Aerodynamic layout of horizontally taking-off and landing two stage to orbit aircraft

An aerodynamic layout and aircraft technology, applied in the aircraft field, can solve the problems that the power propulsion system cannot meet the requirements, and achieve the effects of meeting the fuel carrying requirements, improving heading stability, and good lift-drag performance

Inactive Publication Date: 2018-12-04
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among them, single-stage orbit entry can reduce the unit launch cost to the greatest extent, ...

Method used

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  • Aerodynamic layout of horizontally taking-off and landing two stage to orbit aircraft
  • Aerodynamic layout of horizontally taking-off and landing two stage to orbit aircraft
  • Aerodynamic layout of horizontally taking-off and landing two stage to orbit aircraft

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Embodiment 1

[0035] To transport a payload of 2 tons and 20 cubic meters to an orbit of 100 kilometers, the two-stage separation window is: Mach number 6, altitude 30 kilometers, and the two-stage aircraft that meet the above requirements are as follows:

[0036] The first level adopts the scheme of wing-body fusion body with waveriding properties and double vertical tails. The wing of this scheme is a strip-swept wing as shown in 9. The sweep angle is 60~70 degrees, and adopts Anti-down design, the down-reverse angle is 10~30 degrees, double vertical tails 10 and movable rudder surfaces 11 are arranged at the rear of the fuselage, the double vertical tails are arranged on both sides of the fuselage, and the movable rudder surfaces are located at the tail of the double vertical tails . The body is completely under the aircraft, adopts the cross-sectional shape shown in the bottom cross-section part 14, and is powered by a combined turbine / ramjet engine. The flaps shown in flap 12 are arra...

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Abstract

The invention discloses an aerodynamic layout of a horizontally taking-off and landing two stage to orbit aircraft. The aerodynamic layout of the horizontally taking-off and landing two stage to orbitaircraft comprises a first-stage aircraft and a second-stage aircraft, wherein the first-stage aircraft is of an anhedral design with waverider attribute and blended wing body twin-vertical tail; anaircraft body part of the first-stage aircraft is of a flat design; the back of the aircraft body part is of a smoothed design; and the smoothed part is used for placing the second-stage aircraft; thesecond-stage aircraft adopts an aerodynamic layout with a low aspect ratio sweptback wing, a wing-body combination and a single vertical tail; the aircraft body section of an aircraft body part of the second-stage aircraft is of semicircular and inverted-circular shape; and the belly part of the aircraft body part is a plane and is connected with the smoothed part of the back of the first-stage aircraft. According to the aerodynamic layout of the horizontally taking-off and landing two stage to orbit aircraft, various control functions of the first-stage aircraft and the second-stage aircraftcan be effectively enhanced, carrying requirements of fuel are satisfied, and good thermal protective performance is realized.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to an aerodynamic layout of a two-stage orbiting aircraft that adopts turbine / ram combined power for the first stage and rocket power for the second stage. Background technique [0002] Reuse is an important measure for space-to-earth shuttle vehicles to greatly reduce launch costs, greatly reduce launch cycles, and greatly improve aerospace applications. All space powers have realized that if they want to control the world, they must first control space. Focusing on the demand for fast, reliable and cheap access to space, countries have carried out a series of explorations on the layout of reusable launch vehicles: German scientist Sanger took the lead in proposing the idea of ​​a rocket engine-propelled "Silver Bird" aerospace bomber. Braun and Qian Xuesen proposed the concept of the reusable vehicle RLV. After World War II, the United States proposed a variety of aerospace vehicle concep...

Claims

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Application Information

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IPC IPC(8): B64D5/00B64C39/10B64C5/06B64C9/00
CPCB64C5/06B64C9/00B64C39/10B64C2009/005B64D5/00
Inventor 刘深深唐伟余雷赵鹏段焰辉冯毅张培红郭勇颜曾磊代光月
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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