公开(公告)号：US4481703A

公开(公告)日：1984-11-13

申请号：US358775

申请日：1982-03-17

申请人： Harry A. Scott

发明人： Harry A. Scott

IPC分类号： B64C3/18 ,  B23P17/00

CPC分类号： B64C3/187 ,  Y10T29/49956

摘要： A method is disclosed for fabricating rib structures of different sizes for a segment of an airfoil having both a spanwise taper in thickness and at least one aerodynamic surface having a substantially constant radius of curvature in the chordwise direction. In one embodiment a plurality of rib webs are formed at least as large as the largest rib structure. Each of the rib webs is trimmed at their lower edges progressively greater amounts to form rib webs of a proper size for each rib structure. A plurality of upper and lower rib caps as well as front and rear spar attachment brackets are formed and attached to the trimmed rib webs. In another embodiment the rib webs are formed with either or both integral upper rib caps and spar attachment brackets. In still another embodiment a plurality of rib webs are formed and joined together by twos by inverting one rib web to the other and progressively overlapping their lower edges and fastening them together to form properly sized rib structures. These rib webs are formed with either or both integral upper rib caps and spar attachment brackets or they can be formed separately and attached to the joined rib webs. In the case where the spars are not spanwise parallel, the rib webs are formed without spar attachment brackets and thereafter at least one end of the rib webs and rib caps, whether integral or not, are also trimmed progressively greater amounts so that they are of the proper size for each rib structure.

摘要翻译： 公开了一种制造不同尺寸的肋结构的方法，用于具有厚度的翼展倾斜锥形和翼弦方向上具有基本上恒定曲率半径的至少一个空气动力学表面的翼型段。 在一个实施例中，多个肋腹板形成至少与最大肋骨结构一样大。 每个肋腹板在其下边缘处逐渐地修剪较大的量，以形成每个肋结构的适当尺寸的肋腹板。 多个上下肋盖以及前后翼梁附接支架形成并附接到修剪的肋腹板。 在另一个实施例中，肋腹板形成有一个或两个整体的上肋帽和翼梁附接支架。 在另一个实施例中，通过将一个罗纹腹板翻转到另一个并且逐渐与它们的下边缘重叠并将它们紧固在一起以形成适当尺寸的肋结构，由多个肋形成并通过二者连接在一起。 这些肋腹板形成有一个或两个整体的上肋盖和翼梁附接支架，或者它们可以单独形成并附接到连接的肋腹板上。 在翼梁不是翼展方向平行的情况下，肋腹板形成为没有翼梁连接支架，此后肋腹板和肋盖的至少一端（无论是否整体）也逐渐地修剪更大的量，使得它们是 每个肋骨结构的适当尺寸。

公开(公告)号：US5154373A

公开(公告)日：1992-10-13

申请号：US248687

申请日：1988-09-26

申请人： Harry A. Scott

发明人： Harry A. Scott

IPC分类号： B64C1/40 ,  B64C1/38 ,  B64C3/36 ,  B64G1/58

CPC分类号： B64C3/36 ,  B64C1/38 ,  B64G1/58 ,  C04B37/008 ,  C04B37/025 ,  C04B37/028 ,  C04B2237/12 ,  C04B2237/363 ,  C04B2237/365 ,  C04B2237/368 ,  C04B2237/38 ,  C04B2237/402 ,  C04B2237/403 ,  C04B2237/406 ,  C04B2237/704

摘要： An integral structure and thermal protection system, particularly designed for hypersonic aerospace vehicles, is comprised of a hard external shell or outer face sheet formed of a ceramic matrix, such as silicon carbide, and a rigid insulator core in the form of foamed ceramic, such as silicon carbide, the outer face sheet being integrally connected to the insulator core. A prime strucutral material, such as an aircraft structural member, is integrally connected as by bonding or brazing to the insulator core, the core being attached to the prime structural material or aircraft structural member by an inner face sheet forming the outer skin of such structural member.

摘要翻译： 特别设计用于超音速航空航天车辆的整体结构和热保护系统由硬质外壳或由诸如碳化硅的陶瓷基体形成的外表面片以及泡沫陶瓷形式的刚性绝缘体芯组成， 作为碳化硅，外表面片与绝缘体芯一体连接。 诸如飞行器结构构件的主要结构材料通过粘合或钎焊一体地连接到绝缘体芯，芯通过形成这种结构的外表皮的内表面片附接到主结构材料或飞机结构构件 会员。

