Terminal airways traffic control system
阅读：642发布：2020-08-30
专利汇可以提供Terminal airways traffic control system专利检索，专利查询，专利分析的服务。并且A system for scheduling aircraft arrivals from cruise to touchdown, and also for scheduling departures from airport to cruise altitude; wherein space considerations are reserved to the aircraft pilot and wherein time considerations are reserved to the control authority. The aircraft is navigated by the pilot along a Terminal Corridor Route (TCR) in conformance to the requirements of a ground based Traffic Control Computer (TCC). The airborne Aircraft Instrumentation Computer (AIC) includes a programmed computer and an instrument panel display that positions the aircraft relative to an optimum time flexible energy path and responsive to in-flight data which is also telemetered to the TCC for processing. The TCC repeatedly processes all in-range aircraft on a time cycle basis and imposes and regulates time intervals between said aircraft by issuing speed-up and slow-down commands thereto as necessary to qualify said aircraft to proceed, and alerts the control authority and pilot as well of aircraft which do not qualify and/or require corrective proceedures. The system identifies all in-range aircraft and sequentially programs the flight paths thereof along the required track and through waypoints; taking into account the kinetic as well as potential energies involved for executing practical and efficient flight to the ends of infallible traffic control and safety, economy, antipollution and noise abatement.，下面是Terminal airways traffic control system专利的具体信息内容。
1. In combination: aircraft borne instrumentation comprising, means generating an altitude signal, means generating a waypoint altitude signal, and telemetering means transmitting said aforementioned signals as in-flight navigational data; and a remote based computer comprising, telemetering means receiving said aforementioned signals, and position computer means relating said aforementioned signals and processing the same each according to its effect into a computed distance to said waypoint signal.
2. The combined airborne instrumentation and remote based computer as set forth in claim 1 and wherein the position computer means relates said aforementioned in-flight data signals and said waypoint altitude signal and processes the same according to the ascent formula Pwc S (Aw - A/1,000); wherein Pwc is the computed distance from waypoint in ascent, S is the slope constant, Aw is altitude of the waypoint, and A is the aircraft altitude.
3. The combined airborne instrumentation and remote based computer as set forth in claim 1, wherein the aircraft borne instrumentation includes means generating a deceleration requirement signal and said telemetering means transmits said signal, and wherein said means relating said aforementioned signals processes said deceleration requirement signal according to its effect into said computed distance to said waypoint signal.
4. The combined airborne instrumentation and remote based computer as set forth in claim 1, wherein the aircraft borne instrumentation includes means generating a groundspeed signal and means generating a deceleration requirement signal and said telemetering means transmits the same, and wherein the position computer means relates said aformentioned inflight data, said groundspeed signal, said deceleration requirement and said altitude and waypoint altitude signals and processes the same according to the formula Pwd S (A - Aw/1,000) + K (GS - Fs) lim 0; wherein Pwd is the computed distance from waypoint in descent, S is the slope constant, A is the aircraft altitude, Aw is altitude of the waypoint, K is the variable conversion factor, GS is the groundspeed, and Fs is the predetermined minimum speed.
5. The combined airborne instrumentation and remote based computer as set forth in claim 1 and wherein the aircraft borne instrumentation includes means generating a groundspeed signal, means generating a deceleration requirement signal and said telemetering means transmits the same, and said means relatiNg said aforementioned signals and processing in-flight data including groundspeed according to the formula K (GS - Fs) lim 0; wherein K is the variable conversion factor, GS is the groundspeed, and Fs is the predetermined minimum speed.
6. The combined airborne instrumentation and remote based computer as set forth in claim 1, wherein the aircraft borne instrumentation includes means generating a groundspeed signal, means generating a deceleration requirement signal and said telemetering means transmits the same, and means relating said aforementioned signals and processing in-flight data including groundspeed according to the formula K (GS + Fs) lim 0, and wherein the position computer means relates said aforementioned in-flight data signals and said waypoint altitude signal and processes the same according to the formula Pwd S (A - Aw/1, 000) plus the aforementioned formula K (GS - Fs) lim 0; wherein Pwd is the computed distance from waypoint in descent, S is the slope constant, A is the aircraft altitude, Aw is the altitude of the waypoint, K is the variable conversion factor, GS is the groundpseed, and Fs is the predetermined minimum speed.
7. In combination: aircraft borne instrumentation comprising, means generating an altitude signal, means generating a waypoint altitude signal, means generating a remaining distance signal, and telemetering means transmitting said aforementioned signals as in-flight navigational data; and a remote based computer comprising, telemetering means receiving said aforementioned signals, position computer means relating said aforementioned signals and processing the same each according to its effect into a computed distance to said waypoint signal, and position comparator means relating said remaining distance signal and computed distance to said waypoint signal and producing a position differential signal for operation of and monitoring of the aircraft.
8. The combined airborne instrumentation and remote based computer as set forth in claim 7 and wherein the position computer means relates said aforementioned in-flight data signals and processes the same according to the ascent formula Pwc - S (Aw - A/1,000); wherein Pwc is the computed distance from waypoint in ascent, S is the slope constant, Aw is altitude of the waypoint, and A is the aircraft altitude.
9. The combined airborne instrumentation and remote based computer as set forth in claim 7, wherein the aircraft borne instrumentation includes means generating a deceleration requirement signal and said telemetering means transmits said signal, and wherein said means relating said aforementioned signals processes said deceleration requirement signal according to its effect into said computed distance to said waypoint signal.
