CA1131782A - Variometer for use in an aerodyne - Google Patents
Variometer for use in an aerodyneInfo
- Publication number
- CA1131782A CA1131782A CA327,736A CA327736A CA1131782A CA 1131782 A CA1131782 A CA 1131782A CA 327736 A CA327736 A CA 327736A CA 1131782 A CA1131782 A CA 1131782A
- Authority
- CA
- Canada
- Prior art keywords
- signal
- aerodyne
- vertical speed
- input
- output
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/04—Control of altitude or depth
- G05D1/06—Rate of change of altitude or depth
- G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
- G05D1/0615—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/62—Devices characterised by the determination or the variation of atmospheric pressure with height to measure the vertical components of speed
Abstract
ABSTRACT OF THE DISCLOSURE
The invention provides a variometer comprising: a dial having a scale representing a vertical speed, a needle indicating the instantaneous vertical speed h*° on said scale, an index representing the potential vertical speed h°T and, optionally, an indication, by digital display, of the slope of the aircraft, wherein the instantaneous vertical speed h*° is obtained by means of a circuit that solves the equation:
where:
jx1 is the acceleration component on the vertical axis of the aerodyne;
g is the acceleration due to gravity;
.theta. is the angle of roll of the aircraft;
s is the Laplace operator;
T1 and T2 are time constants;
h°A is a vertical speed signal that may originate from an anemometer system.
The invention provides a variometer comprising: a dial having a scale representing a vertical speed, a needle indicating the instantaneous vertical speed h*° on said scale, an index representing the potential vertical speed h°T and, optionally, an indication, by digital display, of the slope of the aircraft, wherein the instantaneous vertical speed h*° is obtained by means of a circuit that solves the equation:
where:
jx1 is the acceleration component on the vertical axis of the aerodyne;
g is the acceleration due to gravity;
.theta. is the angle of roll of the aircraft;
s is the Laplace operator;
T1 and T2 are time constants;
h°A is a vertical speed signal that may originate from an anemometer system.
Description
11317~2 The present invention concerns an improved variometer of a type comprising essentially a dial including a scale repre-senting a vertical speed, a needle indicating the instantane-ous vertical speed of the aerodyne on said scale, an index representing the potential vertical speed, which index is movable around the dial and whose position relative to the needle instantly shows the acceleration of the aerodyne along its trajectory, and possibly also an indication of the slope of the aircraft by means of a digital display.
In such a variometer the signal representing the instan-taneous vertical speed is obtained by means of a processor that solves the equation:
hA 1 2 Tl T2 ~ x + x (j - g), 1 + T 2 S 1 + T 1 5 2 where h* is the instantaneous aerodyne vertical speed signal;
hA is a vertical speed signal that may originate from an anemometer system;
Tl is a time constant;
T 2 is a time constant;
s is the Laplace operator;
j is the acceleration component along the vertical axis, which may originate from an intertial system.
X
, , .
~178;~
The signal representing the potential vertical speed hT
of the aerodyne is obtained by solving, with the aid of a processor, an equation of the form:
hT = h* + g Vx ~ dVx where h* is the instantaneous vertical speed of the aerodyne;
g is ~he acceleration due to gravity;
V is the ground speed furnished by an intertial system.
Owing to the character of the parameters it employs, and especially the groundspeed V and the acceleration component j , the variometer according to Canadian co-pending applica-tion No. 302,991 is applied essentially to aerodynes equipped with an inertial cystem.
Thus, more precisely, the subject of the present inven-tion is a variometer whose general principle is similar to that of the above-mentioned co-pending application, but which can make use of the parameters that are available on aerodynes which do not contain inertial systems.
To arrive at this result, according to the invention, the value of the instantaneous vertical speed indicated by the needle of the variometer is obtained by associating with the filtered vertical speed a forward phase shift ~hich is a function of the acceleration j along the vertical axis of the aircraft, calculated from ~he vertical acceleration measured according to the axes linked to the aerodyne and the angle of roll ~ of the aerodyne.
