US3572612A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Programming and mixing unit for vtol aircraft
Assignee: 125769 CANADA Inc A CORP OF CANADA
•
Filing: 1968-07-15
•
Granted: 1971-03-30
•
Expires: 1988-07-15
Abstract
Abstract A control system for a tilt wing VTOL aircraft is described. In normal or horizontal flight at a wing tilt angle of zero, the conventional attitude control elements have control authority i.e. the pilots pitch, yaw and roll controls are transmitted respectively to the usual elevators, rudder, and ailerons. As wing tilt angle increases, however, roll control authority is gradually transferred to laterally spaced thrust producers positioned on the aircraft wings, while yaw control authority is gradually transferred to the ailerons. At the same time, pitch control authority is gradually transferred by the control system to the only auxiliary attitude control element required, namely a vertical thrust producer located adjacent the tail end of the aircraft. The transfers of control authority are effected by a mixing and programming unit which includes a plurality of mechanisms the gain of which vary in response to the angle to the angle of wing tilt, such mixing and programming unit having inputs connected to receive the pilots pitch yaw and roll control signals, and outputs connected to the above mentioned attitude control elements.
Inventors
- 👤 Karl Irbitis
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 08:58
CPC Classifications
B; B64; B64C; B64C29/00; B64C29/0008; B64C29/0016; B64C29/0033
Claims Analysis
Total Claims: 70
Claim 1
Independent Claim
806 words
In a VTOL aircraft of the tilt wing-type having a wing mounted on said aircraft and extending from opposite sides of the fuselage of the aircraft, means for tilting said wing between substantially horizontal and substantially vertical positions, laterally spaced thrust producers associated with said wing, control surfaces attached to said wing in positions to intercept gas streams induced by said laterally spaced thrust producers, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft, means responsive to a controlling input thereto to differentially vary the settings of said control surfaces, means responsive to controlling inputs thereto to differentially vary the thrusts of the laterally spaced thrust producers, means to vary the thrust of said rearwardly positioned thrust producer, pilot''s control means for producing pitch, roll and yaw control signals, means connecting the pilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a control unit comprising in combination: a. pitch, roll and yaw programming assemblies each having one input connected to receive pilot''s pitch, roll and yaw control signals respectively from said pilot''s control means; b. a further controlling input means operatively associated with each of said pitch, roll, and yaw programming assemblies; c. means connecting said further controlling input means for actuation in accordance with the tilting motion of the wing, d. said pitch programming assembly having an output connected to said means for varying the thrust of said rearwardly positioned thrust producer, the pitch programming assembly being constructed and arranged to respond to the further controlling input means by providing for transmission of pilot''s pitch control signals between its input for pilot''s pitch control signals and its output when said wing is tilted to a substantially vertical position, and further being arranged to progressively decrease the amounts of pilot''s pitch control signals transmitted from its input to its output as said wing is tilted back to a horizontal position; e. said yaw and roll programming assemblies each having first and second output means, the first output means of each of said jaw and roll assemblies being connected to the means to differentially vary the thrusts of the laterally spaced thrust producers, and the second output means of each of said yaw and roll assemblies being connected to the means to dIfferentially vary the settings of the control surface means, f. said yaw programming assembly being arranged to transmit pilot''s yaw control signals between its input for yaw control signals and its first output means to provide for a controlling input to the means to differentially vary the thrusts of the laterally spaced thrust producers when said wing is tilted to a position intermediate the vertical and horizontal positions, said yaw programming assembly further being arranged to respond to the further controlling input by transmitting pilot''s yaw control signals between its input for yaw control signals and its second output means to provide for a controlling input to the means to differentially vary the settings of the control surfaces when said wing is tilted to a vertical position and to gradually decrease the amount of pilot''s yaw control signals transmitted to said second output as the wing is tilted back to horizontal position; and g. said roll programming assembly including means arranged to respond to said further controlling input by providing for transmission of pilot''s roll control signals between its input for roll control and the first output means thereof to provide for a controlling input to the means for differentially varying thrusts of the laterally spaced thrust producers when said wing is tilted to a substantially vertical position, said roll programming assembly also including means to gradually decrease the amounts of pilot''s roll control signals transmitted between its input and its first output means and to gradually increase the amounts of pilot''s roll control signals transmitted between its input for roll control signals and its second output to provide for a controlling input to the means to differentially vary the settings of the control surfaces when the wing is tilted back to horizontal position; and h. at least one of said pitch, yaw and roll programming assemblies including a variable gain mechanism comprising; a programming cam connected to said further controlling input means so that it is moved to positions in accordance with the angle of tilt of said wing and a linkage mechanism associated with said programming cam and connected between the programming assembly''s input for pilot''s control signals and its associated output with said linkage mechanism arranged such that movement of said programming cam in response to tilting motion of said wing alters the configuration of the linkage mechanism in such a way as to vary in predetermined manner said amounts of pilot''s control signals transmitted from the input of such programming assembly to its output.
Claim 2
Dependent Claim
806 words
In a VTOL aircraft of the tilt wing-type having a wing mounted on said aircraft and extending from opposite sides of the fuselage of the aircraft, means for tilting said wing between substantially horizontal and substantially vertical positions, laterally spaced thrust producers associated with said wing, control surfaces attached to said wing in positions to intercept gas streams induced by said laterally spaced thrust producers, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft, means responsive to a controlling input thereto to differentially vary the settings of said control surfaces, means responsive to controlling inputs thereto to differentially vary the thrusts of the laterally spaced thrust producers, means to vary the thrust of said rearwardly positioned thrust producer, pilot''s control means for producing pitch, roll and yaw control signals, means connecting the pilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a control unit comprising in combination: a. pitch, roll and yaw programming assemblies each having one input connected to receive pilot''s pitch, roll and yaw control signals respectively from said pilot''s control means; b. a further controlling input means operatively associated with each of said pitch, roll, and yaw programming assemblies; c. means connecting said further controlling input means for actuation in accordance with the tilting motion of the wing, d. said pitch programming assembly having an output connected to said means for varying the thrust of said rearwardly positioned thrust producer, the pitch programming assembly being constructed and arranged to respond to the further controlling input means by providing for transmission of pilot''s pitch control signals between its input for pilot''s pitch control signals and its output when said wing is tilted to a substantially vertical position, and further being arranged to progressively decrease the amounts of pilot''s pitch control signals transmitted from its input to its output as said wing is tilted back to a horizontal position; e. said yaw and roll programming assemblies each having first and second output means, the first output means of each of said jaw and roll assemblies being connected to the means to differentially vary the thrusts of the laterally spaced thrust producers, and the second output means of each of said yaw and roll assemblies being connected to the means to dIfferentially vary the settings of the control surface means, f. said yaw programming assembly being arranged to transmit pilot''s yaw control signals between its input for yaw control signals and its first output means to provide for a controlling input to the means to differentially vary the thrusts of the laterally spaced thrust producers when said wing is tilted to a position intermediate the vertical and horizontal positions, said yaw programming assembly further being arranged to respond to the further controlling input by transmitting pilot''s yaw control signals between its input for yaw control signals and its second output means to provide for a controlling input to the means to differentially vary the settings of the control surfaces when said wing is tilted to a vertical position and to gradually decrease the amount of pilot''s yaw control signals transmitted to said second output as the wing is tilted back to horizontal position; and g. said roll programming assembly including means arranged to respond to said further controlling input by providing for transmission of pilot''s roll control signals between its input for roll control and the first output means thereof to provide for a controlling input to the means for differentially varying thrusts of the laterally spaced thrust producers when said wing is tilted to a substantially vertical position, said roll programming assembly also including means to gradually decrease the amounts of pilot''s roll control signals transmitted between its input and its first output means and to gradually increase the amounts of pilot''s roll control signals transmitted between its input for roll control signals and its second output to provide for a controlling input to the means to differentially vary the settings of the control surfaces when the wing is tilted back to horizontal position; and h. at least one of said pitch, yaw and roll programming assemblies including a variable gain mechanism comprising; a programming cam connected to said further controlling input means so that it is moved to positions in accordance with the angle of tilt of said wing and a linkage mechanism associated with said programming cam and connected between the programming assembly''s input for pilot''s control signals and its associated output with said linkage mechanism arranged such that movement of said programming cam in response to tilting motion of said wing alters the configuration of the linkage mechanism in such a way as to vary in predetermined manner said amounts of pilot''s control signals transmitted from the input of such programming assembly to its output.