10. The combined airborne instrumentation and remote based computer as set forth in claim 7, wherein the aircraft borne instrumentation includes means generating a groundspeed signal and means generating a deceleration requirement signal and said telemetering means transmits the same, and wherein the position computer means relates said aforementioned in-flight data, said deceleration requirement and said altitude and waypoint altitude signals and processes the same according to the formula Pwd S (A - AW1,000) + K (GS - Fs) lim 0; wherein Pwd is the computed distance from waypoint in descent, S is the slope constant, A is the aircraft altitude, Aw is altitude of the waypoint, K is the variable conversion factor, GS is the groundspeed, and Fs is the predetermined minimum speed.
11. The Combined airborne instrumentation and remote based computer as set forth in claim 7 and wherein the aircraft borne instrumentation includes means generating a groundspeed signal, means generating a predetermined minimum speed signal, and means relating said aforementioned signals and processing in-flight data into a deceleration requirement signal according to the formula K (GS - Fs) lim 0 and said telemetering means transmits the same; wherein K is the variable conversion factor, GS is the groundspeed, and Fs is the predetermined minimum speed.
12. The combined airborne instrumentation and remote based computer as set forth in claim 7, wherein the aircraft borne instrumentation includes means generating a groundspeed signal, means generating a predetermined minimum speed signal, and means relating said aforementioned signals and processing in-flight data into a deceleration requirement signal according to the formula K (GS - Fs) lim 0 and said telemetering means transmits the same, and wherein the position computer means relates said aforementioned in-flight data signals and processes the same according to the formula Pwd S (A - Aw/1,000) plus the aforementioned formula K (GS - Fs) lim 0; wherein K is the variable conversion factor, GS is the groundspeed, Fs is the predetermined minimum speed, Pwd is the computed distance from waypoint in descent, S is the slope constant, A is the aircraft altitude, and Aw is altitude of the waypoint.
13. In combination: aircraft borne instrumentation comprising, means generating an altitude signal, means generating a waypoint altitude signal, means generating a remaining distance signal, and telemetering means transmitting said aforementioned signals as in-flight navigational data; and a remote based computer comprising, telemetering means receiving said aforementioned signals, position computer means relating said aforementioned signals and processing the same each according to its effect into a computed distance to said waypoint signal, position comparator means relating said remaining distance signal and computed distance to said waypoint signal and producing a position differential signal, and space tolerance means establishing permissible deviation from the remaining distance and with a comparator means determining when said position differential signal is a value greater than a predetermined value and with alert means issuing an alert signal when said determination is made by said comparator means, said alert signal being useful for operation of and monitoring of the aircraft.
14. The combined airborne instrumentation and remote based computer as set forth in claim 13 and wherein the said last mentioned comparator means determines when said position differential signal is a value greater than a predetermined maximum value.
15. The combined airborne instrumentation and remote based computer as set forth in claim 13 and wherein the said last mentioned comparator means determines when said position differential signal is a value lesser than a predetermined minimum value.
16. The combined airborne instrumentation and remote based computer as set forth in claim 13, wherein the said last mentioned comparator means determines when said position differential signal is either greater than a predetermined maximum value or said position differential signal is lesser than a predetermined minimum value, and wherein said alert means issues an alert signal when either determination is made.
17. The combined airborne instrumentation and remote based computer as set forth in claim 13, wherein the aircraft borne instrumentation includes means generating a deceleration requirement signal and said telemetering means transmits said signal, wherein said means relating said aforementioned signals procesSes said deceleration requirement signal according to its effect into a computed distance to said waypoint signal, and wherein the said last mentioned comparator means determines when said position differential signal is a value greater than a predetermined maximum value.
18. The combined airborne instrumentation and remote based computer as set forth in claim 13, wherein the aircraft borne instrumentation includes means generating a deceleration requirement signal and said telemetering means transmits said signal, wherein said means relating said aforementioned signals processes said deceleration requirements signal according to its effect into said distance to said waypoint signal, and wherein the said last mentioned comparator means determines when said position differential signal is a value lesser than a predetermined minimum value.
19. The combined airborne instrumentation and remote based computer as set forth in claim 13, wherein the aircraft borne instrumentation includes means generating a deceleration requirement signal and said telemetering means transmits said signal, wherein said means relating said aforementioned signals processes said deceleration requirement signal according to its effect into said computer distance to said waypoint signal, and wherein the said last mentioned comparator means determines when said position differential signal is either greater than a predetermined maximum value an alternately lesser than a predetermined minimum value, and wherein said alert means issues an alert signal when either determination is made.
20. The combined airborne instrumentation and remote based computer as set forth in claim 13, there being level flight squelch means holding the said alert signal in abeyance responsive to altitude deviation sensing means.
21. The combined airborne instrumentation and remote based computer as set forth in claim 13, there being level flight squelch means holding the said alert signal in abeyance responsive to altitude deviation sensing means determining when the altitude signal deviates greater than a predetermined tolerance value.
22. The combined airborne instrumentation and remote based computer as set forth in claim 13, wherein the said last mentioned comparator means determines when said position differential signal is either greater than a predetermined maximum value and alternately lesser than a predetermined minimum value, and wherein said alert means issues an alert signal when either determination is made, there being level flight squelch means holding said alert signal in abeyance responsive to altitude deviation sensing means.
23. The combined airborne instrumentation and remote based computer as set forth in claim 13, wherein the said last mentioned comparator means determines when said position differential signal is either greater than a predetermined maximum value and alternating lesser than a predetermined minimum value, and wherein said alert means issues an alert signal when either determination is made, there being level flight squelch means holding the said alert signal in abeyance responsive to altitude deviation sensing means determining when the altitude signal deviates greater than a predetermined tolerance value at which time the squelch means is ineffective.
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