| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Negative climb after take-off warning system with configuration warning means | US109580 | 1980-01-04 | US4319218A | 1982-03-09 | Charles D. Bateman |
| During a take-off or missed approach phase of operation the aircraft's maximum barometric altitude is retained in a memory element and compared to the aircraft's current altitude, and if the aircraft's current barometric altitude should be below the maximum altitude by a predetermined amount based on the aircraft's radio altitude, a voice warning is generated indicating that the aircraft is descending. Landing gear and flaps are monitored by the system and if the gear or flaps are down, an additional voice warning is generated indicating that the gear or flaps are down. | ||||||
| 142 | Slope sensor for a vehicle | US31968 | 1979-04-20 | US4231257A | 1980-11-04 | Yasuhisa Yoshino; Akira Kuno; Yoshio Shinoda |
| First and second sample-hold circuits sample and hold the atmospheric pressure alternately every time when a vehicle travels a predetermined distance. A signal representing a difference between the holding values of the first and second sample-hold circuits, that is, a signal representing a slope of the road on which the vehicle is travelling is displayed through a latch circuit. | ||||||
| 143 | Rate of change in altitude apparatus | US726882 | 1976-09-27 | US4112413A | 1978-09-05 | Donald Paul Muhs; Russell Frank Hart |
| A rate of change in altitude computer for providing a pilot with information to safely operate an aircraft. A beam of light is communicated through a mask. A gear responsive to altitude rotates the mask. A photocell receives the beam of light as it passes through the mask to produce sinusoidal wave signals. The positive node of the sinusoidal wave signal is modified to activate a transistor which allows a capacitor to be charged for a time period equal to the positive node. During the negative node of the sinusoidal wave signal the capacitor discharges. When the voltage associated with the charging and discharging of the capacitor is averaged, a steady state voltage is produced. The steady state voltage, which is proportional to the rate of rotation of the mask, drives a dial of an indicator to provide an operator with visual information relating to instantaneous rate of changes in altitude. | ||||||
| 144 | Circuit for measuring the rate of synchro rotation | US58139475 | 1975-05-27 | US3930143A | 1975-12-30 | MULLER HANS RUDOLF |
| Utilizing a three-wire input from a synchro, a signal representing the rate of rotation of the synchro shaft is generated by means of: summing amplifiers to generate signals representing the cosine of the shaft angle and the sine of the shaft angle; a circuit for generating a signal representing the tangent of the shaft angle; a circuit for generating the signal representing the cotangent of the shaft angle; feedback circuits for linearizing both the tangent and cotangent signals; a differentiator circuit for differentiating the tangent signal; a differentiator circuit for differentiating the cotangent signal; and a switching circuit for selecting the rate output from the differentiator with a linear output.
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| 145 | Aircraft rate trim system | US39077173 | 1973-08-23 | US3921941A | 1975-11-25 | LEHFELDT JAMES J |
| A method and apparatus are provided that enables a pilot of an aircraft to adjust, in a precise and smooth manner, various aircraft flight parameters while the aircraft is on a hold mode of an aircraft flight director or an autopilot flight control system. The preferred embodiment uses a signal input from a vertical gyro and an indicated air speed rate sensor to modify a trim rate command input to the autopilot or flight director, thereby enabling the aircraft to modify its air speed reference in the autopilot or flight director without disengagement of the flight control system.
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| 146 | Capacitance variometer | US3703828D | 1969-11-05 | US3703828A | 1972-11-28 | BULLARD EDWIN R JR; JOOSTEN WESLEY L |
| An electronic variometer or rate of climb indicator of the diaphragm capacitance type, having improved sensitivity and response time. Pressure is sensed by differential pressure transducer having dual capacitor elements and a diaphragm which deflects in response to changes in pressure. A leak tube extends from a back chamber within the pressure transducer into an atmospheric chamber. The problem of non-linearity is overcome by the use of the dual capacitor elements which are connected in circuit to adjust the frequency of oscillation of a square-wave oscillator. The two channel output of the oscillator is passed through filter networks to eliminate the oscillation frequency and is then sent to a differential amplifier and displayed on a meter.