Claim 3
Dependent Claim
107 words
Apparatus according to claim 1 further including means providing a collective control surfaces deflection output setting as a function of wing tilt angle, and means summing said collective control surfaces output deflection with the differential deflection output setting provided by said means for differentially varying the control surfaces settings thereby to obtain a net control surfaces setting, means providing a collective thrusts setting for the laterally spaced thrust producers, and means summing said collective thrusts setting with the differential thrusts setting provided by the means for differentially varying the thrusts of the laterally spaced thrust producers to provide a net output setting for each of the latter.
Claim 4
Dependent Claim
96 words
The VTOL aircraft according to claim 1 wherein said pitch programming assembly includes one such variable gain mechanism and said yaw and roll programming assemblies each include two such variable gain mechanisms, the linkage mechanism of each variable gain mechanism being connected between the input for pilot''s control signals and a respective output of the programming assembly with which it is associated, with each programming cam being contoured to effect the changes in the amounts of pilot''s control signals transmitted between the input and the output of the variable gain mechanism with which it is associated.
Claim 5
Dependent Claim
46 words
The VTOL aircraft according to claim 3 wherein said further controlling input means includes shaft means arranged for rotation to angular positions in accordance with the angle of tilt of said wing, the programming cams being connected to and arranged for rotation with said shaft means.
Claim 6
Dependent Claim
783 words
In a VTOL aircraft of the tilt wing-type, having a wing mounted on said aircraft and extending from opposite sides of the fuselage of the aircraft, means for tilting said wing between substantially horizontal and substantially vertical positions, laterally spaced thrust producers associated with said wing, control surfaces attached to said wing in positions to intercept gas streams induced by said laterally spaced thrust producers, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft, means responsive to a controlling input thereto to differentially vary the settings of said control surfaces, means responsive to controlling inputs thereto to differentially vary the thrusts of the laterally spaced thrust producers, means to vary the thrust of said rearwardly positioned thrust producer, pilot''s control means for producing pitch, roll and yaw control signals, means connecting thepilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a control unit comprising in combination: a. pitch, roll and yaw programming assemblies each having one input connected to receive pilot''s pitch, roll and yaw control signals respectively from said pilot''s control means; b. a further controlling input means operatively associated with each of said pitch, roll and yaw programming assemblies; c. means connecting said further controlling input means for actuation in accordance with the tilting motion of the wing, d. said pitch programming assembly having an output connected to said means for varying the thrust of said rearwardly positioned thrust producer, the pitch programming assembly being constructed and arranged to respond to the further controlling input means by providing for transmission of pilot''s pitch control signals between its input for pilot''s pitch control signals and its output when said wing is tilted to a substantially vertical position, and further being arranged to progressively decrease the amounts of pilot''s pitch control signals transmitted from it input to its output as said wing is tilted back to a horizontal position; e. said yaw and roll programming assemblies each having first and second output means, the first output means of each of said yaw and roll assemblies being connected to the means to differentially vary the thrusts of the laterally spaced thrust producers, and the second output means of each of said yaw and roll assemblies being connected to the means to differentially vary the settings of the surface means; f. said yaw programming assembly being arranged to transmit pilot''s yaw control signals between its input for yaw control signals and its first output means to provide for a controlling input to the means to differentially vary the thrusts of the laterally spaced thrust producers when said wing is tilted to a position intermediate the vertical and horizontal positions, said yaw programming assembly further being arranged to respond to the further controlling input by transmitting pilot''s yaw control signals between its input for yaw control signals and its second output means to provide for a controlling input to the means to differentially vary the settings of the control surfaces when said wing is tilted to a vertical position and to gradually decrease the amount of pilot''s yaw control signals transmitted to said second output as the wing is tilted back to horizontal position; g. said roll programming assembly including means arranged to respond to said further controlling input by providing for transmission of pilot''s roll control signals between its input for roll control and the first Output means thereof to provide for a controlling input to the means for differentially varying thrusts of the laterally spaced thrust producers when said wing is tilted to a substantially vertical position, said roll programming assembly also including means to gradually decrease the amounts of pilot''s roll control signals transmitted between its input and its first output means and to gradually increase the amounts of pilot''s roll control signals transmitted between its input for roll control signals and its second output to provide for a controlling input to the means to differentially vary the settings of the control surfaces when the wing is tilted back to horizontal position; and h. wherein said pitch programming assembly comprises a variable gain mechanism including a programming cam connected to said further controlling input means and being moved in accordance with the angle of tilt of said wing, and link and lever means associated with said programming cam connected between the pitch control input of the pitch programming assembly and the output thereof and constructed and arranged such that movement of the programming cam alters the configuration of said link and lever means thereby to vary in a predetermined manner the amount of pitch control movement transmitted therethrough to the output of the pitch programming assembly.
