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给出了一种低速飞行时使用空气－涡轮－火箭发动机、高速飞行时使用火箭发动机加速、且二者都以液氢为燃料的完全可重复使用、水平起降、从地球发射入轨的运载器方案。用液体空气循环为涡轮－火箭发动机提供氧化剂。当涡轮－火箭发动机以Ｍａ＝２～５或６在大气中飞行时，可收集、分离和贮存纯液氧，为后继火箭发动机提供９０％的氧化剂。这样可使起飞重量和所需推力大大减小。在收集空气末段降低轨道高度，可减小翼面积，从而增大载荷。用现代材料（如石墨聚合物）直接取代铝或铝锂合金是达到单级入轨运载器结构重量目标的关键因素。采用“驾波器”气动力构型，也是一项很有希望减轻运载器重量的措施。
An example is given of an air-turbine-rocket engine for low-speed flight, rocket-engineered for high-speed flight, and fully reusable with both liquid hydrogen and fuel, horizontal take-off and landing, Program. Liquid air circulation provides oxidizer to the turbine-rocket engine. When turbo-rocket engines fly in the atmosphere at Ma = 2-5 or 6, pure liquid oxygen can be collected, separated and stored to provide 90% of the oxidizer to subsequent rocket engines. This will takeoff weight and thrust required greatly reduced. Lowering the orbit height at the end of the collection of air reduces the wing area and increases the load. The direct replacement of aluminum or lithium-aluminum alloys with modern materials such as graphite polymers is a key factor in achieving the structural weight goal of a single-stage rail-in carrier. The use of a “navigator” aerodynamic configuration is also a very promising way to reduce the weight of a carrier.