Y' 113~ 32 This instantaneous vertical speed is given by an expres-sion of the form:
h* = h ~ - x ( 1 2 + 1 2 (j ~) where j is the component of the acceleration along the verti-1 cal axis.
associated with the aircraft;
g is the acceleration due to gravity;
0 is the angle of roll of the aircraft;
The potential vertical speed hT of the aerodyne is given by the following formula:
h = h* + 1 V (dV*) where I: h* is the instantaneous vertical speed of the aerodyne (obtained as indicated above);
II: VH is a hybrid speed which has the formula:
TAS 1 + (11 + T2)5 Ti ~25 . .
~;
`:
~3~78Z
where TAS is the intrinsic speed of the aerodyne (true air speed):
Tl and T2 are time constants;
~ is the longitudinal trim of the aerodyne;
j is the component of the acceleration along the longi-tudinal axis of the aerodyne;
s is the Laplace operator;
dt is a mingling of the derivative of the intrinsic speed of the aerodyne and the weight-compensated longitudinal acceleration of the mass, and has the form;
dt 1 + T35 (iXl g s ~) l + s TAS
where T3 is a time constant.
An important advantage of the above-described method of determining the potential vertical speed consists in the fact that it makes it possible, in the event of a wind gradient, to establish a valid behaviour regardless of the air speed of the aerodyne, and do so without the necessity of making other corrections as was the case in the system described in Cana-dian application No. 302, 991.
An embodiment of the invention is described hereinafter as a non-limiting example, having reference to the accompanying drawing, where:
Figure l is a block diagram of the system for calculating . the instantaneous vertical speed of the aerodyne;
~31~32 Figure 2 is a block diagram of the system for calculating the potential vertical speed hT of the aerodyne;
Figure 3 is a block diagram illustrating the principle by which the improved variometer is controlled;
Figure 4 is a schematic representation of the face of an improved variometer.
Referring to Figure 1, the circuit by which the instan-taneous vertical speed signal is obtained and which controls the position of the variometer needle (Figure 4) comprises essentially:
- a direct chain, the input of which receives a signal representing the expression j - g cos ~,this direct chain com-prising an adding means 2, an integrating means 3 (transfer functlon l/s) at the output of which the instantaneous vertical speed signal h* is obtained;
- a feedback loop comprising a first subtracting means 4 which receives the signal h* and a vertical speed signal hA (input 5) coming from the anemometer system of the aerodyne, and the output of which is connected to an integrating means 6 of transfer function T -1 T S and an amplifier 7 having the gain 1 2x these two means being in parallel and being connected, at their outputs, to the two inputs of an adding means 8 which is connected in turn to adding means 2 ahead of integrating means 3.
With respect to the signal representing the potential vertical speed hT of the aerodyne, by which the movable index 11 (figure 4) of the variometer is generated, this signal is developed by means of the circuit represented in Figure 2 from:-..
. "
' 1131~82 - a signal representing the acceleration component Jx furnished by an accelerometer block 12;
- a signal representing the longltudinal trim ~, fur-nished by a verticality system 13;
- a system representing the TAS of the aerodyne deriving from an anemometer system 14;
- a signal representing the instantaneous vertical speed h* of the aerodyne furnished by a circuit of the type represented in Figure 1.
The signal coming from accelerometer block 12 is trans-mitted to a subtracting means 15 which, at its other input, re-ceives a signal 9 given by a sine-function generator 16 which receives the signal representing the trim ~ and given by verticality system 13.
The subtracting means 15, in turn, is connected at its output:
- on the one hand to a complementary filter 17 of second order which also receives a signal representing the TAS of the aerodyne coming from anemometer system 14 and which transmits a signal representing the hybrid speed VH, as defined above, to a multiplier means 18, and - on the other hand to an adding means 19 through the intermediary of a filter 20 with transfer function 1 + 3 5 .
:, ~
~L3~ 3Z
Adding means 19 also receives a signal representing the derivative with respect to time of the intrinsic speed of the aircraft which is given by a differentiation means 21 of transfer function 1 + I , connected to the output of anemometer system 14.
It should be noted that in order to ensure proper func-Or Ortioning, the time constants T3/differentiation means 21 and/filter 20 must be identical.
The signal dV = ~ 3s(~xl g sin ~) + 1 + T 5 TAS
furnished by addition means 19 is transmitted to the second input of multiplier 18.