Claim 7
Dependent Claim
783 words
In a VTOL aircraft of the tilt wing-type, having a wing mounted on said aircraft and extending from opposite sides of the fuselage of the aircraft, means for tilting said wing between substantially horizontal and substantially vertical positions, laterally spaced thrust producers associated with said wing, control surfaces attached to said wing in positions to intercept gas streams induced by said laterally spaced thrust producers, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft, means responsive to a controlling input thereto to differentially vary the settings of said control surfaces, means responsive to controlling inputs thereto to differentially vary the thrusts of the laterally spaced thrust producers, means to vary the thrust of said rearwardly positioned thrust producer, pilot''s control means for producing pitch, roll and yaw control signals, means connecting thepilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a control unit comprising in combination: a. pitch, roll and yaw programming assemblies each having one input connected to receive pilot''s pitch, roll and yaw control signals respectively from said pilot''s control means; b. a further controlling input means operatively associated with each of said pitch, roll and yaw programming assemblies; c. means connecting said further controlling input means for actuation in accordance with the tilting motion of the wing, d. said pitch programming assembly having an output connected to said means for varying the thrust of said rearwardly positioned thrust producer, the pitch programming assembly being constructed and arranged to respond to the further controlling input means by providing for transmission of pilot''s pitch control signals between its input for pilot''s pitch control signals and its output when said wing is tilted to a substantially vertical position, and further being arranged to progressively decrease the amounts of pilot''s pitch control signals transmitted from it input to its output as said wing is tilted back to a horizontal position; e. said yaw and roll programming assemblies each having first and second output means, the first output means of each of said yaw and roll assemblies being connected to the means to differentially vary the thrusts of the laterally spaced thrust producers, and the second output means of each of said yaw and roll assemblies being connected to the means to differentially vary the settings of the surface means; f. said yaw programming assembly being arranged to transmit pilot''s yaw control signals between its input for yaw control signals and its first output means to provide for a controlling input to the means to differentially vary the thrusts of the laterally spaced thrust producers when said wing is tilted to a position intermediate the vertical and horizontal positions, said yaw programming assembly further being arranged to respond to the further controlling input by transmitting pilot''s yaw control signals between its input for yaw control signals and its second output means to provide for a controlling input to the means to differentially vary the settings of the control surfaces when said wing is tilted to a vertical position and to gradually decrease the amount of pilot''s yaw control signals transmitted to said second output as the wing is tilted back to horizontal position; g. said roll programming assembly including means arranged to respond to said further controlling input by providing for transmission of pilot''s roll control signals between its input for roll control and the first Output means thereof to provide for a controlling input to the means for differentially varying thrusts of the laterally spaced thrust producers when said wing is tilted to a substantially vertical position, said roll programming assembly also including means to gradually decrease the amounts of pilot''s roll control signals transmitted between its input and its first output means and to gradually increase the amounts of pilot''s roll control signals transmitted between its input for roll control signals and its second output to provide for a controlling input to the means to differentially vary the settings of the control surfaces when the wing is tilted back to horizontal position; and h. wherein said pitch programming assembly comprises a variable gain mechanism including a programming cam connected to said further controlling input means and being moved in accordance with the angle of tilt of said wing, and link and lever means associated with said programming cam connected between the pitch control input of the pitch programming assembly and the output thereof and constructed and arranged such that movement of the programming cam alters the configuration of said link and lever means thereby to vary in a predetermined manner the amount of pitch control movement transmitted therethrough to the output of the pitch programming assembly.
Claim 8
Dependent Claim
53 words
In a VTOL aircraft according to claim 5 wherein said programming cam is designed to provide predetermined minimum output settings at every angle of wing tilt greater than zero thereby to induce in said rearwardly positioned thrust producer at every angle of wing tilt greater than zero at least a minimum lifting thrust.
Claim 9
Dependent Claim
193 words
The VTOL aircraft according to claim 5 wherein the yaw programming assembly comprises first, and second variable gain mechanisms, the first and second variable gain mechanisms assigned to yaw control including first and second programming cams connected to said further controlling input means thereby to be moved in accordance with said wing tilt motion, and first and second sets of lever and linkage means respectively associated with said first and second programming cams and connected between the yaw controlling input and the respective first and second outputs of the yaw programming assembly, said first programming cam and the set of lever and linkage means associated therewith being constructed and arranged that, with increasing wing tilt, the gain of the first variable gain mechanism first increases to a maximum, and thereafter gradually decreases to a zero value as the aircraft wing it tilted from a horizontal to a vertical position, said second programming cam and the lever and linkage means associated therewith being constructed and arranged such that as the wing is tilted from a horizontal to a vertical position, the gain of the second variable gain mechanism increases to a predetermined maximum value.
Claim 10
Dependent Claim
195 words
The VTOL aircraft according to claim 7 wherein the roll programming assembly comprises third and fourth variable gain mechanisms, the third and fourth variable gain mechanisms including third and fourth programming cams connected to said further controlling input means and hence being moved in accordance with said wing tilt motion, and third and fourth sets of lever and linkage means associated with said third and fourth programming cams and connected between the input thereto for roll control signals and the respective first and second outputs of the roll programming assembly, said third programming cam and the set of lever and linkage means associated therewith being constructed and arranged such that with increasing wing tilt the gain of the third variable gain mechanism increases from zero to a maximum value as the wing is tilted from a horizontal to a vertical position, said fourth programming cam and the lever and linkage means associated therewith being constructed and arranged such that as the wing is tilted from a horizontal to a vertical position, the gain of the fourth variable gain mecHanism increases from a predetermined value greater than zero to a maximum and thereafter decreases to zero.
Claim 11
Dependent Claim
78 words
The VTOL aircraft according to claim 8 wherein the further controlling input and the first, second, third and fourth programming cams of said yaw and roll programming assemblies are mounted upon a common shaft with the latter being rotated as a predetermined function of the angle of wing tilt, each of said programming cams being mounted on said shaft for ready removal and replacement thereby permitting the programming of said yaw and roll programming assemblies to be varied.
Claim 12
Dependent Claim
132 words
A mixing and programming unit according to claim 9 wherein said input for pilto''s yaw control signals includes a yaw input lever which is pivoted about an axis parallel to said common shaft intermediate said first and second programming cams, said input for pilot''s roll control signals includes a roll input lever which is pivoted about an axis parallel to said common shaft intermediate said third and fourth programming cams, each of said first, second, third, and fourth sets of lever and linkage means comprises interconnected variable gain levers, all the variable gain levers being pivotally connected about axes parallel to said common shaft with said first and second sets on opposite sides of the yaw input lever and the third and fourth sets on opposite sides of said roll input lever.
Claim 13
Dependent Claim
150 words
The invention set forth in claim 1 wherein said further controlling input means comprises at least one wing tilt input member mounted for rotation to angular positions determined by the tilt angle of said wing, said pitch, roll, and yaw programming assemblies each having at least one such variable gain mechanism with the respective programming cams thereof being of predetermined configurations and being adapted to vary the gain of their associated variable gain mechanisms in predetermined fashion as a function of wing tilt angle to effect said changes in the amount of pilot''s control signal transmitted between the input and the corresponding outputs of the programming assemblies, said variable gain mechanisms including their associated programming cams being serially disposed along said wing tilt input member with said programming cams being attached to the latter to assume angular positions corresponding to the angular positions assumed by said wing tilt input member.
Claim 14
Dependent Claim
42 words
The invention according to claim 11 wherein said pitch roll, and yaw programming assemblies are disposed within a housing means, and wherein said wing tilt input member comprises an elongated shaft extending within and rotatably mounted with respect to said housing means.
Claim 15
Dependent Claim
62 words
The invention according to claim 8 wherein said aircraft further includes a horizontal stabilizer pivotally attached to the rearward portion thereof, a further programming assembly operatively associated with said wing tilt input member and output means for said further programming assembly operatively connected to said stabilizer to effect changes in the angle of incidence thereof in response to tilting of said wings.
Claim 16
Dependent Claim
46 words
The invention according to claim 13 wherein said further programming assembly is arranged to gradually increase the angle of incidence of said stabilizer to a maximum and to thereafter reduce said angle of incidence as said wing is tilted from a horizontal to a vertical position.
Claim 17
Dependent Claim
86 words
The invention according to claim 8 wherein the aircraft further includes means producing pitch, roll, and yaw stabilizing inputs, summing means to combine the pilot''s yaw control signal to the yaw stability input to produce a net trimmed yaw input signal, summing means to combine the pilot''s roll control signal with the roll stability input to produce a net trimmed roll input signal, and summing means to combine the pilot''s pitch control signal to the pitch stability input to produce a net trimmed pitch input signal.
