JPS59216792A - Alarm system of abnormal speed of fall of strategic plane - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION This invention relates generally to ground proximity warning systems, and more particularly to:
The present invention relates to a system for alerting the pilot of a strategic aircraft, such as a fighter/attack aircraft, if the rate of descent of the aircraft is extreme relative to the altitude at which the aircraft is flying.

Systems are known for giving pylon warnings when an aircraft is descending too quickly during an approach. A typical example of such a system is U.S. Pat.
No. 3, 9'lZgOg No. 3, ? S-be,! l
No. 9 and each co/r. It is disclosed in the specification of J.3li.

If the aircraft's rate of descent exceeds a predetermined safe speed determined by the aircraft's radio altitude, are all of the above systems useful in performing basic functions for the pilot? The system described is a transport aircraft,
The patent is designed to work with large turbine-driven type aircraft flown by commercial airlines. Such transport aircraft are designed for transport aircraft because they have a typical flight feel that is considerably different from the flight profile of strategic aircraft, such as fighter/attack aircraft landing on aircraft carriers. This system is not effective for strategic aircraft. The reason for this is that these systems often fail to issue false warnings, causing pilots to "ignore" them and lose their effectiveness.

SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide a ground approach warning system that overcomes many of the problems of prior art warning systems.

Another object of the invention is that if the rate of descent of an aircraft is the altitude at which it is flying, l/C. Accordingly, if it is a day-to-day situation, the objective is to provide a lighting system that issues a warning to the pilots of strategic aircraft in the event of an approach.

Yet another object of this invention is that if the aircraft's descent rate during its flight is dangerously high, the Tl-4 luminescence standard is selected to match the operating procedures used in such strategic aircraft. The objective is to provide a ground approach warning system to replace the pilots of strategic aircraft.

Briefly, according to the preferred embodiment of the present invention, when the landing gear is down and the indicated flight speed is below Jθ0 knots,
A system is provided that monitors the rate of descent of the aircraft when the weapon is not in I+fifth position and issues an audible warning to the pilot if the rate of pressure drop exceeds a predetermined safety limit for the radio altitude at which the aircraft is flying. be done.

FIG. 1 shows an embodiment of the ground approach warning system according to the invention, designated by the street number IO. A system 10'l according to the present invention is illustrated in FIG. 1 in a logic block diagram such as gate groups, comparators, etc. The actual logical implementation includes various digital and analog implementations other than those shown in Figure 1. The signals used include radio altitude, barometric altitude velocity, flight speed, and , a signal indicating the position of the landing gear, and a signal indicating whether a weapon is equipped, along with various useful signals. Depending on the type of aircraft in which the warning system is installed, the signals shown in FIG. It is derived from a flight speed signal source 7g, such as a speed indicator, and various individual elements that indicate the position of the landing gear, whether it is equipped with weapons, whether the wheels are loaded or not. These 14 numbers may alternatively be obtained from a digital data bus in some newer aircraft.

Since this system is intended to be activated only during the approach to the landing phase of the flight profile, its operation is limited during Ike's Flight 7A to ensure that no false alarms are issued during these phases. is prohibited. This inhibit function consists of a pair of AND gates, 20 and 2, that monitor various flight conditions and flight configurations to fully determine whether the aircraft is on approach to landing.
．． This is accomplished by 2. Supervised by AND gateco OK
One parameter to be fMed is whether the landing gear is in F and if and when wheels 2 (weighted). Additionally, the signal indicating that the weapon is not mounted is AND Gate −θ is added because under normal persistence conditions no weapons are equipped. This indicates that it was working. In addition, the jilt speed is monitored by two comparators, and the flight speed is 30
Below 0 knots, a signal indicating a possible landing condition is provided to the AND gate OVC. Also, a signal indicating that the radio altitude signal and the barometric altitude IV gauge signal are not inhibited is also added to the AND gate to prevent the occurrence of a combination in the event of a malfunction of the barometric or radio altimeter.

In addition to this, to further reduce the potential for false alarms, the system provides a
Comparator circuit 26 responds to a signal from radio altimeter 76 and provides an l1if enable signal to AND gate 2 only when the aircraft is between 50 and 1000 feet of radio altitude.

If all of the above conditions are met, the AND gate 22 becomes operational and the pair of comparators, ? 0 and 3.2 by 1tjl) Hj be OR gate, 2g
be placed under the control of. The comparator 30 and JJ respond to the radio wave altitude and pressure velocity, and the descent speed is relative to a predetermined radio wave altitude)6. ' OR gate when 21
! 'When receiving the signal from comparator 30 or comparator 3- which adds the IC signal, OR gate 2g is AND gate 2.2VtCmo voice I! It acts to cause an alarm starting signal to be applied to an alarm circuit such as an alarm generator 3. As a result, the three alarm generators have a 5INK RATE.
The digital 'IC' is adapted to generate synthesized audio signals such as VC's and is VC'd to transmit those signals directly or indirectly to a transducer 36, such as a loudspeaker or earphone.

