• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    1. A DAMAGED AERODYNAMIC BRAKE OF SPACE AIRCRAFT, containing symmetrically installed brake plates attached to the edge of an aircraft, characterized in that, in order to reduce the speed of the aircraft when entering from space into the atmosphere of the Earth, each brake plate is made of a refractor material rigidly connected to the grip on the leading edge, while the braking 1TECO is filled with a cross section decreasing from the leading edge to the rear The self-braking flap is concave in the direction of the direction, with its rear end perpendicular to the direction of flight. 2. A brake according to claim 1, characterized in that the brake flaps are installed symmetrically on the upper and lower surfaces of the wings. 3. Brake on PP. 1 and 2, which is distinguished by the fact that the concavity of the brake pads installed on the upper and lower surfaces of the wings is the same. ate with
    公开号:SU1151199A3
    申请号:SU792714302
    申请日:1979-01-22
    公开日:1985-04-15
    发明作者:М.Лоэб Карл (Младший)
    申请人:Карл М. Лоэб (США)；
    IPC主号:
    专利说明:

    The invention relates to aviation and space technology.
    Aerodynamic brakes for aircraft are known; made in the form of symmetrically mounted 5 brake flaps mounted on the wings of the aircraft £ ΐ3. However, their use for spacecraft is difficult due to the high braking temperatures of 10 when space enters the atmosphere.
    The purpose of the invention is to provide a reduction in the speed of the aircraft at the entrance from space J5 to the Earth’s atmosphere.
    The goal is achieved in that in a destructible aerodynamic brake of a spacecraft containing symmetrically mounted 20 brake flaps mounted on the wings of the aircraft, each brake flap is made of refractory sheet material rigidly connected to the wing along the front 25 edge, while the brake flap is made with a cross section decreasing from the leading edge to the rear, and the brake flap itself is made concave in the direction of flight, with 30 its rear end perpendicular to the direction flight direction.
    In addition, the brake flaps are mounted symmetrically on the upper and lower surfaces of the wings. 5
    The concavity of the brake flaps mounted on the upper and lower surfaces of the wings is the same.
    In FIG. 1 schematically shows a spacecraft with the proposed aerodynamic brake, plan view; in FIG. 2 - the proposed aerodynamic brake, side view; in FIG. 3 - the proposed aerodynamic brake in the process of its destruction during braking of the aircraft.
    On the wings 1 and 2 of the spacecraft 3 symmetrically mounted on the upper and lower surfaces of the brake flaps 4,5.
    The brake flaps are made in the form of a thin, hard, refractory sheet element of variable cross section, decreasing in the direction of the free end of the flap. The shield is made of refractory material, such as molybdenum and beryllium, concave in the direction of flight of the aircraft. The concavity of all brake flaps is the same.
    In the process of entering the dense layers of the atmosphere, the brake flaps gradually collapse (melt) in the direction from the free end of the flap to its root part.
    The brake can fail partially or completely, so it does not have a noticeable effect on handling when landing.
    Phil
    权利要求:
    Claims (3)
    [1]
    1. A DESTRUCTIBLE AERODYNAMIC BRAKE OF A SPACE AIRCRAFT, containing symmetrically mounted brake flaps mounted on the wings of an aircraft, characterized in that, in order to reduce the speed of the aircraft when entering from outer space into the Earth’s atmosphere, each brake flap is made of refractory sheet material rigidly connected to the wing along the leading edge, while the brake flap is made with a cross section that decreases from the leading edge to the rear, and with the brake flap is made concave in the direction of flight, and its rear end is perpendicular to the direction of flight.
    [2]
    2. Brake pop. 1, characterized in that the brake flaps are mounted symmetrically on the upper and lower surfaces of the wings. §
    [3]
    3. The brake according to paragraphs. 1 and 2, characterized in that the concavity of the brake flaps mounted on the upper and lower surfaces of the wings is made the same.