Claim 18
Dependent Claim
213 words
The VTOL aircraft according to claim 11 wherein the yaw programming assembly comprises a first and a second One of said variable gain mechanisms, the first and second variable gain mechanisms assigned to yaw control including respective first and second ones of said programming cams connected for rotation with said further controlling input means thereby to be moved in accordance with said wing tilt motion, the linkage mechanism of the variable gain mechanisms comprising first and second sets of lever and linkage means respectively associated with said first and second programming cams and connected between the yaw controlling input and the respective first and second outputs of the yaw programming assembly, said first programming cam and the set of lever and linkage means associated therewith being constructed and arranged such that with increasing wing tilt, the gain of the first variable gain mechanism first increases to a maximum, and thereafter gradually decreases to a zero value as the aircraft wing is tilted from a horizontal to a vertical position, said second programming cam and the lever and linkage means associated therewith being constructed and arranged such that as the wing is tilted from a horizontal to a vertical position, the gain of the second variable gain mechanism increases to a predetermined maximum value.
Claim 19
Dependent Claim
214 words
The VTOL aircraft according to claim 16 wherein the roll programming assembly comprises a third and a fourth one of said variable gain mechanisms, the third and fourth variable gain mechanisms including respective third and fourth ones of said programming cams connected for rotation with said further controlling input means and hence being moved in accordance with said wing tilt motion, the linkage mechanism of the variable gain mechanisms comprising third and fourth sets of lever and linkage means associated with said third and fourth programming camps and connected between the input thereto for roll control signals and the respective first and second outputs of the roll programming assembly said third programming cam and the set of lever and linkage means associated therewith being constructed and arranged such that with increasing wing tilt the gain of the third variable gain mechanism increases from zero to a maximum value as the wing is tilted from a horizontal to a vertical position, said fourth programming can and the lever and linkage means associated therewith being constructed and arranged such that as the wing is tilted from a horizontal to a vertical position, the gain of the fourth variable gain mechanism increases from a predetermined value greater than zero to a maximum and thereafter decreases to zero.
Claim 20
Dependent Claim
116 words
The invention defined in claim 11 further including a first summing means connected to said first outputs of the yaw and roll programming assemblies to sum the first outputs of the latter, and means connecting the summed first outputs of the latter to said means to differentially vary the thrusts of the laterally spaced thrust producers, a second summing means connected to said second outputs of the yaw and roll programming assemblies to sum the second outputs of the latter, and means connecting the second summing means to the means to differentially vary the settings of the control surfaces thereby rendering the latter responsive to the summed second outputs of said yaw and roll programming assemblies.
Claim 21
Dependent Claim
112 words
The invention according to claim 18 wherein said pitch programming assembly comprises a single variable gain mechanism connected between the pitch control input of the pitch programming assembly and its output and constructed and arranged such that movement of the programming cam alters the configuration of the linkage mechanism associated therewith to vary in a predetermined manner the amount of pitch control movement transmitted therethrough to said output, said programming cam being designed to provide predetermined minimum output settings at every angle of wing tilt greater than zero thereby to induce in said rearwardly positioned thrust producer at every angle of wing tilt greater than zero at least a minimum lifting thrust.
Claim 22
Dependent Claim
19 words
The invention according to claim 11 wherein said programming cams are removably mounted on said wing tilt input member.
Claim 23
Dependent Claim
107 words
Apparatus according to claim 11 further including means providing a collective control surface deflection output setting as a function of wing tilt angle, and means summing said collective control surface output deflection with the differential deflection output setting provided by said means for differentially varying the control surfaces settings thereby to obtain a net control surface setting, means providing a collective thrust setting for the laterally spaced thrust producers, and means summing said collective thrust setting with the differential thrust setting provided by the means for differentially varying the thrusts of the laterally spaced thrust producers to provide a net output setting for each of the latter.
Claim 24
Dependent Claim
20 words
The VTOL aircraft according to claim 1 wherein said laterally spaced thrust producers comprise motor driven variable blade pitch propellers.
Claim 25
Dependent Claim
18 words
The VTOL aircraft according to claim 22 wherein the rearwardly positioned thrust producer comprises a variable pitch propeller.
Claim 26
Dependent Claim
443 words
A mixing and programming unit for an aircraft having tiltable laterally spaced thrust producers, said unit being adapted to provide pitch, yaw and roll control outputs in response to the pilot''s pitch, yaw and roll inputs thereto comprising: a. a pitch programming assembly having an input for pilot''s pitch control signals and a pitch controlling output means; b. a roll programming assembly having an input for pilot''s roll control signals and a roll controlling output means; c. a yaw programming assembly having an input for pilot''s yaw control signals and a yaw controlling output means; d. a further input means comprising elongated shaft means operatively connected to each of said pitch, roll, and yaw programming assemblies, said shaft means being rotatably mounted and adapted to be connected for rotation to angular positions determined by the angle of tilt of said laterally spaced thrust producers; e. each of said pitch, roll, and yaw programming assemblies comprising variable gain mechanism interconnected between their respective inputs and their output means, each such variable gain mechanism being responsive to rotation of said input shaft means whereby the gain of each variable gain mechanism is a predetermined function of the angle of tilt; f. said pitch programming assembly comprising one variable gain mechanism arranged such that the gain thereof increases from zero to a maximum value as said input shaft is rotated in response to a tilt angle increase from zero to a maximum value; g. said yaw programming assembly comprising a first and a second variable gain mechanism; i. the first variable gain mechanism being arranged such that its gain first increases and thereafter decreases as said input shaft is rotated in response to a tilt angle increase from zero to a maximum, and ii. the second variable gain mechanism being arranged such that its gain increases to a maximum as said input shaft is rotated in response to a tilt angle increase; h. said roll programming assembly comprising a third and a fourth variable gain mechanism; and i. the third variable gain mechanism being arranged such that the gain thereof increases from zero as said input shaft is rotated in response to a tilt angle increase from zero, and ii. the fourth variable gain mechanism being arranged such that its gain first increases from a predetermined value greater than zero to a maximum and then decreases to zero as said input shaft is rotated in response to a tilt angle increase from zero to a maximum; i. the output means for the yaw and roll programming assemblies comprising first, second, third and fourth outputs respectively connected to said first, second, third and fourth variable gain mechanisms.