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| 147 | Digital rate generator | US3603980D | 1969-10-03 | US3603980A | 1971-09-07 | VANWINKLE EDGAR W; KOSAKOWSKI HENRY R; HOLLINGER WALTER P |
| Apparatus associated with a digital condition sensor for providing a digital condition rate signal as a closed loop function of the sensed condition, and which signal is a continuous and precise measure of condition rate.
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| 148 | Altitude rate transducer and computing circuit | US3572115D | 1969-08-12 | US3572115A | 1971-03-23 | FEUER ROBERT |
| AN ALTITUDE RATE SIGNAL IS DEVELOPED ELECTRONICALLY BY DIFFERENTIATING A STATIC PRESSURE SIGNAL P AND SOLVING THE EQUATION DH/DT=-(K/P).(DP/DT) BY LINEAR OPERATIONS WHICH INCLUDE REPRESENTING THE PRODUCT OF P BY A VARIABLE VOLTAGE. IN ONE MODIFICATION A PIEZORESISTIVE STATIC PRESSURE TRANSDUCER IS ENERGIZED BY THE VOLTAGE, AND THE TRANSDUCER OUTPUT IS UTILIZED TO REPRESENT THE PRODUCT. ANOTHER MODIFICATION REPRESENTS THE PRODUCT BY LINEAR CIRCUITRY CAPABLE GENERALLY OF DERIVING ANY FUNCTION OF THE FORM AB/C FROM INPUT SIGNALS REPRESENTING A, B AND C. TWO CHOPPERS ARE DRIVEN SYNCHRONOUSLY WITH VARIABLE ON-OFF RATIO. CIRCUITRY INCLUDING ONE CHOPPER MAINTAINS THE CHOPPING RATIO PROPORTIONAL TO B/C, WHILE THE OTHER CHOPPER MULTIPLIES THAT FUNCTION BY A.
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| 149 | High altitude rate of climb indicator | US3456506D | 1967-06-28 | US3456506A | 1969-07-22 | MAGNUSON LEO D |
| 150 | Rate of climb and descent readout device | US3421370D | 1966-11-04 | US3421370A | 1969-01-14 | NOIA EMANUEL J DI; BREUNICH THEODORE R |
| 151 | Vertical rate sensor | US44413765 | 1965-03-31 | US3374671A | 1968-03-26 | WILLIAMS SIDNEY B; RIGNEY EDWARD T |
| 152 | Rate of climb indicator | US52321966 | 1966-01-26 | US3369397A | 1968-02-20 | MAX ALTH |
| 153 | Altitude rate indicating system | US45661765 | 1965-05-18 | US3358505A | 1967-12-19 | ANDRESEN JR JOHN H |
| 154 | Flow meter | US47043165 | 1965-07-08 | US3327528A | 1967-06-27 | VALGOI ERWIN G |
| 155 | Vertical velocity indicator | US32154163 | 1963-11-05 | US3262312A | 1966-07-26 | WALTER ANGST |
| 156 | Rate of climb indicators | US26455463 | 1963-03-12 | US3237452A | 1966-03-01 | MAX ALTH |
| 157 | Flight condition sensing | US2368860 | 1960-04-21 | US3209593A | 1965-10-05 | JOHANSON CARL E |
| 158 | Vertical speed indicator | US83923859 | 1959-09-10 | US3098381A | 1963-07-23 | LITTLE DAVID S; PORT WASHINGON; PIKE EDWARD W |
| 159 | Aircraft instruments | US57787756 | 1956-04-12 | US3055214A | 1962-09-25 | MCLANE ROBERT C |
| 160 | Rate of climb indicator | US78287758 | 1958-12-24 | US3040569A | 1962-06-26 | GRAY WALTER W |
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