US4071893A
Expired / Lapsed
US
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Flying method and system using total power for an aircraft
Assignee: Societe Francaise dEquipements pour la Navigation Aerienne SFENA SA
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Filing: 1976-07-06
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Granted: 1978-01-31
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Expires: 1996-07-06
Abstract
Abstract A flying method using total power, in particular for the take-off and overshoot of an aircraft, is disclosed in which the aerodynamic gradient γa is governed by reference to a desired gradient γd which is the total gradient γt modulated by the difference between the aircraft speed V and a reference speed V 2 . An error signal δ representative of the difference between the aerodynamic gradient γa and the desired gradient γd is displayed. The display of the desired gradient γd may be by means of the pitching tendency bar of an artificial horizon for example.
Inventors
- 👤 Jean-Luc Sicre
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 22:08
CPC Classifications
G; G06; G06G; G06G7/00; G06G7/48; G06G7/78; G05; G05D; G05D1/00; G05D1/04; G05D1/06; G05D1/0607
Claims Analysis
Total Claims: 24
Claim 1
Independent Claim
72 words
A flying method using total power, for an aircraft, and comprising the following steps, governing the aerodynamic gradient γa by reference to a desired gradient γd, obtaining the desired gradient γd by modulating the total gradient γt by the difference between the aircraft speed V and a reference speed V 2 , and displaying an error signal δ representative of the difference between the aerodynamic gradient γa and the desired gradient γd.
Claim 2
Dependent Claim
72 words
A flying method using total power, for an aircraft, and comprising the following steps, governing the aerodynamic gradient γa by reference to a desired gradient γd, obtaining the desired gradient γd by modulating the total gradient γt by the difference between the aircraft speed V and a reference speed V 2 , and displaying an error signal δ representative of the difference between the aerodynamic gradient γa and the desired gradient γd.
Claim 3
Dependent Claim
29 words
A flying method according to claim 1, wherein said step of displaying includes displaying said error signal δ by means of the pitching tendency bar of an artificial horizon.
Claim 4
Dependent Claim
19 words
A flying method according to claim 1, and further including calculating the total gradient γt from an accelerometric box.
Claim 5
Dependent Claim
40 words
A flying method according to claim 1, and further including calculating the total gradient γt from the speed Vs of the aircraft with respect to the ground, and providing the value of this speed Vs by a central inertial unit.
Claim 6
Dependent Claim
27 words
A flying method according to claim 4, and further including calculating γt from the formula: ##EQU5## (g being the acceleration due to gravity), or the formula: ##EQU6##
Claim 7
Dependent Claim
43 words
A flying method according to claim 5 and further including governing the derivative dVs/dt by a magnitude proportional to the difference (V - V 2 ) in which V is the aerodynamic speed of the aircraft and V 2 is the reference speed.
Claim 8
Dependent Claim
115 words
A flying method according to claim 1, and further including taking into account either the variation δ, intended to subject the speed V to the control of the reference value, or a variation of the stable position with respect to a reference position, and including transmitting the error signal δ to a comparator, comparing δ in the comparator with a signal δ 1 corresponding to said variation of position and with a constant reference signal δ 2 and controlling the longitudinal tendency bar of the artificial horizon by the intermediate signal of the group (δ, δ 1 , δ 2 ) i.e. the signal whose instantaneous value is between those of the other two signals.
Claim 9
Dependent Claim
28 words
A flying method according to claim 7, and utilizing a reference position which corresponds to θ 1 = 18° and a constant reference signal which corresponds to 20°.
Claim 10
Dependent Claim
45 words
A flying method according to claim 1, and utilizing a reference speed of at least two values, (V 2 + 10 knots) or V 2 , these two values being interchangeable according to whether the total gradient γt is above or below a calibrated value.
Claim 11
Dependent Claim
14 words
A flying method according to claim 9, and utilizing a calibrated value of 6°.
Claim 12
Dependent Claim
19 words
A flying method according to claim 1, and including limiting the speed difference signal between positive and negative values.
Claim 13
Independent Claim
183 words
A system for applying a flying method using total power, for an aircraft, and comprising the steps of governing the aerodynamic gradient δa by reference to a desired gradient δd, obtaining the desired gradient δd by modulating the total gradient δt by the difference between the aircraft speed B and a reference speed V 2 , and displaying an error signal δ representative of the difference between the aerodynamic gradient δa and the desired gradient δd, and wherein a signal representative of the total gradient δt is transmitted to a first input of an adder which receives at a second input a signal corresponding to the difference between the speed V and a reference speed, the adder output being connected to a first input of a subtractor which receives at a second input, a signal corresponding to the aerodynamic graident δa, the subtractor output being transmitted to a comparator which is connected to a member for controlling the pitching tendency bar of the artificial horizon, and the comparator also receiving a signal representative of a variation of stable position and a reference signal.