Claim 27
Dependent Claim
443 words
A mixing and programming unit for an aircraft having tiltable laterally spaced thrust producers, said unit being adapted to provide pitch, yaw and roll control outputs in response to the pilot''s pitch, yaw and roll inputs thereto comprising: a. a pitch programming assembly having an input for pilot''s pitch control signals and a pitch controlling output means; b. a roll programming assembly having an input for pilot''s roll control signals and a roll controlling output means; c. a yaw programming assembly having an input for pilot''s yaw control signals and a yaw controlling output means; d. a further input means comprising elongated shaft means operatively connected to each of said pitch, roll, and yaw programming assemblies, said shaft means being rotatably mounted and adapted to be connected for rotation to angular positions determined by the angle of tilt of said laterally spaced thrust producers; e. each of said pitch, roll, and yaw programming assemblies comprising variable gain mechanism interconnected between their respective inputs and their output means, each such variable gain mechanism being responsive to rotation of said input shaft means whereby the gain of each variable gain mechanism is a predetermined function of the angle of tilt; f. said pitch programming assembly comprising one variable gain mechanism arranged such that the gain thereof increases from zero to a maximum value as said input shaft is rotated in response to a tilt angle increase from zero to a maximum value; g. said yaw programming assembly comprising a first and a second variable gain mechanism; i. the first variable gain mechanism being arranged such that its gain first increases and thereafter decreases as said input shaft is rotated in response to a tilt angle increase from zero to a maximum, and ii. the second variable gain mechanism being arranged such that its gain increases to a maximum as said input shaft is rotated in response to a tilt angle increase; h. said roll programming assembly comprising a third and a fourth variable gain mechanism; and i. the third variable gain mechanism being arranged such that the gain thereof increases from zero as said input shaft is rotated in response to a tilt angle increase from zero, and ii. the fourth variable gain mechanism being arranged such that its gain first increases from a predetermined value greater than zero to a maximum and then decreases to zero as said input shaft is rotated in response to a tilt angle increase from zero to a maximum; i. the output means for the yaw and roll programming assemblies comprising first, second, third and fourth outputs respectively connected to said first, second, third and fourth variable gain mechanisms.
Claim 28
Dependent Claim
21 words
The invention as defined in claim 24, wherein said variable gain mechanisms are seriaLly disposed along said elongated input shaft means.
Claim 29
Dependent Claim
66 words
The invention defined in claim 24 wherein each said variable gain mechanism comprises; a programming cam connected to said input shaft means for rotation therewith, and link and lever means operatively connected to said programming cam and interconnected between its input and output means and adapted to assume varied configurations in response to rotation of said programming cam to effect said increases and decreases in gain.
Claim 30
Dependent Claim
21 words
The invention defined in claim 26 wherein at least the yaw and roll programming assemblies are mounted within a common housing.
Claim 31
Dependent Claim
39 words
The invention defined in claim 24 further comprising means for summing together the outputs of the first and the third variable gain mechanisms, and further means for summing together the outputs of the second and fourth variable gain mechanism.
Claim 32
Dependent Claim
83 words
The invention according to claim 28 further comprising means providing pitch, roll and yaw stability inputs, summing means to combine the pilot''s yaw control signal to the yaw stability input to produce a net trimmed yaw input signal, summing means to combine the pilot''s roll control signal with the roll stability input to produce a net trimmed roll input signal, and summing means to combine the pilot''s pitch control signal to the pitch stability input to produce a net trimmed pitch input signal.
Claim 33
Dependent Claim
200 words
The invention defined in claim 26 wherein the link and lever means of each of said yaw and roll variable gain mechanisms comprises; a pivoted cam follower lever having follower means contacting its associated programming cam, a first link connected adjacent one end to the output means of said mechanism and connected adjacent its opposite end for movement in an arcuate path together with said cam follower lever, said opposite end of said first link also being connected to one end of a second link, the second link being connected adjacent its opposite end to an end portion of an input lever, said input lever being pivotally connected to a fixed pivot, the latter being positioned such that one point on said arcuate path is aligned with the axis of the fixed pivot, said input lever also being operably connected to the input means for control signals and occupying angular positions determined thereby, whereby angular movement of said input lever in response to a control input to the variable gain mechanism effects movement of the output means of said mechanism except when said opposite end of said first link is in correspondence with said one point on said arcuate path.
Claim 34
Dependent Claim
42 words
The invention defined in claim 30 wherein a first one of said input levers is common to the first and second variable gain mechanisms, and a second one of said input levers is common to the third and fourth variable gain mechanisms.
Claim 35
Dependent Claim
70 words
The invention defined in claim 31 further including means providing a yaw stability input to said first and second variable gain mechanisms, a summing lever connected to sum said yaw stability input with the pilot''s input yaw control signal to yield a net trimmed yaw input signal, said summing lever connected to said first input lever thereby to provide said operable connection to the latter to apply control signals thereto.
Claim 36
Dependent Claim
72 words
The invention defined in claim 32 further including means providing a roll stability input to said third and fourth variable gain mechanisms, a further summing lever connected to sum said roll stability input with the pilot''s input roll control signal to yield a net trimmed roll input signal, said further summing lever connected to said second input lever thereby to provide said operable connection to the latter to apply control signals thereto.
Claim 37
Dependent Claim
452 words
In a VTOL aircraft of the tilt wing type, having a wing mounted on said aircraft and means to increase the angle of tilt of said wing from a substantially horizontal to a substantially vertical position, laterally spaced thrust producers associated with said wing each having thrust varying means responsive to cOntrol signals, control surfaces attached to said wing in positions to intercept gas streams induced by said laterally spaced thrust producers and including means to vary the control surface settings in response to control signals, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft and having a thrust varying means associated therewith, pilot''s control means for producing pitch, roll and yaw control signals, means connecting the pilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a control authority transfer unit comprising in combination: a. pitch authority transfer means including input means connected to receive pitch control signals from the pilot''s pitch control means, and output means connected to the thrust varying means of said rearwardly positioned thrust producer; b. yaw authority transfer means including input means connected to receive yaw control signals from the pilot''s yaw control means and having output means connected both to said means to vary the thrusts of the laterally spaced thrust producers and to the means to vary the settings of said control surfaces; c. roll authority transfer means including input means connected to receive roll control signals from the pilot''s roll control means and having output means connected both to the means to vary the thrusts of said laterally spaced thrust producers and to the means to vary the settings of said control surfaces; d. a further input means operatively associated with each of said pitch, yaw and roll authority transfer means, said further input means comprising shaft means connected and mounted such that said shaft means is rotated to various angular positions in accordance with the angle of wing tilt; e. said pitch authority transfer means being arranged to respond to actuation of the further input means by progressively transferring pitch control authority to said rearwardly positioned thrust producer as the angle of wing tilt increases; f. said yaw authority transfer means being arranged to respond to actuation of the further input means by progressively transferring yaw control authority to said control surfaces as the angle of wing tilt increases; and g. said roll authority transfer means being arranged to respond to actuation of the further input means by decreasing the roll control authority of said control surfaces while increasing the roll control authority of the laterally spaced thrust producers as the angle of wing tilt increases.
