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1. 发明申请

WO2012141770A2 LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC AND SUPERSONIC CRUISE AIRCRAFT 审中-公开
标题翻译：用于跨音速和超音速飞行器的LAMINAR流动翼优化
公开(公告)号：WO2012141770A2
公开(公告)日：2012-10-18
申请号：PCT/US2012/020588
申请日：2012-01-09
申请人： AERION CORPORATION
发明人： TRACY, Richard, R. , CHASE, James, D.
IPC分类号： B64C3/14 , B64C3/16 , B64C30/00 , B64F5/00
CPC分类号： B64C3/10 , B64C3/14 , B64C30/00 , Y02T50/12
摘要： Aircraft configured to operate at Mach numbers from above.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, and having one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.
摘要翻译：飞机被配置为在马赫数从80以上至1.2的范围内运行，机翼扫掠角由机翼外侧前缘限定小于35度，并且结合外侧机翼的比率的计算值面板纵横比上升到指数78，除以最大厚度除以弦（t / c）的比率，大于约45，并且具有以下之一：a）其中最大厚度除以弦（t / c）位于飞机机身与机翼附件外侧距离约70％的位置，或b）最大厚度除以弦长（t / c）的位置是（t / c）所在位置的平均值在距离附着飞机机体外侧约50％的距离到机翼末端之间。

2. 发明申请

WO2011087475A2 LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT 审中-公开
标题翻译：用于超级和高次序游轮飞机的层间流动优化
公开(公告)号：WO2011087475A2
公开(公告)日：2011-07-21
申请号：PCT/US2010/002758
申请日：2010-10-15
申请人： AERION CORPORATION
发明人： TRACY, Richard, R. , STURDZA, Peter , CHASE, James, D.
IPC分类号： B64C3/14 , B64C3/16 , B64C30/00
CPC分类号： B64C30/00 , B64C3/10 , B64C3/14 , Y02T50/12
摘要： A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).
摘要翻译：一种提供具有机身和机翼的飞行器的方法，其在设计巡航条件下被配置为用于广泛的层流，该方法的特征在于：a）提供具有沿着翼跨度的厚度，弦和形状值的机翼双凸型翼型，其提供基本上最佳的飞机在设计巡航条件下的范围，考虑到翼拖和翼重的影响; b）提供机翼前缘，其构造成实现层流; c）提供机身和机翼轮廓，其组合产生减少的总波阻力并且在机翼上产生大量的层流边界层流动区域; 和d）提供有助于提供a），b）和c）的机翼扫掠角度。

3. 发明申请

WO2008115207A2 HIGHLY EFFICIENT SUPERSONIC LAMINAR FLOW WING 审中-公开
标题翻译：高效的超级层压流
公开(公告)号：WO2008115207A2
公开(公告)日：2008-09-25
申请号：PCT/US2007/022157
申请日：2007-10-17
申请人： AERION CORPORATION
发明人： CHASE, James, D. , HENDERSON, Michael , STURDZA, Peter
IPC分类号： B64C30/00
CPC分类号： B64C30/00 , B64C3/10 , B64C7/00 , B64C9/18 , B64C9/24 , Y02T50/12 , Y02T50/32
摘要： Improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: strake extending forwardly of the wing inboard extent, raked wing tip, reversed fillet at strake or fuselage junction, inboard leading edge flap extending over less than about 15 % of the inboard wing panel span, hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.
摘要翻译：改进的超音速层流翼结构，在超音速飞机上，具有以下一个或多个：在翼的内侧向前延伸的翼片，斜翼尖，在行走或机身接合处的反向圆角，内侧前缘翼片延伸超过约 15％的内侧翼板跨距，混合平面分割翼片具有相对于平面翼片范围向下偏转的下表面部分。

4. 发明申请

WO2012112408A1 LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC CRUISE AIRCRAFT 审中-公开
标题翻译： LAMINAR流动优化用于通用航空飞机
公开(公告)号：WO2012112408A1
公开(公告)日：2012-08-23
申请号：PCT/US2012/024794
申请日：2012-02-13
申请人： AERION CORPORATION
发明人： TRACY, Richard, R. , CHASE, James, D.
IPC分类号： B64C21/00
CPC分类号： B64C3/10 , B64C3/14 , B64C30/00 , Y02T50/12
摘要： An aircraft designed for maximum efficient cruise speed in the range from about Mach 0.8 to about Mach 1.2, and having a fuselage and wings with: (a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along the wing semi-span outboard from the zone of substantial fuselage influence, or (b) wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to the wing tip.
摘要翻译：一种设计用于最大有效巡航速度范围从约0.8马赫至约马赫数1.2的飞机，并具有机身和机翼，其具有：（a）小于约25度的前缘扫掠，结合机翼厚度与翼弦比之间的弦比大约3％到8％左右，作为平均沿着机身半跨越外侧的大面积机身影响的区域，或（b）机翼前缘扫描在约20度和约35度之间，结合翼型厚度与弦的比例等于或低于大约3％，作为沿着半跨舷外平面从大面积机身影响的区域到翼尖。