Claim 14
Independent Claim
183 words
A system for applying a flying method using total power, for an aircraft, and comprising the steps of governing the aerodynamic gradient δa by reference to a desired gradient δd, obtaining the desired gradient δd by modulating the total gradient δt by the difference between the aircraft speed B and a reference speed V 2 , and displaying an error signal δ representative of the difference between the aerodynamic gradient δa and the desired gradient δd, and wherein a signal representative of the total gradient δt is transmitted to a first input of an adder which receives at a second input a signal corresponding to the difference between the speed V and a reference speed, the adder output being connected to a first input of a subtractor which receives at a second input, a signal corresponding to the aerodynamic graident δa, the subtractor output being transmitted to a comparator which is connected to a member for controlling the pitching tendency bar of the artificial horizon, and the comparator also receiving a signal representative of a variation of stable position and a reference signal.
Claim 15
Dependent Claim
77 words
A system according to claim 12, wherein the signal representative of the aerodynamic gradient is provided by a circuit which forms the difference between the stable position θ 1 and the incidence α, this circuit being able to comprise a commutation device controlled by a signal representing the state of the under-carriage, in order to substitute the stable position θ 1 for the incidence α when said under-carriage is collapsed, in order to cancel out said difference.
Claim 16
Dependent Claim
100 words
A system according to one of claim 12, wherein the signal corresponding to the variation between the speed V and the reference speed comprises a subtractor which subtracts from the speed V, provided by an anemometer, a reference speed V 2 , the subtractor being connected to a first input of a second subtractor, having a second input connected to a source of reference voltage by means of a commutator controlled by a level detector of total gradient γt, the second comparator being connected to a non-linear member which serves as a limiter and which provides said speed variation signal.
Claim 17
Dependent Claim
65 words
A system according to claim 12, wherein the level detection circuit which operates from the signal γt is composed of a low pass filter connected to an adder by a direct connection and by a derivation circuit comprising a differentiation and filtering member followed by a diode, the output of the adder being connected to a level detector which ensures the control of said commutator.
Claim 18
Dependent Claim
17 words
A system according to claim 15, wherein the level detector is adapted to control the non-linear member.
Claim 19
Dependent Claim
29 words
A system according to claim 12, wherein the comparator is connected to a member for controlling the pitching tendency bar of the artificial horizon by means of a limiter.
Claim 20
Dependent Claim
80 words
A system according to claim 12, wherein, in order to ensure protection against abnormal negative gradients of the aircraft, due in particular to poor operation of the flying system circuit providing the signal δ, the input of the comparator corresponding to the signal δ 2 is connected to a circuit providing a signal K (γa -γo), in which K is an adjustment gain and γo is a value representative of a minimum safety gradient, below which one should not drop.
Claim 21
Dependent Claim
54 words
A system according to claim 12, comprising a detection device serving to detect at the output of the comparator the presence of the signal δ 2 when the latter is selected, and to disconnect the entire flying system when the signal δ 2 remains selected at the end of a predetermined period of time.
Claim 22
Dependent Claim
55 words
A system according to claim 12, wherein the input δ 2 of the comparator is connected to an amplifier for an adjustment gain K, which receives the differential signal of a subtractor, which in turn receives a signal representative of the aerodynamic gradient γa and, a signal γo representative of a gradient of predetermined value.
Claim 23
Dependent Claim
13 words
A system according to claim 20, wherein the predetermined gradient value is 0.5°.
Claim 24
Dependent Claim
74 words
A system according to claim 20, wherein the amplifier for the gain K is connected to a subtractor which also receives the output signal of the comparator, and the differential signal provided by said subtractor is transmitted to a logic unit which acts on the flight control horizon in order to cause the pitching tendency bar to disappear when said differential signal remains zero for a period of time greater, than a predetermined period.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1981-01-30 | 1981-08-01 | 1982-01-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-01-30 | 1985-08-01 | 1986-01-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-01-30 | 1989-08-01 | 1990-01-31 | $7700.00 | Window Closed / Lapsed |