Claim 38
Dependent Claim
452 words
In a VTOL aircraft of the tilt wing type, having a wing mounted on said aircraft and means to increase the angle of tilt of said wing from a substantially horizontal to a substantially vertical position, laterally spaced thrust producers associated with said wing each having thrust varying means responsive to cOntrol signals, control surfaces attached to said wing in positions to intercept gas streams induced by said laterally spaced thrust producers and including means to vary the control surface settings in response to control signals, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft and having a thrust varying means associated therewith, pilot''s control means for producing pitch, roll and yaw control signals, means connecting the pilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a control authority transfer unit comprising in combination: a. pitch authority transfer means including input means connected to receive pitch control signals from the pilot''s pitch control means, and output means connected to the thrust varying means of said rearwardly positioned thrust producer; b. yaw authority transfer means including input means connected to receive yaw control signals from the pilot''s yaw control means and having output means connected both to said means to vary the thrusts of the laterally spaced thrust producers and to the means to vary the settings of said control surfaces; c. roll authority transfer means including input means connected to receive roll control signals from the pilot''s roll control means and having output means connected both to the means to vary the thrusts of said laterally spaced thrust producers and to the means to vary the settings of said control surfaces; d. a further input means operatively associated with each of said pitch, yaw and roll authority transfer means, said further input means comprising shaft means connected and mounted such that said shaft means is rotated to various angular positions in accordance with the angle of wing tilt; e. said pitch authority transfer means being arranged to respond to actuation of the further input means by progressively transferring pitch control authority to said rearwardly positioned thrust producer as the angle of wing tilt increases; f. said yaw authority transfer means being arranged to respond to actuation of the further input means by progressively transferring yaw control authority to said control surfaces as the angle of wing tilt increases; and g. said roll authority transfer means being arranged to respond to actuation of the further input means by decreasing the roll control authority of said control surfaces while increasing the roll control authority of the laterally spaced thrust producers as the angle of wing tilt increases.
Claim 39
Dependent Claim
25 words
The invention as defined in claim 34 wherein said pitch, yaw and roll authority transfer means are serially disposed along said elongated input shaft means.
Claim 40
Dependent Claim
66 words
The invention defined in claim 34 wherein each of said pitch, roll, and yaw authority transfer means comprises variable gain mechanisms interconnected between their respective inputs and their output means, each such variable gain mechanism being operatively connected to and responsive to rotation of said input shaft means whereby the gain of each variable gain mechanism is a predetermined function of the angle of wing tilt.
Claim 41
Dependent Claim
66 words
The invention defined in claim 36 wherein each said variable gain mechanism comprises; a programming cam connected to said input shaft means for rotation therewith, and link and lever means operatively connected to said programming cam and interconnected between its input and output means and adapted to assume varied configurations in response to rotation of said programming cam to effect said increases and decreases in gain.
Claim 42
Dependent Claim
22 words
The invention defined in claim 37 wherein at least the yaw and roll authority transfer means are mounted within a common housing.
Claim 43
Dependent Claim
43 words
The invention defined in claim 36 wherein said pitch authority transfer means comprises a fifth variable gain mechanism arranged such that the gain thereof increases from zero to a maximum value as the wing tilt angle increases from zero to a maxImum value.
Claim 44
Dependent Claim
200 words
The invention defined in claim 37 wherein the link and lever means of each of said yaw and roll variable gain mechanisms comprises; a pivoted cam follower lever having follower means contacting its associated programming cam, a first link connected adjacent one end to the output means of said mechanism and connected adjacent its opposite end for movement in an arcuate path together with said cam follower lever, said opposite end of said first link also being connected to one end of a second link, the second link being connected adjacent its opposite end to an end portion of an input lever, said input lever being pivotally connected to a fixed pivot, the latter being positioned such that one point on said arcuate path is aligned with the axis of the fixed pivot, said input lever also being operably connected to the input means for control signals and occupying angular positions determined thereby, whereby angular movement of said input lever in response to a control input to the variable gain mechanism effects movement of the output means of said mechanism except when said opposite end of said first link is in correspondence with said one point on said arcuate path.
Claim 45
Dependent Claim
42 words
The invention defined in claim 40 wherein a first one of said input levers is common to the first and second variable gain mechanisms, and a second one of said input levers is common to the third and fourth variable gain mechanisms.
Claim 46
Dependent Claim
70 words
The invention defined in claim 41 further including means providing a yaw stability input to said first and second variable gain mechanisms, a summing lever connected to sum said yaw stability input with the pilot''s input yaw control signal to yield a net trimmed yaw input signal, said summing lever connected to said first input lever thereby to provide said operable connection to the latter to apply control signals thereto.
Claim 47
Dependent Claim
72 words
The invention defined in claim 42 further including means providing a roll stability input to said third and fourth variable gain mechanisms, a further summing lever connected to sum said roll stability input with the pilot''s input roll control signal to yield a net trimmed roll input signal, said further summing lever connected to said second input lever thereby to provide said operable connection to the latter to apply control signals thereto.
Claim 48
Dependent Claim
83 words
The invention according to claim 34 further comprising means providing pitch, roll and yaw stability inputs, summing means to combine the pilot''s yaw control signal to the yaw stability input to produce a net trimmed yaw input signal, summing means to combine the pilot''s roll control signal with the roll stability input to produce a net trimmed roll input signal, and summing means to combine the pilot''s pitch control signal to the pitch stability input to produce a net trimmed pitch input signal.
Claim 49
Dependent Claim
37 words
The invention defined in claim 34 wherein said yaw authority transfer means is further arranged to increase and thereafter decrease the yaw control authority of the laterally spaced thrust producers as the angle of wing tilt increases.
Claim 50
Dependent Claim
52 words
The invention defined in claim 45 wherein said roll authority transfer means is further arranged to increase the roll control authority of said control surfaces from a value greater than zero to a maximum value prior to effecting said decrease of roll control authority therein as the angle of wing tilt increases.
Claim 51
Dependent Claim
69 words
The invention defined in claim 46 wherein said yaw authority transfer means comprises a first and a second variable gain mechanism: i. the first variable gain mechanism arranged such that its gain first increases and thereafter decreases as the wing tilt angle increases from zero to a maximum; and ii. the second variable gain mechanism arranged such that its gain increases to a maximum as wing tilt angle increases.
Claim 52
Dependent Claim
114 words
The invention defined in claim 47 wherein: said roll authority transfer means comprises a third and a fourth variable gain mechanism; i. the third variable gain mechanisM arranged such that the gain thereof increases from zero as the wing tilt angle increases from zero, and ii. the fourth variable gain mechanism arranged such that its gain first increases from a predetermined value greater than zero to a maximum and then decreases to zero as the wing tilt angle increases from zero to a maximum; the output means for the yaw and roll authority transfer means comprising first, second, third and fourth outputs respectively connected to said first, second, third and fourth variable gain mechanisms.
Claim 53
Dependent Claim
120 words
The invention defined in claim 48 further comprising first summing means for summing together the outputs of the first and the third variable gain mechanisms, and second summing means for summing together the outputs of the second and fourth variable gain mechanisms, the thrust varying means of the laterally spaced thrust producers including means for introducing a differential in the thrust settings thereof; the means varying the control surfaces settings including means introducing a differential in the settings thereof, means connecting the output of the first summing means to the means introducing a differential in the thrust settings, and means connecting the output of the second summing means to the means for introducing a differential in the control surfaces settings.
