| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 221 | Automatic pilot system for model aircraft | US09413200 | 1999-10-05 | US06497600B1 | 2002-12-24 | Alejandro Velasco Levy; Ildiko Palyka |
| An automatic pilot system for a model airplane comprising one or more flexible control elements. When installed on a vertical stabilizer of the airplane, a flexible control element acts as an automatic rudder which provides directional control for the airplane so that it takes off in a straight line at high speed and glides in a circular path of a predetermined radius at low speed. When installed on a horizontal stabilizer of the airplane, a flexible control element acts as an automatic elevator which provides a reduced angle of attack during take-off to minimize the aerodynamic drag, an increased angle of attack during gliding flight to make the flight slower and longer-lasting, and an even greater angle of attack during landing to make the landing even slower for safety. When installed on a wing of the airplane, a flexible control element acts as an automatic dihedral wing tip which provides increased lateral stability for the airplane. When the automatic pilot system utilizes all three types of flexible control elements, it provides full three-dimensional automatic control. Each flexible control element constitutes a single-piece structure which integrates three functionally distinct sections: an attachment section, a flexing section, and a controlling section. | ||||||
| 222 | Strakes for landing speed reduction | US570342 | 1990-08-21 | US5249762A | 1993-10-05 | Andrew Skow |
| An engine inlet having strakes for landing speed reduction on a trapezoidal wing shaped aircraft, specifically the T-38. The strakes are mounted on the engine inlet just forward of the wing leading edge and well above the wing plane. The preferred strakes have an area greater than 3% of the wing area and are uncanted with respect to the wing. Use of the strakes forstalls wing buffet, yet exhibits well behaved longitudinal stability at high angles of attack thereby allowing operation of the aircraft at higher angles of attack and associated higher coefficients of lift, such as during landing, resulting in a reduction of the landing speed of the aircraft. Various strakes in the placement thereof are disclosed. | ||||||
| 223 | Dual towline spin-recovery device | US532342 | 1983-09-15 | US4538778A | 1985-09-03 | William L. White |
| A device which corrects aerodynamic spin wherein a parachute 38 exerts anti-spin forces on an aircraft 10 to effect spin recovery. The dual parachute towlines 30 and 32 are each attached to the parachute 38 and are attached to the rear fuselage equidistant to and on opposite sides of the aircraft centerline, at 25 and 27. As the parachute 38 is deployed during spin, the parachute force 40 acts through only the towline 30, and exerts its force outboard of center on the aircraft 10. As a result, the parachute exerts not only an anti-spin torque, but additionally causes the aircraft to roll, creating a gyroscopic anti-spin rolling moment. The additional anti-spin rolling moment facilitates spin recovery by permitting a relatively smaller parachute to accomplish spin recovery equivalent to that of a larger parachute attached to the center of the rear fuselage. The relatively smaller parachute enables spin recovery while minimizing the aerodynamic, structural and in-flight complications associated with larger parachutes and chute forces. | ||||||
| 224 | Extended moment arm anti-spin device | US508371 | 1983-06-27 | US4496122A | 1985-01-29 | Raymond D. Whipple |
| A device which corrects aerodynamic spin wherein a collapsible boom 42 extends an aircraft moment arm and an anti-spin parachute force 24 is exerted upon the end of the moment arm to correct intentional or inadvertent aerodynamic spin. This configuration effects spin recovery by means of a parachute 30 whose required diameter 32 decreases as an inverse function of the increasing length of the moment arm. The collapsible boom 42 enables the parachute 30 to avoid the aircraft wake 50 without mechanical assistance, retracts to permit steep takeoff, and permits a parachute 30 to correct spin while minimizing associated aerodynamic, structural and in-flight complications. | ||||||
| 225 | Aerodynamic side-force alleviator means | US19541 | 1979-03-12 | US4225102A | 1980-09-30 | Robert A. Administrator of the National Aeronautics and Space Administration, with respect to an invention of Frosch; Dhanvada M. Rao |
| Apparatus for alleviating high angle-of-attack side force on slender pointed cylindrical forebodies such as fighter aircraft, missiles and the like and employing a symmetrical pair of helical separation trips to disrupt the leeside vortices normally attained. The symmetrical pair of trips start at either a common point or at spaced points on the upper surface of the forebody and extend along separate helical paths along the circumference of the forebody. | ||||||
| 226 | Flap system | US3790106D | 1973-01-24 | US3790106A | 1974-02-05 | SWEENEY T; SCHWEIZER W; MORRIS J |
| A flap system for improving the lifting capabilities of aircraft wings and for alleviating the effects of wind gusts acting upon aircraft including flaps pivotally mounted near the trailing edges of the aircraft''s wings, which each have a separate and distinctive leading edge portion and a trailing portion which are pivotally connected. Locking apparatus are provided which can be actuated to lock the leading edge portion and the trailing edge portion of each flap together, and to maintain the leading edge portion of each flap in a stationary position relative to the wing when the trailing flap portion is disengaged from the leading edge flap portion. When the leading edge flap portion and the trailing edge flap portion are locked together, the flap serves as a high lift flap and when the leading edge flap portion is held in a stationary position with respect to the wing and the trailing edge flap portion is disengaged from the leading edge flap portion, the trailing edge flap portion is freely floating and acts as a gust alleviation flap.