Illustrated Embodiment 2 In this example, there are 1.2 comparators 30.
Although used to determine the barometric velocity-radio altitude relationship required for generation of NM, a single signal comparator could also be used. However, it will be appreciated that due to the particular shape of the reporting curve shown in FIG. 2, it is convenient to use 1.2 separate comparators. Comparator Jθ is used to initiate an alarm for low radio altitudes and descending F rates of less than 300 Q feet/min. Comparator 3.2, on the other hand, is used to trigger a warning for descent rates of 3000 feet/minute or more. Comparator 3.2 thus monitors the signal from the pressure velocity circuit /q and is applied to the other terminal of comparator J2. A reference signal representing a rate of descent of 300 θ feet/min is compared with the signal from the air pressure velocity circuit/Z. The signal from the air pressure velocity circuit llI is
Whenever a reference signal representing a rate of descent of 3000 feet/min is exceeded, comparator J2
Add signals. This signal causes an OR gate, 2g
AND gate, 2.2 is enabled to generate an alarm. For a rate of descent below 30 θ ft/min, the air pressure is controlled by comparator 30 and determined by a step curve for a radio altitude of AOO ft and a rate of descent of 3000 ft/min as shown in FIG. Alarms are generated as a function of both descent speed and radio altitude. Typically, when the rate of descent exceeds 5000 feet/min at a radio altitude of 600 feet; when the rate of descent exceeds 2sθ0 feet/minute at a radio altitude of 200 feet; A "5INK RATg" alarm is generated when the altitude exceeds 50 feet/minute and the rate of descent exceeds 230 feet/minute.

The aforementioned relationship between the barometric velocity circuit and radio altitude required to generate the alarm is shown in detail in FIG. The shaded area under the graph in Figure 1 is light emission"5 If JK RA
The figures show the same various relationships between the lower velocity and the r+L wave height value.

This fallout is determined by the flight characteristics of fighter/attack bombers such as the Fairchild 810 and the manner in which such aircraft are operated during the landing flight phase.

Because such flight crows often fly relatively low and experience relatively high descent speeds during such low-altitude flights, the upper part of the envelope line in Figure 1 may be erroneous during maneuvers over 100 theta feet. VC is limited to 11,000 feet to prevent alarms from being issued.

This results in an envelope A that is considerably wider than the envelope route used for carriers flying out to altitudes of about 2'130 feet. Furthermore, the rate of descent allowed at relatively low altitudes is substantially greater for the strategy than for the transport aircraft. for example,
In the alarm envelope shown in Figure 2, the rate of descent to 2soo feet 1-/min is t
id↑8, do it. On the other hand, the G-Stem used for transportation sends out signals at about half of its descending speed. However, the allowable descent speed below 1.2 ft allows for a touchdown of 1a at an extremely fast descent speed.
Rapid trap reduction to about 1 kOθ feet/min at SO feet above ground level.

Obviously, many modifications and variations of the invention are possible in light of the above teachings. It is therefore intended that, within the scope of the appended claims, the invention may be practiced otherwise than as specifically described. be.

[Brief explanation of drawings]

@/Figure C Figure 1 is a logical block diagram of the optical system according to the present invention, and Figure 1 is a graph of the rate of pressure drop required to issue a warning as a function of radio altitude. 10, alarm system; /ko, pressure altitude 8 [; /g, pressure speed circuit; 16, radio altimeter; 7g, flight speed signal source;
, 7 t, t, "5INK RATE" alarm generator.

Claims (1)

[Scope of Claims] / Means for supplying a signal representing the flight speed of the aircraft in a signal system for issuing a warning to the pilot on approach to YC landing when the aircraft is making a sudden descent; Means for supplying a signal indicating the aircraft's descent speed; Means for supplying a signal indicating the aircraft's ground altitude; The flight speed signal supply means, the descending speed signal supply means, and the descending speed signal supply means; means responsive to the ground altitude signal supply means for issuing a warning when the aircraft is flying below a predetermined flight speed and has a rate of descent greater than a predetermined speed determined by the ground altitude of the air price; An alarm system comprising: the response means; 2. The warning system according to claim 1, wherein the predetermined flight speed is approximately 30θ knots. 3. The system includes means for supplying a signal indicative of the position of the land equipment of the aircraft, the aircraft position signal supply allowing the generation of said notification only when the land equipment is down. Patent m characterized by answering j6 to means
The alarm system described in Section 1. The punishment report is generated by the rqij aviation side or about 1 minute on the ground.
,．． 00 feet or less, approximately 3. θ00 feet/
10. The alarm system of claim 1, further comprising means for generating an h-alarm at a rate of descent greater than 1 minute. S The above-mentioned W alarm generating means is configured to detect when the descending F rate exceeds about 200 feet at a distance of about 200 feet above the ground.
The descending speed required to generate the final message is approximately ? Claim 9 of the VW patent, characterized in that the scope increases with ground altitude until required to generate a signal at an altitude of approximately 600 feet above ground level at a rate of descent of 1,000 feet per minute. Alarm system as described. 6. The above-mentioned ti alarm generating means further includes means for generating the above-mentioned alert when the descending speed exceeds about 600 feet at an altitude of about 50 feet above the ground, and it is necessary to generate a sled warning. The lower speed of 1riJ is approximately 2. 200 above the ground at a descent rate of SOθ ft/min.
A feature g characterized in that it increases with ground altitude until it is necessary to issue a warning at an altitude of 5 feet.
't-gi; Scope of Requirement The alarm system according to item S. 7. The above-mentioned substitute ￥υ36 means is 200 feet above the ground,
Claims further comprising means for linearly increasing the rate of descent necessary to generate an alarm at a distance between 200 feet and 600 feet above ground level. The path light system according to item 6. g. The warning system of claim 1, further comprising means for inhibiting generation of the warning when the altitude of the aircraft is less than about 50 feet above the ground. ? the aircraft is armed with a weapon, and the system includes means for detecting the weapon deployment of the aircraft to allow the generation of the alert only when the aircraft is equipped with a weapon; The U-information system according to claim 1, characterized in that all means for responding are covered. 10. The alarm system according to claim 1, wherein the descending speed signal supplying means includes means for supplying a signal representing the atmospheric pressure below M degrees.