Claim 54
Dependent Claim
545 words
In a VTOL aircraft, having a wing mounted on said aircraft, laterally spaced thrust producers associated with said wing each having thrust varying means responsive to control signals, means to tilt said laterally spaced thrust producers between a substantially horizontal and a substantially vertical position to cause the aircraft to go from normal flight through transitional flight to hovering or vertical flight, an attitude control element capable of applying yaw forces to the aircraft in the transitional, hovering and vertical flight modes, means to vary the settings of said attitude control element in response to control signals fed thereto, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft and having a thrust varying means associated therewith, pilot''s control means for producing pitch, roll and yaw control signals, means connecting the pilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a programming unit comprising in combination: a. pitch programming means including input means connected to the pilot''s pitch control means, and output means connected to the thrust varying means of said rearwardly positioned thrust producer; b. yaw programming means including input means connected to the pilot''s yaw control means and having output means connected to said means to vary the thrusts of the laterally spaced thrust producers and to the means to vary the setting of said attitude control element; c. roll programming means including input means connected to the pilot''s roll control means and having output means connected to the means to vary the thrusts of said laterally spaced thrust producers; d. a further input means operatively associated with each of said pitch, yaw and roll programming means, said further input means being connected for actuation in accordance with the angle of tilt of said laterally spaced thrust producers; e. said pitch programming means being arranged to respond to actuation of the further input means by increasing the pitch control authority of said rearwardly positioned thrust producer as the angle of tilt increases; f. said yaw programming means being arranged to respond to actuation of the further input means by increasing the yaw control authority of said attitude control element as the angle of tilt increases while increasing and thereafter decreasing the yaw control authority of the laterally spaced thrust producers; g. said roll programming means being arranged to respond to actuation of the further input means by increasing the roll control authority of tHe laterally spaced thrust producers as the angle of tilt increases; and h. at least one of said pitch, yaw and roll programming means including a variable gain mechanism comprising; a programming cam connected to said further input means so that it is moved to positions in accordance with the angle of tilt of said wing, and a linkage mechanism associated with said programming cam and connected between the programming means input for pilot''s control signals and its associated output with said linkage mechanism arranged such that movement of said programming cam in response to tilting motion of said wing alters the configuration of the linkage mechanism in such a way as to vary in predetermined manner said amounts of pilot''s control signals transmitted from the input of such programming means to its output.
Claim 55
Dependent Claim
545 words
In a VTOL aircraft, having a wing mounted on said aircraft, laterally spaced thrust producers associated with said wing each having thrust varying means responsive to control signals, means to tilt said laterally spaced thrust producers between a substantially horizontal and a substantially vertical position to cause the aircraft to go from normal flight through transitional flight to hovering or vertical flight, an attitude control element capable of applying yaw forces to the aircraft in the transitional, hovering and vertical flight modes, means to vary the settings of said attitude control element in response to control signals fed thereto, elevators and a rudder associated with said aircraft, and a vertical thrust producer positioned rearwardly on said aircraft and having a thrust varying means associated therewith, pilot''s control means for producing pitch, roll and yaw control signals, means connecting the pilot''s control means to said rudder and said elevators to transmit yaw and pitch control signals respectively, a programming unit comprising in combination: a. pitch programming means including input means connected to the pilot''s pitch control means, and output means connected to the thrust varying means of said rearwardly positioned thrust producer; b. yaw programming means including input means connected to the pilot''s yaw control means and having output means connected to said means to vary the thrusts of the laterally spaced thrust producers and to the means to vary the setting of said attitude control element; c. roll programming means including input means connected to the pilot''s roll control means and having output means connected to the means to vary the thrusts of said laterally spaced thrust producers; d. a further input means operatively associated with each of said pitch, yaw and roll programming means, said further input means being connected for actuation in accordance with the angle of tilt of said laterally spaced thrust producers; e. said pitch programming means being arranged to respond to actuation of the further input means by increasing the pitch control authority of said rearwardly positioned thrust producer as the angle of tilt increases; f. said yaw programming means being arranged to respond to actuation of the further input means by increasing the yaw control authority of said attitude control element as the angle of tilt increases while increasing and thereafter decreasing the yaw control authority of the laterally spaced thrust producers; g. said roll programming means being arranged to respond to actuation of the further input means by increasing the roll control authority of tHe laterally spaced thrust producers as the angle of tilt increases; and h. at least one of said pitch, yaw and roll programming means including a variable gain mechanism comprising; a programming cam connected to said further input means so that it is moved to positions in accordance with the angle of tilt of said wing, and a linkage mechanism associated with said programming cam and connected between the programming means input for pilot''s control signals and its associated output with said linkage mechanism arranged such that movement of said programming cam in response to tilting motion of said wing alters the configuration of the linkage mechanism in such a way as to vary in predetermined manner said amounts of pilot''s control signals transmitted from the input of such programming means to its output.
Claim 56
Dependent Claim
40 words
The invention as defined in claim 50 wherein the input means is elongated and mounted for movement in relation to the angle of tilt, with said pitch, yaw and roll programming means being serially disposed along said elongated input means.
Claim 57
Dependent Claim
26 words
The invention defined in claim 50 wherein said elongated input means comprises shaft means mounted for rotation to angular positions determined by the angle of tilt.
Claim 58
Dependent Claim
23 words
The mixing programming unit according to claim 56 wherein said pitch, roll, and yaw programming assemblies are serially arranged along said shaft means.
Claim 59
Dependent Claim
66 words
The invention defined in claim 50 wherein each of said pitch, roll, and yaw programming means includes at least one of said variable gain mechanisms interconnected between its respective inputs and its output means, each said variable gain mechanism having its programming cam connected to said further input means whereby the gain of each variable gain mechanism is a predetermined function of the angle of tilt.
Claim 60
Dependent Claim
70 words
The invention defined in claim 51 wherein said yaw programming means comprises a first and a second one of said variable gain mechanisms: i. the first variable gain mechanism arranged such that its gain first increases and thereafter decreases as the tilt angle increases from zero to a maximum; and ii. the second variable gain mechanism arranged such that its gain increases to a maximum as the tilt angle increases.
Claim 61
Dependent Claim
69 words
The invention defined in claim 54 wherein: said roll programming means includes a third one of said variable gain mechanisms; i. the third variable gain mechanism arranged such that the gain thereof increases from zero as the tilt angle increases from zero; the output means and the yaw and roll programming means comprising first, second and third outputs respectively connected to said first, second and third variable gain mechanisms.
Claim 62
Dependent Claim
260 words
A mixing and programming unit for use with a VTOL aircraft having a plurality of attitude control elements including tiltable laterally spaced thrust producers, said unit being adapted to provide pitch, yaw and roll control outputs for the attitude control elements in response to pilot''s pitch, yaw and roll control signal inputs, said unit comprising pitch, roll, and yaw programming assemblies having respective pilot''s pitch, roll and yaw control signal input means and also having respective pitch roll and yaw controlling output means associated therewith, and a shaft means rotatably mounted on said unit and adapted to be connected such that the shaft occupies angular positions in accordance with the angle of tilt of the thrust producers, said shaft means being operatively connected to each of the pitch, roll and yaw programming assemblies to provide a further input thereto, each of the pitch, roll, and yaw programming assemblies including a variable gain mechanism connected between its input for pilot''s control signals and its output means with each variable gain mechanism being adapted to respond to the further input provided by the shaft means whereby the gain of each variable gain mechanism is a predetermined function of the angular position of said shaft, each variable gain mechanism including a programming cam connected to said input shaft means for rotation therewith, and link and lever means operatively connected to said programming cam and interConnected between its input and output means and adapted to assume varied configurations in response to rotation of said programming cam to effect said increases and decreases in gain.
