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首页> 外文期刊>Journal of Aeronautics & Aerospace Engineering >Parameterization of Micro Satellite Launch Vehicle
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Parameterization of Micro Satellite Launch Vehicle

机译：微型卫星运载火箭的参数化

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The new trends in micro satellites mission for wide range of applications has motivated worldwide research in design and development of micro satellite launch vehicles (MSLVs) as a vital options in the deployment of such satellites into their respective mission orbits. Presently, most micro satellites are launched through rideshares with rockets or rocket-like systems, which were developed essentially in the seventieth and eightieth of the last century. The MSLV as a proportional micro satellite launch vehicle, up till now has only the status of technology and system study work and is well known that the research and development of MSLV are diversified in different fields. However, the realization of MSLVs is rigorous since such vehicles compound the inherent difficulties of traditional launch experiment with intrinsic problems of uneven mass distribution, slenderness, high frequency and amplitude of vibration etc. MSLV are also more likely to be affected by wind gusts and other disturbances than their conventional counterpart, and the physical parameters such as mass distribution and moments of inertia can be easily altered by changing the payload location and unpredictable propellant burning. All these factors compromise the additional velocities to overcome the aerodynamic drag, to account for steering of the vehicle and other losses. Consequently, We prototype a three stage micro-satellite launch equipment as a similitude of the European Space Agency’s VEGA launcher using a scale down derivation model and parameterized using existing VEGA launch vehicle (LV) technical data. VEGA launch data, total orbital velocity requirement including the losses and stage payload ratio are inferred and applied to the model of parameterization of launch vehicles through coupled- parameters simulations. This approach can be helpful in viability and performance insights in terms of payload mass, stage mass distribution and material properties precision and effectiveness. It can also serve as a background for the Lanre et al., J Aeronaut Aerospace Eng 2014, 3:2 DOI: 10.4172/2168-9792.1000134 development of time optimal waypoint trajectory of micro satellite launchers.
机译：微卫星飞行任务的广泛应用的新趋势激发了全世界对微卫星运载火箭（MSLV）设计和开发的研究，这是将此类卫星部署到其各自的任务轨道的重要选择。目前，大多数微型卫星是通过与火箭或类火箭系统的乘车共享发射的，而火箭或类似火箭的系统基本上是在上个世纪七十和八十年代开发的。 MSLV作为一种比例微卫星运载工具，到目前为止仅具有技术和系统研究工作的地位，众所周知，MSLV的研究和开发在不同领域是多元化的。然而，MSLV的实现是严格的，因为此类运载工具加重了传统发射实验的固有困难以及质量分布不均，细长，振动的高频和振幅等固有问题。MSLV也更容易受到阵风等的影响通过改变有效载荷位置和不可预知的推进剂燃烧，可以轻松地更改与常规扰动相比的扰动，以及诸如质量分布和惯性矩之类的物理参数。所有这些因素都折衷了额外的速度，以克服空气阻力，从而解决了车辆的转向和其他损失。因此，我们使用了按比例缩小的推导模型并使用现有的VEGA运载工具（LV）技术数据对三阶段微卫星发射设备进行了原型设计，以模仿欧洲航天局的VEGA发射器。推断出VEGA发射数据，总轨道速度要求（包括损耗和载物台有效载荷比），并通过耦合参数模拟将其应用于运载火箭的参数化模型。这种方法可以在有效载荷质量，载物台质量分布以及材料特性的精度和有效性方面帮助提高可行性和性能。它也可以作为Lanre等人（J Aeronaut航空航天工程2014）3：2 DOI：10.4172 / 2168-9792.1000134的背景，以开发微型卫星发射器的时间最佳航点轨迹。

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