公开(公告)号：US5058830A

公开(公告)日：1991-10-22

申请号：US476849

申请日：1990-02-08

申请人： Stephen G. Wurst ,  Harry A. Scott

发明人： Stephen G. Wurst ,  Harry A. Scott

IPC分类号： B64D25/12

CPC分类号： B64D25/12

摘要： A crew protection system designed to isolate an aircraft crew and provide a means for safely evacuating an aircraft, particularly hypersonic vehicles, in emergency situations. The crew compartment is designed within the forebody of the main vehicle. The forebody is designed so as to separate cleanly from the main vehicle as by generation of a circumferential structural break, in the event of a catastrophic failure or explosion of the main vehicle fuel tank. In the event of such an uncommanded failure of the main tank and propellant combustion, resulting in the above noted structural failure, the resultant pressure impulse thrusts the forebody containing the crew compartment clear from the remainder of the vehicle. The provision of a system of baffles in the forebody between the crew compartment and the fuel tank, and the shape of the forebody and the materials used in its construction mitigate the effects of the blast pressure impulse on the crew. The forebody is also designed to be stable during the transient period immediately following the blast and the subsequent free fall of the forebody, permitting the crew to safely evacuate the crew compartment and forebody at a preselected altitude.

摘要翻译： 船员保护系统旨在隔离飞机机组人员，并提供在紧急情况下安全撤离飞机，特别是超音速车辆的手段。 船员舱设计在主车辆的前身内。 在主车辆燃料箱发生灾难性故障或爆炸的情况下，前体被设计成与主车辆清洁地分开，因为产生圆周结构断裂。 在主油箱和推进剂燃烧发生这种不命令的故障的情况下，导致上述结构失效，所得到的压力冲击从车辆的其余部分推开包含船员舱的前体。 在船员舱和燃料箱之间的前身提供挡板系统，以及在其构造中使用的前体和材料的形状减轻了冲击压力对船员的影响。 前身还被设计为在爆炸之后的瞬时期间和随后的自动坠落的前体期间稳定，允许船员在预选高度安全地撤离船员舱和前舱。

公开(公告)号：US4356616A

公开(公告)日：1982-11-02

申请号：US124196

申请日：1980-02-25

申请人： Harry A. Scott

发明人： Harry A. Scott

IPC分类号： B64C3/18 ,  B23P17/00

CPC分类号： B64C3/187 ,  Y10T29/49622 ,  Y10T29/49956 ,  Y10T29/49972

摘要： A method is disclosed for fabricating rib structures of different sizes for a segment of an airfoil having both a spanwise taper in thickness and at least one aerodynamic surface having a substantially constant radius of curvature in the chordwise direction. In one embodiment a plurality of rib webs are formed at least as large as the largest rib structure. Each of the rib webs is trimmed at their lower edges progressively greater amounts to form rib webs of a proper size for each rib structure. A plurality of upper and lower rib caps as well as front and rear spar attachment brackets are formed and attached to the trimmed rib webs. In another embodiment the rib webs are formed with either or both integral upper rib caps and spar attachment brackets. In still another embodiment a plurality of rib webs are formed and joined together by twos by inverting one rib web to the other and progressively overlapping their lower edges and fastening them together to form properly sized rib structures. These rib webs are formed with either or both integral upper rib caps and spar attachment brackets or they can be formed separately and attached to the joined rib webs. In the case where the spars are not spanwise parallel, the rib webs are formed without spar attachment brackets and thereafter at least one end of the rib webs and rib caps, whether integral or not, are also trimmed progressively greater amounts so that they are of the proper size for each rib structure.

摘要翻译： 公开了一种制造不同尺寸的肋结构的方法，用于具有厚度的翼展倾斜锥形和翼弦方向上具有基本上恒定曲率半径的至少一个空气动力学表面的翼型段。 在一个实施例中，多个肋腹板形成至少与最大肋骨结构一样大。 每个肋腹板在其下边缘处逐渐地修剪较大的量，以形成每个肋结构的适当尺寸的肋腹板。 多个上下肋盖以及前后翼梁附接支架形成并附接到修剪的肋腹板。 在另一个实施例中，肋腹板形成有一个或两个整体的上肋帽和翼梁附接支架。 在另一个实施例中，通过将一个罗纹腹板翻转到另一个并且逐渐与它们的下边缘重叠并将它们紧固在一起以形成适当尺寸的肋结构，由多个肋形成并通过二者连接在一起。 这些肋腹板形成有一个或两个整体的上肋盖和翼梁附接支架，或者它们可以单独形成并附接到连接的肋腹板上。 在翼梁不是翼展方向平行的情况下，肋腹板形成为没有翼梁连接支架，此后肋腹板和肋盖的至少一端（无论是否整体）也逐渐地修剪更大的量，使得它们是 每个肋骨结构的适当尺寸。