|
||||||
| 227 | Adaptive missile guidance systems | US3588002D | 1967-10-24 | US3588002A | 1971-06-28 | WHITE ALBERT J |
D R A W I N G A MISSILE GUIDANCE STATION INCLUDING A RESOLVER FOR MODIFYING PITCH AND YAW DEMAND SIGNALS IN ACCORDANCE WITH AN ASSUMED MISSILE ROLL ANGLE, WHICH SIGNALS ARE TRANSMITTED TO THE MISSILE. MODELS OF THE PITCH AND YAW GUIDANCE LOOPS AT THE STATION RECEIVE SIGNALS REPRESENTING REQUIRED MISSILE PITCH AND YAW ANGLES. THE PERFORMANCE OF THESE MODELS IS COMPARED WITH THAT OF THE MISSILE AND THE DIFFERENCES IN PITCH AND YAW PERFORMANCE ARE USED TO ADJUST THE ANGLE OF THE RESOLVER. |
||||||
| 228 | Heading-setting device | US49954265 | 1965-10-21 | US3394676A | 1968-07-30 | FRANCOIS BONNEFONT EDMOND BERN |
| 229 | Pitch-stabilized, varying-sweep wing | US42588465 | 1965-01-15 | US3285542A | 1966-11-15 | HOLMQUIST WAYNE N |
| 230 | Roll control system and fluid tachometer therefor | US32693463 | 1963-11-29 | US3278139A | 1966-10-11 | BORCHER CHARLES A; WILLIAM FRANTZ |
| 231 | Roll stabilizing system for an airborne device | US29052463 | 1963-06-25 | US3204894A | 1965-09-07 | GOSTA GERTZELL NILS DAVID SVEN |
| 232 | Mass transfer attitude-control for space vehicles | US7657360 | 1960-12-19 | US3091417A | 1963-05-28 | MIKSCH RUSSELL S |
| 233 | Control means for aircraft in power-supported flight | US61447256 | 1956-10-08 | US3061241A | 1962-10-30 | HOLLAND JR RAYMOND PRUNTY |
| 234 | Gravity actuated airplane control | US78885959 | 1959-01-26 | US3032296A | 1962-05-01 | THEODORE STREUBEL |
| 235 | Pitch attitude stabilizing system for aircraft | US79191259 | 1959-02-09 | US3012741A | 1961-12-12 | ALICK CLARKSON |
| 236 | Control apparatus for an aircraft | US40712154 | 1954-01-29 | US2948495A | 1960-08-09 | MARGGRAF KURT A |
| 237 | Gust alleviating control means for airplanes | US72860847 | 1947-02-14 | US2584667A | 1952-02-05 | BOCKRATH GEORGE E |
| 238 | Fluid-dynamic stabilizer and damper | US68381446 | 1946-07-16 | US2573562A | 1951-10-30 | ADOLPH GARBELL MAURICE |
| 239 | Control of aircraft | US76469047 | 1947-07-30 | US2523579A | 1950-09-26 | JOHN LLOYD |
| 240 | Automatic stabilizer for airplanes | US57300245 | 1945-01-16 | US2496100A | 1950-01-31 | JOSE MARQUES; CASAS NOVAS |
QQ群二维码
意见反馈
意见反馈