The output of multiplier 18 is connected through the inter-mediary of a filter 22 of transfer function 1 1+ T 5 to one of the two inputs of a summation means 23, which receives, through its second input 24, a signal representing the instantaneous vertical speed h*, originating from the circuit represented in Figure 1.
The signal furnished by summation means 23 is the signal of potential vertical speed hT which makes it possible to gene~
rate the index 11 of the variometer (Figure 4).
In general, the signals representing h*, hT and the parameter displayed digitally at digital display 25 on the va-riometer (Figure 4), e.g. the slope Yl = ~ ~ ~ or the slope Y2 ~ V- ~ which is a pseudo air/ground slope, can be formed by a calculating means according to the block diagram represented in Figure 3.
This calculating means can comprise a central unit 26 which receives:-~ .
, -8-11317~32 - the signals representing the TAS of the aerodyne and the vertical speed hA of the aerodyne coming from an anemometer sys-tem 27;
- signals representing the longitudinal trim ~ and the angle of roll 0 of the aerodyne, from a verticality system 28;
- the signals j and j which are components of the ac-celeration associated with the aerodyne, from an accelerometer block 29;
- a signal representing the angle of incidence ~ of the aerodyne, from an angle-of-incidence detector 30.
It should be noted that from these various parameters the central unit can furnish a datum on the total slope YT =( xl g zl ) and a datum on the aerodynamic slope ra = ~ - ~, which data can be utilized by numerous instruments on board the aerodyne, e.g.
automatic pilot systems, flight ~uidance horizons, etc.
This central unit can also be designed to carry out rapid detection of a wind gradient, e.g. by monitoring the variations of a quantity s (TAS) A (YT ra) g 1 + 0.2 s and delivering a warning signal when this quantity, possibly com-bined with the angle of incidence ~ of the aerodyne at the moment the wind gradient appears, rises above the predetermined threshold value.
. . : .
~ ' ~
Where the aerodyne possesses such a wind-gradient-detection system the invention proposes to utilize, as a warning signal, a signal lamp 31 situated on the dial of the variometer or in its immediate vicinity, so that as soon as a wind gradient occurs, the attention of the pilot will be attracted to the variometer, which indicates, in particular by the distance between the needle and index 11, the nature of the manoeuvres which he must execute.
, ~
, ~
In such a variometer the signal representing the instan-taneous vertical speed is obtained by means of a processor that solves the equation:
hA 1 2 Tl T2 ~ x + x (j - g), 1 + T 2 S 1 + T 1 5 2 where h* is the instantaneous aerodyne vertical speed signal;
hA is a vertical speed signal that may originate from an anemometer system;
Tl is a time constant;
T 2 is a time constant;
s is the Laplace operator;
j is the acceleration component along the vertical axis, which may originate from an intertial system.
X
, , .
~178;~
The signal representing the potential vertical speed hT
of the aerodyne is obtained by solving, with the aid of a processor, an equation of the form:
hT = h* + g Vx ~ dVx where h* is the instantaneous vertical speed of the aerodyne;
g is ~he acceleration due to gravity;
V is the ground speed furnished by an intertial system.
Owing to the character of the parameters it employs, and especially the groundspeed V and the acceleration component j , the variometer according to Canadian co-pending applica-tion No. 302,991 is applied essentially to aerodynes equipped with an inertial cystem.
Thus, more precisely, the subject of the present inven-tion is a variometer whose general principle is similar to that of the above-mentioned co-pending application, but which can make use of the parameters that are available on aerodynes which do not contain inertial systems.
To arrive at this result, according to the invention, the value of the instantaneous vertical speed indicated by the needle of the variometer is obtained by associating with the filtered vertical speed a forward phase shift ~hich is a function of the acceleration j along the vertical axis of the aircraft, calculated from ~he vertical acceleration measured according to the axes linked to the aerodyne and the angle of roll ~ of the aerodyne.
Y' 113~ 32 This instantaneous vertical speed is given by an expres-sion of the form:
h* = h ~ - x ( 1 2 + 1 2 (j ~) where j is the component of the acceleration along the verti-1 cal axis.
associated with the aircraft;
g is the acceleration due to gravity;
0 is the angle of roll of the aircraft;
The potential vertical speed hT of the aerodyne is given by the following formula:
h = h* + 1 V (dV*) where I: h* is the instantaneous vertical speed of the aerodyne (obtained as indicated above);
II: VH is a hybrid speed which has the formula:
TAS 1 + (11 + T2)5 Ti ~25 . .
