• 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:
    1500636 Ground proximity warning systems SUNDSTRAND DATA CONTROL Inc 24 Feb 1976 [2 April 1975] 07219/76 Heading B7W A ground proximity warning system forces the crew to increase the altitude of the aircraft by a predetermined amount (200 ft.) every time a terrain closure warning is generated. An initial warning received along line 24 sets flip-flop 26 to produce and maintain a continuous closure warning via OR gate 32 and an AND gate 34. To terminate the warning the aircraft must climb at a rate (hÀ B ) of at least 300 ft./min., which causes a signal to be fed along line 36 to AND gate 34 to inhibit the warning signal. When the aircraft has climbed at least 200 feet, measured by integrating at 48 the rate of climb signal hÀ B , the flip-flop is reset. Should the aircraft reduce its climbing rate to below 300 ft./min. before climbing 200 ft. the warning signal is reactivated. An OR gate 61 may be provided to maintain a warning signal if the aircraft continues to approach the terrain even though it is still climbing above the predetermined rate of 300 ft./min.
    公开号:SU797615A3
    申请号:SU762339651
    申请日:1976-04-02
    公开日:1981-01-15
    发明作者:Д. Бэйтмэн Чарльз；Р. Мюллер Ханс；Дж. Брем Фрэнк
    申请人:Сандстрэнд Дейта Контрол, Инк (Фирма)；
    IPC主号:
    专利说明:

    one
    The invention relates to means of warning about the approach of an aircraft to the earth's surface and about the excessive speed of this approximation.
    Closest to the proposed is a warning system containing a radio altimeter and a speed sensor for changing the barometric altitude, the outputs of which are connected to the inputs of the device forming the signal about the dangerous approach of the aircraft to the earth's surface l. .
    In a known system, a warning signal is generated if the speed of approaching the earth's surface is too high for a given flight altitude, and turns off as soon as the earth's surface begins to move away from the flight path. In some cases, for example, when flying over a terrain with a wave-like surface, whose average height gradually increases, such a system cannot ensure flight safety.
    The purpose of the invention is to increase the reliability of the warning.
    The goal is achieved by the fact that in the warning system; containing a radio altimeter and a speed sensor for changing the barometric altitude, the outputs of which are connected to the inputs of the signal generation device, a memory element, an OR element, a height increment determination device, a first and a second threshold devices and a prohibition element are added, the output of the signal forming device is connected with; the recording input of the memory element and the first input of the OR element, the second input of koToporo is connected to the output of the PS element, and the output is connected to the signal input of the prohibition element, the output of the memory element is also connected to the control input of the height incrementing device, the signal input of which is connected with the output of the speed sensor, the change in barometric altitude, and the output connected to the input. The first threshold device, the output of which is connected to the memory input of the memory element, the input of the second threshold device is connected to the output of the velocity sensor of varying barometric altitude, and the output is connected to the control input of the prohibition element whose output is the output of the entire system. The memory element can be executed, for example, in the form of a static trigger. The triggering level of the first and second threshold devices should be set at 60 m, and the second one - 1.5 m / s. In addition, in order to prevent the formation of a false warning signal during the landing approach, the system further comprises a second OR element connected between the output of the first threshold device and the erase input of the memory element. Fig. 1 is a block diagram of a warning system; in fig. 2 - the change of the trajectory itself when using the proposed system in the case of flight over a wavy surface with increasing average height. The warning system contains a radio altimeter 1, a sensor 2, a velocity change of a barometric altitude, a signal generation device 3, a device 4 defined height increments, first 5 and second 5 threshold devices, memory element 7, prohibition element 8, first L second 10 elements OR, The warning system works as follows. The signals of the speed sensor of changing the barometric altitude 2 and for the sake of the altimeter 1 are fed to the inputs (Devices 3 form an alarm signal generating a signal for the EB of a dangerous approach of the aircraft to the ground according to the ratio of the current altitude and speed of its change. This signal is fed to the 5 recording memory of memory 7 1 at the same time - to one element of the element, OR 9, from the output of which 1 prohibition element 8 passes through the system’s output 11, if the control input of prohibition element 8 is the iT signal generated by the threshold device 6. The last. The esli rate of change of altitude increases beyond a predetermined value, for example, 1.5 m / s. Simultaneously with the output of the signal at the output of the alert signal generating device 3, the signal at the output of the memory element, which turns on the device t for determining the height increment, is ignored. memory element 7, I therefore, at the output of the OR