Claim 63
Dependent Claim
260 words
A mixing and programming unit for use with a VTOL aircraft having a plurality of attitude control elements including tiltable laterally spaced thrust producers, said unit being adapted to provide pitch, yaw and roll control outputs for the attitude control elements in response to pilot''s pitch, yaw and roll control signal inputs, said unit comprising pitch, roll, and yaw programming assemblies having respective pilot''s pitch, roll and yaw control signal input means and also having respective pitch roll and yaw controlling output means associated therewith, and a shaft means rotatably mounted on said unit and adapted to be connected such that the shaft occupies angular positions in accordance with the angle of tilt of the thrust producers, said shaft means being operatively connected to each of the pitch, roll and yaw programming assemblies to provide a further input thereto, each of the pitch, roll, and yaw programming assemblies including a variable gain mechanism connected between its input for pilot''s control signals and its output means with each variable gain mechanism being adapted to respond to the further input provided by the shaft means whereby the gain of each variable gain mechanism is a predetermined function of the angular position of said shaft, each variable gain mechanism including a programming cam connected to said input shaft means for rotation therewith, and link and lever means operatively connected to said programming cam and interConnected between its input and output means and adapted to assume varied configurations in response to rotation of said programming cam to effect said increases and decreases in gain.
Claim 64
Dependent Claim
203 words
The mixing and programming unit according to claim 57 wherein the link and lever means of each of said yaw and roll variable gain mechanism comprises; a pivoted cam follower lever having follower means contacting its associated programming cam, a first link connected adjacent one end to the output means of said mechanism and connected adjacent its opposite end for movement in an arcuate path together with said cam follower lever, said opposite end of said first link also being connected to one end of a second link, the second link being connected adjacent its opposite end to an end portion of an input lever, said input lever being pivotally connected to a fixed pivot, the latter being positioned such that one point on said arcuate path is aligned with the axis of the fixed pivot, said input lever also being operably connected to the input means for control signals and occupying angular positions determined thereby, whereby angular movement of said input lever in response to a control input to the variable gain mechanism effects movement of the output means of said mechanism except when said opposite end of said first link is in correspondence with said one point on said arcuate path.
Claim 65
Dependent Claim
98 words
The mixing and programming unit according to claim 56 wherein the yaw programming assembly comprises a first and a second variable gain mechanism with the roll programming assembly comprising a third and a fourth variable gain mechanism with the output means for said yaw and roll programming assemblies comprising first, second, third and fourth outputs respectively associated with said first, second, third and fourth variable gain mechanisms, means for summing together the outputs of the first and the third variable gain mechanisms, and further means for summing together the outputs of the second and fourth variable gain mechanisms.
Claim 66
Dependent Claim
142 words
The mixing and programming unit according to claim 58 wherein the yaw programming assembly comprises a first and a second variable gain mechanism with the roll programming assembly comprising a third and a fourth variable gain mechanism with the output means for said yaw and roll programming assemblies comprising first, second, third and fourth outputs respectively associated with said first, second, third and fourth variable gain mechanism, means providing pitch, roll and yaw stability inputs, summing means to combine the pilot''s yaw control signal to the yaw stability input to produce a net trimmed yaw input signal, summing means to combine the pilot''s roll control signal with the roll stability input to produce a net trimmed roll input signal, and summing means to combine the pilot''s pitch control signal to the pitch stability input to produce a net trimmed pitch input signal.
Claim 67
Dependent Claim
44 words
The mixing programming unit according to claim 59 wherein a first one of said input levers is common to the first and second variable gain mechanisms, and a second one of said input levers is common to the third and fourth variable gain mechanisms.
Claim 68
Dependent Claim
320 words
A mixing and programming unit for a VTOL aircraft having tiltable laterally spaced thrust producers adapted to be tilted between a nontilted substantially horizontal position and a tilted position relative to the substantially horizontal position, said unit being adapted to provide pitch, yaw and roll control outputs in response to the pilot''s pitch, yaw and roll inputs thereto comprising: a. a pitch programming assembly having an input for pilot''s pitch control signals and a pitch controlling output means; b. a roll programming assembly having an input for pilot''s roll control signals and a first and a second roll controlling output means; c. a yaw proGramming assembly having an input for pilot''s yaw control signals and a first and a second yaw controlling output means; d. a further input means operatively connected to each of said pitch, roll, and yaw programming assemblies, said further input means comprising shaft means mounted for rotation to angular positions determined by the angle of tilt of said laterally spaced thrust producers; e. each of said pitch, roll, and yaw programming assemblies being responsive to said further input means whereby the output of each of said output means is a predetermined function of said angle of tilt; f. said pitch programming assembly being adapted to produce an output in response to a pilot''s pitch control input thereto when the laterally spaced thrust producers are tilted; g. said yaw programming assembly being adapted to produce in response to a pilot''s yaw input signal thereto, when said laterally spaced thrust producers are tilted, one output at said first yaw controlling output means and another output at said second yaw controlling output means; and h. said roll programming assembly being adapted to produce in response to a pilot''s roll input signal thereto, when said laterally spaced thrust producers are tilted, one output at said first roll controlling output means and another output at said second roll controlling output means.
Claim 69
Dependent Claim
320 words
A mixing and programming unit for a VTOL aircraft having tiltable laterally spaced thrust producers adapted to be tilted between a nontilted substantially horizontal position and a tilted position relative to the substantially horizontal position, said unit being adapted to provide pitch, yaw and roll control outputs in response to the pilot''s pitch, yaw and roll inputs thereto comprising: a. a pitch programming assembly having an input for pilot''s pitch control signals and a pitch controlling output means; b. a roll programming assembly having an input for pilot''s roll control signals and a first and a second roll controlling output means; c. a yaw proGramming assembly having an input for pilot''s yaw control signals and a first and a second yaw controlling output means; d. a further input means operatively connected to each of said pitch, roll, and yaw programming assemblies, said further input means comprising shaft means mounted for rotation to angular positions determined by the angle of tilt of said laterally spaced thrust producers; e. each of said pitch, roll, and yaw programming assemblies being responsive to said further input means whereby the output of each of said output means is a predetermined function of said angle of tilt; f. said pitch programming assembly being adapted to produce an output in response to a pilot''s pitch control input thereto when the laterally spaced thrust producers are tilted; g. said yaw programming assembly being adapted to produce in response to a pilot''s yaw input signal thereto, when said laterally spaced thrust producers are tilted, one output at said first yaw controlling output means and another output at said second yaw controlling output means; and h. said roll programming assembly being adapted to produce in response to a pilot''s roll input signal thereto, when said laterally spaced thrust producers are tilted, one output at said first roll controlling output means and another output at said second roll controlling output means.
Claim 70
Dependent Claim
84 words
The invention set forth in claim 62 wherein said pitch, roll, and yaw programming assemblies each include at least one variable gain mechanism, each of the latter having respective programming cams of predetermined configuration adapted to vary the gain of their associated variable gain mechanisms in predetermined fashion in response to changes in wing tilt angle, the programming cams being connected to said shaft means for rotation therewith so that they assume angular positions corresponding to the angular positions of tilt of said wing.
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) | 1974-03-29 | 1974-09-28 | 1975-03-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-03-29 | 1978-09-28 | 1979-03-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-03-29 | 1982-09-28 | 1983-03-30 | $7700.00 | Window Closed / Lapsed |