~;
`:
~3~78Z
where TAS is the intrinsic speed of the aerodyne (true air speed):
Tl and T2 are time constants;
~ is the longitudinal trim of the aerodyne;
j is the component of the acceleration along the longi-tudinal axis of the aerodyne;
s is the Laplace operator;
dt is a mingling of the derivative of the intrinsic speed of the aerodyne and the weight-compensated longitudinal acceleration of the mass, and has the form;
dt 1 + T35 (iXl g s ~) l + s TAS
where T3 is a time constant.
An important advantage of the above-described method of determining the potential vertical speed consists in the fact that it makes it possible, in the event of a wind gradient, to establish a valid behaviour regardless of the air speed of the aerodyne, and do so without the necessity of making other corrections as was the case in the system described in Cana-dian application No. 302, 991.
An embodiment of the invention is described hereinafter as a non-limiting example, having reference to the accompanying drawing, where:
Figure l is a block diagram of the system for calculating . the instantaneous vertical speed of the aerodyne;
~31~32 Figure 2 is a block diagram of the system for calculating the potential vertical speed hT of the aerodyne;
Figure 3 is a block diagram illustrating the principle by which the improved variometer is controlled;
Figure 4 is a schematic representation of the face of an improved variometer.
Referring to Figure 1, the circuit by which the instan-taneous vertical speed signal is obtained and which controls the position of the variometer needle (Figure 4) comprises essentially:
- a direct chain, the input of which receives a signal representing the expression j - g cos ~,this direct chain com-prising an adding means 2, an integrating means 3 (transfer functlon l/s) at the output of which the instantaneous vertical speed signal h* is obtained;
- a feedback loop comprising a first subtracting means 4 which receives the signal h* and a vertical speed signal hA (input 5) coming from the anemometer system of the aerodyne, and the output of which is connected to an integrating means 6 of transfer function T -1 T S and an amplifier 7 having the gain 1 2x these two means being in parallel and being connected, at their outputs, to the two inputs of an adding means 8 which is connected in turn to adding means 2 ahead of integrating means 3.
With respect to the signal representing the potential vertical speed hT of the aerodyne, by which the movable index 11 (figure 4) of the variometer is generated, this signal is developed by means of the circuit represented in Figure 2 from:-..
. "
' 1131~82 - a signal representing the acceleration component Jx furnished by an accelerometer block 12;
- a signal representing the longltudinal trim ~, fur-nished by a verticality system 13;
- a system representing the TAS of the aerodyne deriving from an anemometer system 14;
- a signal representing the instantaneous vertical speed h* of the aerodyne furnished by a circuit of the type represented in Figure 1.
The signal coming from accelerometer block 12 is trans-mitted to a subtracting means 15 which, at its other input, re-ceives a signal 9 given by a sine-function generator 16 which receives the signal representing the trim ~ and given by verticality system 13.
The subtracting means 15, in turn, is connected at its output:
- on the one hand to a complementary filter 17 of second order which also receives a signal representing the TAS of the aerodyne coming from anemometer system 14 and which transmits a signal representing the hybrid speed VH, as defined above, to a multiplier means 18, and - on the other hand to an adding means 19 through the intermediary of a filter 20 with transfer function 1 + 3 5 .
:, ~
~L3~ 3Z
Adding means 19 also receives a signal representing the derivative with respect to time of the intrinsic speed of the aircraft which is given by a differentiation means 21 of transfer function 1 + I , connected to the output of anemometer system 14.
It should be noted that in order to ensure proper func-Or Ortioning, the time constants T3/differentiation means 21 and/filter 20 must be identical.
The signal dV = ~ 3s(~xl g sin ~) + 1 + T 5 TAS
furnished by addition means 19 is transmitted to the second input of multiplier 18.
The output of multiplier 18 is connected through the inter-mediary of a filter 22 of transfer function 1 1+ T 5 to one of the two inputs of a summation means 23, which receives, through its second input 24, a signal representing the instantaneous vertical speed h*, originating from the circuit represented in Figure 1.