element 9 as well as at the output 11 of the system in the absence of prohibiting the le signal from the output of the threshold / device 6) remains until the sign of the specified height increment (nap Example 60 m) at the output of the threshold device 5, the latter erases {Signal stored in the element 7 Psm. At the same time, if there is no signal at the output of the device for generating the alert signal 3. there is no longer, disappears, and the signal at the output II of the entire system. If the climb is fast enough, the warning signal at the system output 11 is turned off by the output signal of the threshold device 6, which acts on controlling the input of the prohibition element 8. Signals 12 and 13, arriving at the second and third inputs of the element OR 10, prevent the memory element 7 from triggering when approaching, when the flaps are lowered or the height is less than 15 m. 1, the kinks of the aircraft trajectories due to the inertia of the control process are somewhat delayed with respect to the instants of occurrence and disappearance of the warning signal at output 11 ,. Point 14 corresponds to the moment of the first occurrence of the signal at the input of the device 3 generating the alert signal (timing diagram A). At point 15 this signal disappears, however, the warning signal at output 11 (timing diagram 6) is retained due to the presence of memory element 7, since the increment of the height has not yet reached the threshold of the threshold device 5 (for example, 60 m). At point .16, the warning signal is interrupted by the prohibition element 8 as a result of the trigger of the threshold device 6 (time diagram B) due to awns climb At point 17 the inhibiting signal is removed, and a warning signal occurs at the output 11 again increments As set predetermined height is not yet finished. The warning signal is turned off at point 18 when the height increment reaches a predetermined value and the threshold device 5 is triggered. At point 19, the warning signals (temporary, diagram A) and warnings (temporary diagram 6) reappear. At point 20, the alert signal disappears, but the alert signal still remains. Beginning at 21, there is no warning signal, because the climb rate is quite high. In the proposed system, the warning signal does not disappear simultaneously with the disappearance of the signal at the output of the warning device immediately after the earth's surface begins to move away from the flight path. This signal is turned off when a predetermined elevation height is reached after the appearance of the signal at the output of the device 3 generating the alert signal;; which provides a safe field over the terrain with a wave-like rel-wave when there is an increase in the average height.
    权利要求:
    Claims (4)
    [1]
    1. A warning system containing a high altitude sensor and a speed sensor for changing the barometric altitude, the outputs of which are connected to the inputs of the alert signal generation device, characterized in that, to increase the reliability of the warning, the memory element of the increment OR is added to it. the heights, the first and second threshold devices and the prohibition element, wherein the output of the alert signal generating device is connected to the recording input of the memory element and the first input and OR, the second input of which is connected to the output of the memory element, and the output to the signal input of the prohibition element, the output of the memory element is also connected to the control input of the height incrementing device, the signal input of which is connected to the output of the rate change sensor
    [2]
    barometric height, and the output is connected to the input of the first threshold device, the output of which is connected to the memory element input, the input of the second threshold device f is connected to the output of the speed sensor of changing the barometric height, and the output to the control input of the prohibition element whose output is the output of the entire system. : 2. The system of claim 1, is different, ayu with the fact that the memory element is designed as a static trigger.
    [3]
    3. The system according to claim 1, characterized in that the response levels of the first and second threshold devices are set (equal to, respectively, 60 m and 1.5 m / s.
    [4]
    4. Pop-up system 1, characterized in that, in order to prevent the formation of a false warning signal during landing, it further comprises a second OR element connected between the output of the first threshold device and the erased input of the memory element.
    Sources of information taken into account in the examination
    1. US patent 3,715,718, cl. 340-27 P, published. 1973 (prototype).
    K 13
    f {1 &. I
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    同族专利:
    公开号 | 公开日
    JPS5745322B2|1982-09-27|
    SE7603427L|1976-10-03|
    DE2554206C3|1980-02-07|
    JPS51120599A|1976-10-21|
    FR2306430A1|1976-10-29|
    CA1039535A|1978-10-03|
    AU502561B2|1979-08-02|
    GB1500636A|1978-02-08|
    AU8626875A|1977-05-12|
    IT1058062B|1982-04-10|
    DE2554206B2|1979-06-13|
    US3934222A|1976-01-20|
    DE2554206A1|1976-10-07|
    FR2306430B1|1978-05-19|
    SE429789B|1983-09-26|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    US05/564,512|US3934222A|1975-04-02|1975-04-02|Terrain closure warning system with climb inhibit and altitude gain measurement|
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