出结论,对全尺寸火箭飞机进行模拟的结果也是切合实际的。

实际影响

事实证明,在翼型飞机构型中的火箭飞机可以满足FAA关于亚轨道飞行期间的G载荷和G率的建议。此外,事实证明,SDSA软件包可以成功地用于模拟以迎角不仅小于失速角而且大于失速角飞行的飞机的飞行特性。

社会影响

将火箭飞机应用在机翼机翼构型中可以使亚轨道旅游飞行更受欢迎,从而促进载人航天的发展并有助于降低成本。因此,重要的是要证明他们可以满足FAA关于此类服务的建议。

创意/价值

分析了火箭飞机的原始设计。它配备了优化的str翼,并由倾斜的,所有移动的翼尖板控制。它的失速后飞行特性是通过使用SDSA软件包进行仿真的,该软件包先前仅针对小于失速角的迎角进行了验证。因此,实验验证是必要的。但是,由于使用Froude标尺导致过多的技术问题,因此无法使用动态标尺模型执行常规测试。因此,建立了几何比例模型并进行了飞行测试。然后使用该模型对实验进行了单独的仿真。将此单独模拟的结果与飞行测试的结果进行了比较。通过比较,可以得出结论,说明SDSA软件可用于失速后分析,并间接地得出建议的火箭飞机对亚轨道飞行的适用性。这种对数值模拟进行实验验证的方法非常独特。最后,采用了一种非常新颖的在飞行试验实验中启动模型的方法。

更新日期:2021-04-06
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