The signal furnished by summation means 23 is the signal of potential vertical speed hT which makes it possible to gene~
rate the index 11 of the variometer (Figure 4).
In general, the signals representing h*, hT and the parameter displayed digitally at digital display 25 on the va-riometer (Figure 4), e.g. the slope Yl = ~ ~ ~ or the slope Y2 ~ V- ~ which is a pseudo air/ground slope, can be formed by a calculating means according to the block diagram represented in Figure 3.
This calculating means can comprise a central unit 26 which receives:-~ .
, -8-11317~32 - the signals representing the TAS of the aerodyne and the vertical speed hA of the aerodyne coming from an anemometer sys-tem 27;
- signals representing the longitudinal trim ~ and the angle of roll 0 of the aerodyne, from a verticality system 28;
- the signals j and j which are components of the ac-celeration associated with the aerodyne, from an accelerometer block 29;
- a signal representing the angle of incidence ~ of the aerodyne, from an angle-of-incidence detector 30.
It should be noted that from these various parameters the central unit can furnish a datum on the total slope YT =( xl g zl ) and a datum on the aerodynamic slope ra = ~ - ~, which data can be utilized by numerous instruments on board the aerodyne, e.g.
automatic pilot systems, flight ~uidance horizons, etc.
This central unit can also be designed to carry out rapid detection of a wind gradient, e.g. by monitoring the variations of a quantity s (TAS) A (YT ra) g 1 + 0.2 s and delivering a warning signal when this quantity, possibly com-bined with the angle of incidence ~ of the aerodyne at the moment the wind gradient appears, rises above the predetermined threshold value.
. . : .
~ ' ~
Where the aerodyne possesses such a wind-gradient-detection system the invention proposes to utilize, as a warning signal, a signal lamp 31 situated on the dial of the variometer or in its immediate vicinity, so that as soon as a wind gradient occurs, the attention of the pilot will be attracted to the variometer, which indicates, in particular by the distance between the needle and index 11, the nature of the manoeuvres which he must execute.
, ~
, ~
Claims (7)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. An aerodyne display apparatus, comprising a vario-meter having a scale representing vertical speed, a first indica-tor movable along said scale indicating instantaneous vertical speed h*o, and a second indicator movable along said scale re-presenting potential vertical speed hoT, inputs for receiving respectively signals representing the acceleration component jz1, on the vertical axis, and the angle of roll ? of the aerodyne, and the vertical speed hoA, a processing circuit for deriving a signal representing instantaneous vertical speed h*o from the signals applied to said inputs in accordance with the following relationship:
where g is the acceleration due to gravity, s is the Laplace operator, and T1 and T2 are time constants, said processing circuit being connected to said variometer, whereby the signal derived in said processing circuit drives said first indicator.
where g is the acceleration due to gravity, s is the Laplace operator, and T1 and T2 are time constants, said processing circuit being connected to said variometer, whereby the signal derived in said processing circuit drives said first indicator.
2. A display apparatus according to claim 1 further com-prising inputs for receiving signals representing the longitu-dinal trim .theta. of the aerodyne, the acceleration component jx1 along the longitudinal axis, and the true airspeed TAS, and a second processing circuit for deriving a signal representing the potential vertical speed hoT of the aerodyne from the sig-nals applied to said inputs in accordance with the following relationship:
where VH is a hybrid speed which is given by where T '1 and T 1 2 are time constants, s is the Laplace operator, and is a mixture of the derivative of the true airspeed of the aerodyne and the weight-compensated longitudinal acceler-ation, the expression for being of the form:
where T3 is a time constant, said second processing circuit being connected to said variometer, whereby the signal derived in said second processing circuit drives said second indicator.
where VH is a hybrid speed which is given by where T '1 and T 1 2 are time constants, s is the Laplace operator, and is a mixture of the derivative of the true airspeed of the aerodyne and the weight-compensated longitudinal acceler-ation, the expression for being of the form:
where T3 is a time constant, said second processing circuit being connected to said variometer, whereby the signal derived in said second processing circuit drives said second indicator.