    SU, .. 1151199
    1151199 2
    类似技术:
    公开号 | 公开日 | 专利标题
    US3744745A|1973-07-10|Liftvanes
    US4739957A|1988-04-26|Strake fence flap
    GB2036668A|1980-07-02|Horizontal landing arrangement for a flying body
    SU1151199A3|1985-04-15|Collapsing aerodynamic brake of spacecraft
    US2500015A|1950-03-07|Frame structure for airplanes
    US2562905A|1951-08-07|Means for increasing lateral stability of aircraft
    US2362804A|1944-11-14|Rotary wing for aircraft
    US2743887A|1956-05-01|Split aircraft wing
    GB2093152A|1982-08-25|Boundary Layer Control
    US3064927A|1962-11-20|Retractable auxiliary leading edge for high-speed wings
    JPS5459798A|1979-05-14|Aircraft that direction of empennage can be varied
    Solomon et al.1953|Effect of Longitudinal Wings Position on the Pressure Characteristics at Transonic Speeds of a 45© Sweptback Wing-fuselage Model
    Fischel et al.1955|Effect of several wing modifications on the low-speed stalling characteristics of the Douglas D-558-II research airplane
    Howell1955|An Experimental Study of a Method of Designing the Sweptback-Wing-Fuselage Juncture for Reducing the Drag at Transonic Speeds
    US3326499A|1967-06-20|Ribs on airplane wings
    Boermans et al.1982|Design and tests of airfoils for sailplanes with an application to the ASW-19 B.
    JPS53119599A|1978-10-19|Ultrasonic wing for aircraft
    Hilbig et al.1989|The intelligent wing-Aerodynamic developments for future transportaircraft
    Nakai et al.1973|Some effects of center of gravity locations of added mass on transonic flutter characteristics of low aspect ratio and sweptback thin cantilever wing
    Erickson et al.1992|Effects of forebody strakes and Mach number on overall aerodynamic characteristics of configuration with 55 deg cropped delta wing
    ALLEGRE1971|Delta wings, with or without trailing edge flap, in a rarefied hypersonic gas flow|
    RAO et al.1981|Wind-tunnel studies of advanced cargo aircraft concepts|[Final Report, 22 Jun. 1979- 21 Jun. 1980]
    PATTERSON1976|Wingtip vortex dissipator for aircraft[Patent]
    AU4214789A|1990-03-23|Generation of an aerodynamic force by lateral blowing of air at the underwing of aircraft wings from the wing extremities towards the wing root at the aircraft fuselage
    BUTLER et al.1963|Analysis of boundary layer controls for high lift at low speeds along trailing-edge flaps, and the design features required for optimum performance
    同族专利:
    公开号 | 公开日
    GB2012690B|1982-02-10|
    DE2901015A1|1979-08-02|
    GB2012690A|1979-08-01|
    JPS54113124A|1979-09-04|
    FR2415042B1|1984-02-17|
    FR2415042A1|1979-08-17|
    US4186900A|1980-02-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2418273A|1944-12-26|1947-04-01|Willard H Moore|Aircraft wing flap assembly|
    US3067971A|1959-10-01|1962-12-11|North American Aviation Inc|Super drag flap|
    US3137995A|1960-01-26|1964-06-23|Chemical Engineering Dept|Ablation resistant reaction propulsion nozzle|
    US3189477A|1960-04-13|1965-06-15|Carborundum Co|Oxidation-resistant ceramics and methods of manufacturing the same|
    US3243313A|1960-04-25|1966-03-29|Ling Temco Vought Inc|Heat-resistant article|
    US3287019A|1964-04-20|1966-11-22|Arthur Norman Robert|Maneuverable target for anti-missile systems|US4784350A|1979-02-12|1988-11-15|The United States Of America As Represented By The Secretary Of The Navy|Passive step trimmer for a maneuvering re-entry body |
    US5457471A|1984-09-10|1995-10-10|Hughes Missile Systems Company|Adaptively ablatable radome|
    ES8706942A1|1986-04-16|1987-07-01|Esperanza & Cie Sa|Mortar grenade|
    US5125600A|1991-06-03|1992-06-30|Rockwell International Corporation|Removable radome cover|
    GB9425078D0|1994-12-13|1995-02-08|British Airways Plc|A seating unit|
    GB9813558D0|1998-06-24|2002-03-06|Royal Ordnance Plc|Device for exerting drag|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US05/871,615|US4186900A|1978-01-23|1978-01-23|Disintegratable aerodynamic brake|
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