5. 发明申请

WO2012021360A1 AIRCRAFT EMERGENCY AND BACKUP SECONDARY POWER APPARATUS 审中-公开
标题翻译：飞机紧急和备用辅助动力装置
公开(公告)号：WO2012021360A1
公开(公告)日：2012-02-16
申请号：PCT/US2011/046522
申请日：2011-08-04
申请人： AERION CORPORATION
发明人： CHASE, James, D.
IPC分类号： F16D31/02
CPC分类号： F16D31/02 , B64C30/00 , B64D41/00 , B64D41/007 , Y02T50/44
摘要： In combination, an aircraft and a rotatively combined electrical power/generator and hydraulic motor/pump configured to provide either hydraulic power from electrical power, or electrical power from hydraulic power, installed in said aircraft.
摘要翻译：在组合中，飞行器和旋转地组合的电力/发电机和液压马达/泵被配置成提供安装在所述飞机中的来自电力的液压动力或来自液压动力的电力。 p>

6. 发明授权

EP2081821B1 SUPERSONIC AIRCRAFT 有权
标题翻译：超音速飞机
公开(公告)号：EP2081821B1
公开(公告)日：2016-01-27
申请号：EP07874420.8
申请日：2007-10-17
申请人： Aerion Corporation
发明人： CHASE, James, D. , HENDERSON, Michael , STURDZA, Peter
IPC分类号： B64C3/10 , B64C7/00 , B64C9/18 , B64C9/24 , B64C30/00
CPC分类号： B64C30/00 , B64C3/10 , B64C7/00 , B64C9/18 , B64C9/24 , Y02T50/12 , Y02T50/32

7. 发明申请

WO2011087475A9 LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT 审中-公开
公开(公告)号：WO2011087475A9
公开(公告)日：2011-07-21
申请号：PCT/US2010/002758
申请日：2010-10-15
申请人： AERION CORPORATION
发明人： TRACY, Richard, R. , STURDZA, Peter , CHASE, James, D.
IPC分类号： B64C3/14
摘要： A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).

8. 发明申请

WO2010114604A1 JET NOZZLE PLUG WITH VARYING NON-CIRCULAR CROSS SECTIONS 审中-公开
标题翻译：喷嘴喷嘴与变化的非圆形横截面
公开(公告)号：WO2010114604A1
公开(公告)日：2010-10-07
申请号：PCT/US2010/000960
申请日：2010-03-31
申请人： AERION CORPORATION
发明人： CHASE, James, D. , GARZON, German, Andres
IPC分类号： F02K1/44
CPC分类号： F02K1/08 , F02K1/00
摘要： In a jet engine having a plug nozzle and a plug extending rearwardly from the nozzle exit, the improvement comprising a plug having successive cross sections spaced apart rearwardly of the nozzle exit, the cross sections transitioning from circular or near circular at the exit plane defined at the nozzle exit, to progressively non-circular, rearwardly.
摘要翻译：在具有塞子喷嘴和从喷嘴出口向后延伸的塞子的喷气发动机中，改进包括具有在喷嘴出口的后方间隔开的连续横截面的塞子，横截面从在喷嘴出口逐渐非圆形，向后。

9. 发明申请

WO2008105847A2 SUPERSONIC AIRCRAFT JET ENGINE 审中-公开
标题翻译：超音速飞机喷气发动机
公开(公告)号：WO2008105847A2
公开(公告)日：2008-09-04
申请号：PCT/US2007/021624
申请日：2007-10-10
申请人： AERION CORPORATION
发明人： CHASE, James, D. , GARZON, German, Andres
IPC分类号： B64C30/00
CPC分类号： B64C30/00 , B64D27/20 , B64D29/04 , B64D33/02 , B64D2033/026 , Y02T50/44
摘要： Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following X 0 ) a region just ahead of the lip X 1 ) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.
摘要翻译：超音速飞行器的喷气发动机进气口结构包括具有入口斜坡和与斜坡向外隔开的发动机罩唇缘的结构，使得进入的空气在斜坡和凸缘之间流动，所述唇缘和斜坡被配置为产生从斜坡的前部向外延伸以通过唇部的第一倾斜冲击和从斜坡的后部向外延伸到下列X 0之一的终端冲击）一个恰好在唇部X 1前面的区域）基本上与所述唇缘相连。产生不均匀的冲击系统，其产生接近等熵压缩和相对冲击回收的中心区域，并且减小冲压回收的外部区域，但导致减小的整流罩角度和阻力。还提供翻译罩结构和喷嘴与机身轮廓一体化以减少船尾拖曳的功能。

10. 发明公开

EP2668094A2 LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC AND SUPERSONIC CRUISE AIRCRAFT 有权转让
标题翻译：对于高超音速和亚音速飞行的飞机的优化LAMINARFLUSSFLÜGEL
公开(公告)号：EP2668094A2
公开(公告)日：2013-12-04
申请号：EP12771457.4
申请日：2012-01-09
申请人： Aerion Corporation
发明人： TRACY, Richard, R. , CHASE, James, D.
IPC分类号： B64C3/10
CPC分类号： B64C3/10 , B64C3/14 , B64C30/00 , Y02T50/12
摘要： Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.

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