3. A display apparatus according to claim 2 wherein said first-mentioned processing circuit comprises: a direct chain having an input receiving a signal representing (jz1-g cos 0), and comprising a first adding means followed by an integrating means at the output of which the signal h*° is obtained, said first adding means having one input receiving said signal re-presenting jz1 - g cos ?; a feedback loop containing a subtract-ing means receiving at its inputs respectively the signal h*°
and a signal h°A, and the output of which is connected to an inte-grating means having a transfer function and to an amplifier having a gain the integrating means and the am-plifier having a gain being connected in parallel and connected at their outputs to respective inputs of a second add-ing means, the output of which is connected in turn to another of the inputs of the first adding means.
and a signal h°A, and the output of which is connected to an inte-grating means having a transfer function and to an amplifier having a gain the integrating means and the am-plifier having a gain being connected in parallel and connected at their outputs to respective inputs of a second add-ing means, the output of which is connected in turn to another of the inputs of the first adding means.
4. A display apparatus according to claim 3 wherein the second processing circuit comprises: a subtracting means which receives at one input the signal jx1, and at its other in-put a signal sine .theta., said subtracting means having an output connected to an input of a complementary filter of second order, which also receives at another input the signal representing the true airspeed of the aerodyne, said complementary filter hav-ing an output connected to a first input of a multiplying means, the output of the subtracting means also being connected through a filter to one input of a third adding means, another input of which receives a signal representing the derivative with res-pect to time of the true airspeed of the aerodyne, and the output of said third adding means connected to a second input of the multiplying means, an output of which is connected, through a filter, to one of two inputs of a fourth adding means, which re-ceives at its second input a signal representing the instantan-eous vertical speed h*°, and which at its output provides the potential vertical speed signal h°T.
5. A display apparatus according to claim 1, 2 or 3, further including a signal lamp serving to generate a warning signal of a wind-gradient detection system.
6. A display apparatus according to claim 1, 2 or 3, wherein the variometer has a digital display indicating the slope of the aerodyne.
7. A display apparatus according to claim 1, 2 or 3, further comprising an accelerometer for supplying the jz1 and jx1 signals, an aneometer for supplying the TAS signal, and trim and roll sensors for supplying the .theta. and ? signals.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7814560A FR2426265A2 (en) | 1977-05-10 | 1978-05-17 | Aircraft vertical speed variometer - uses anemometric information to derive reading without need for inertial sensor |
| FR78.14560 | 1978-05-17 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1131782A true CA1131782A (en) | 1982-09-14 |
Family
ID=9208324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA327,736A Expired CA1131782A (en) | 1978-05-17 | 1979-05-16 | Variometer for use in an aerodyne |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0006773B1 (en) |
| JP (1) | JPS6156952B2 (en) |
| CA (1) | CA1131782A (en) |
| DE (1) | DE2964402D1 (en) |
| WO (1) | WO1979001079A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2921728B1 (en) * | 2007-09-27 | 2009-11-27 | Eurocopter France | METHOD AND DEVICE FOR OBTAINING VERTICAL SPEED PREDICTIVE OF A GIRAVION |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3077557A (en) * | 1960-09-30 | 1963-02-12 | Sperry Rand Corp | Flight path computer |
| US3296422A (en) * | 1962-02-12 | 1967-01-03 | Honeywell Inc | Apparatus for computing true vertical position, velocity and acceleration for aircraft |
-
1979
- 1979-05-14 DE DE7979400301T patent/DE2964402D1/en not_active Expired
- 1979-05-14 JP JP54500765A patent/JPS6156952B2/ja not_active Expired
- 1979-05-14 WO PCT/FR1979/000043 patent/WO1979001079A1/en unknown
- 1979-05-14 EP EP79400301A patent/EP0006773B1/en not_active Expired
- 1979-05-16 CA CA327,736A patent/CA1131782A/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| WO1979001079A1 (en) | 1979-12-13 |
| DE2964402D1 (en) | 1983-02-03 |
| EP0006773A3 (en) | 1980-01-23 |
| JPS55500265A (en) | 1980-05-01 |
| EP0006773A2 (en) | 1980-01-09 |
| EP0006773B1 (en) | 1982-12-29 |
| JPS6156952B2 (en) | 1986-12-04 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |