Patent Application
20110046901
This invention relates to a method for monitoring the status of an energy reserve accumulator connected to a fluid system.
It also relates correlatively to a monitoring device adapted for using the method as well as to an aircraft using the invention.
Airplanes generally are equipped with several hydraulic circuits, allowing activation of all the ancillary equipment of the airplane.
Generally, each device controlled by a hydraulic circuit is installed on both a main hydraulic circuit and an auxiliary hydraulic circuit, independent and autonomous, for reasons of safety.
As described in the document FR 2 888 898, it is known to use on such a hydraulic system an energy reserve accumulator that makes it possible to release its hydraulic energy reserve to the controlled components, in order to maintain the pressure in the hydraulic circuit at a level close to the rated operating pressure of these components.
This energy reserve accumulator is placed on the high-pressure hydraulic line of the fluid system, between a hydraulic power generator and the controlled components, remote from this power generator.
Such an accumulator makes it possible to absorb the overpressures generated in the hydraulic circuit by the operation of the various controlled components and in this way to prevent the structure and the equipment items of the airplane from being damaged during sudden pressure change in the lines.
In order to monitor the status of an energy reserve accumulator, the document FR 2 888 898 proposes a method for checking the status of pressurization of an energy accumulator.
In principle, this monitoring method consists, after having pressurized the fluid system to an operating pressure, in measuring the time interval necessary for the fluid system to progress from a predetermined first pressure to a predetermined second pressure and in comparing this time interval with a predetermined reference time.
This reference time is determined by using the monitoring method on a reference accumulator.
This monitoring method, however, is ineffective in certain configurations of the hydraulic system.
In fact, the speed with which the pressure of the fluid decreases in a fluid system depends on the voluminal capacity of this system.
Thus, the greater the volume of fluid, the longer the pressure of the fluid system will take to drop.
Furthermore, in a fluid system, there is an internal flow between the high-pressure part and the low-pressure part of the system. The lower the flow between the high-pressure part and the low-pressure part, the longer the pressure of the system will take to drop.
Thus, in an aircraft with low flow rate and/or with a large voluminal capacity of the fluid system, the time taken by the system to progress from a first predetermined pressure to a second predetermined pressure may be considerable because of the configuration of the hydraulic system itself, and thus not be directly representative of the operating status of the energy accumulator.
This invention has as a purpose to resolve the aforementioned drawbacks and to propose an effective method for status monitoring of an energy reserve accumulator, making it possible to check the operation of an energy accumulator independently of the configuration of the hydraulic system on which this energy accumulator is installed.
To this end, this invention relates to a method for monitoring the status of an energy reserve accumulator, the accumulator being connected to a fluid system, characterized in that it comprises the following successive steps:
Thus, by comparing two time-interval measurements on a curve of pressure decrease in the fluid system, it is possible to deduce the operating status of the energy accumulator connected to this fluid system, freeing oneself from the characteristics (voluminal capacity, internal flow rate) of the hydraulic system.
In a practical embodiment of the invention, allowing an easy comparison of the measured times, the difference between the first predetermined pressure and the second predetermined pressure is more or less equal to the difference between the third predetermined pressure and the fourth predetermined pressure.
In practice, the second predetermined pressure is higher than the precharge pressure of the accumulator at a temperature more or less equal to 60° C.
Furthermore, the third predetermined pressure is lower than the precharge pressure of the accumulator at a temperature more or less equal to −40° C.
The predetermined pressures used to monitor the operating status of the energy accumulator take into account the precharge pressure of the accumulator, the accumulator being able to provide energy to the fluid system as long as the pressure of the fluid system is higher than the precharge pressure.
According to a second aspect of the invention, it also relates to a device for monitoring the status of an energy reserve accumulator, the accumulator being connected to a high-pressure line of a fluid system and the fluid system comprising at least one pump for pressurization of the system, characterized in that it includes:
and in that the processing unit comprises electronic means for measuring a first time separating a measurement of a first predetermined pressure and a measurement of a second predetermined pressure transmitted by the pressure detector, and a second time separating a measurement of a third predetermined pressure and a measurement of a fourth predetermined pressure transmitted by the pressure detector, and means for comparing the first time and the second time to determine the status of the energy reserve accumulator.
This monitoring device has characteristics and advantages similar to those described above with reference to the method for monitoring the operating status of an energy reserve accumulator.
Finally, this invention relates to an aircraft comprising at least one energy reserve accumulator connected to a high-pressure line of a fluid system, characterized in that it comprises means adapted for using the method in accordance with the invention.
Other features and advantages of the invention also will become apparent in the description below.
In the attached drawings, provided by way of non-limitative examples:
Here, the hydraulic circuit is adapted for controlling the operation of a control surface 1 of an aircraft. Each fluid system comprises its own fluid reservoir 2 connected to a closed fluid distribution circuit 3, which includes a high-pressure line HP and a low-pressure line BP for the return of low-pressure fluid to reservoir 2. The fluid used is an incompressible liquid for an airplane, but any other liquid, or air, may be used for applications other than aeronautical (land or naval).
In this embodiment, the fluid distribution circuit is connected to a hydraulic jack 4. Such a distribution circuit 3 comprises rigid lines and possibly flexible lines for movable connections (brakes, landing gears, . . . ). The generation of hydraulic power is ensured, for example, by a variable-flow piston-pump 5.
When the pilot acts on a control 6 such as a joy stick, a control signal is sent to a computer 7 that controls a selector 8. A face of jack 4 receives the hydraulic pressure in an inlet chamber 9 bringing about a movement of the jack (toward the right in
It is known that in order to operate efficiently, the components consuming hydraulic power such as the jack described above need a constant rated pressure in chambers 9 or 10 according to the operation to be performed. As it happens, rapid operations cause the rated pressure to drop transitorily, because the hydraulic pumps are not able to ensure maintenance of this pressure, particularly if consumer components 4 are located far from this power source. The fluid entering inlet chamber 9 in fact must be under rated pressure in order to cause control surface 1 to move in optimal manner. The low-pressure fluid of outlet chamber 10 returns via a low-pressure line BP to reservoir 2. It is this pressure difference between inlet chamber 9 and outlet chamber 10 that activates control surface 1.
An energy reserve accumulator 13 that is adapted for releasing its hydraulic energy reserve to the consumer component or components 4 then is called upon in order to maintain the pressure at a level close to the rated operating pressure. This energy reserve accumulator 13 is placed on high-pressure hydraulic line HP between hydraulic power generator 5 and consumer components 4 farthest from this power generator 5.
This accumulator 13 also makes it possible to absorb the overpressures generated in the hydraulic circuit by the operation of consumer components 4. In this way, the structure and the equipment items of the airplane are prevented from being damaged during sudden pressure change in the lines.
Each fluid system comprises at least one energy reserve accumulator 13, their number depending on the demands of the ancillary equipment for fluid under rated pressure. The device of the invention described below in the context of monitoring the status of an accumulator connected to a fluid system may be adapted by the individual skilled in the art for monitoring all the accumulators of a fluid system.
Energy reserve accumulator 13 here is a membrane accumulator, that is to say comprising an elastic wall delineating the inner space of this accumulator in two cavities 14, 15. In a variant, this accumulator may be a hydraulic accumulator with metal bellows.
Since proper operation of this energy reserve accumulator is ensured only when the accumulator is correctly pressurized, it is necessary to regularly check the status of accumulator 13.
The device comprises a pressure detector 16 for measuring the pressure of the fluid in high-pressure line HP of this fluid system. This pressure detector 16 is installed on distribution circuit 3 on the same high-pressure line HP where energy reserve accumulator 13 to be tested is placed. It transmits a measurement signal representative of the pressure measured by the detector to a real-time processing unit 17.
This pressure detector 16 advantageously makes it possible to measure pressures going up to 420 bars with a measuring accuracy under +/−2.5 bars. Pressure detector 16 must have a very rapid acquisition speed in order to be able to respond to discharge times well under a second.
Real-time processing unit 17 is, for example, an on-board computer. It comprises electronic means 18 for measuring time interval Δt separating two pressure measurements predetermined by pressure detector 16. It further comprises means 19 for comparing time intervals Δt with each other. These means are used by software means that are known to the individual skilled in the art and will not be described here.
Monitoring the status of an accumulator 13 may be carried out in blind time each time the pump pressurizes the fluid system to rated pressure in stable manner, then stops. This monitoring thus may be performed, for example, after a maintenance operation, keeping up the generation of power necessary for the test. The secondary power generation, however, must be capable of being cut off instantaneously. A hydraulic pump with an electric power source, for example, thus may be used.
The processing unit then starts, in preprogrammed manner, the method for status monitoring of an accumulator, such as described below.
Real-time processing unit 17 may send a signal of status of energy reserve accumulator 13 to display means indicating to the operator whether a maintenance operation should be carried out on this accumulator 13.
The method for monitoring the status of an energy reserve accumulator 13 installed on a fluid system such as described above now is going to be described with reference to
First of all, this fluid system is pressurized. For that, at least one pressurization pump 5 such as described above is used. This fluid is maintained at an operating pressure PF, for example 210 bars, for at least a time τ so as to ensure stabilization of the fluid system. Stabilization of the system is achieved when no further pressure change is seen in the fluid system.
Pressurization of the fluid system then is stopped and the drop in pressure of the system is monitored. The gas pressure in the second cavity of energy reserve accumulator 13 then is deduced from analysis of pressure discharge time Δt of the fluid system.
In principle, the monitoring method consists in measuring a first time Δt1 taken by the fluid system to progress from a first pressure P1 to a second pressure P2, lower than first pressure P1, then a second time Δt2 taken by the fluid system to progress from a third pressure P3, lower than second pressure P2, to a fourth pressure P4, itself lower than third pressure P3.
It will be noted that the first and second pressures are higher than a precharge pressure PP of accumulator 13, while the third and fourth pressures are lower than the precharge pressure of accumulator 13. This precharge pressure PP corresponds to the pressure of the gas in second cavity 15 of energy reserve accumulator 13 in its new state, that is to say corresponds to the pressure such as specified on delivery from the factory.
By way of example, this precharge pressure PP is typically 133 bars at 20° C. for a nitrogen-type gas.
That means that accumulator 13 may provide energy to the fluid system as long as the pressure of the fluid system is higher than the precharge pressure.
It will be noted in particular that this precharge pressure PP depends on the temperature at which accumulator 13 happens to be.
In aeronautical applications, the method for monitoring the status of an accumulator should be used outside of extreme temperatures, of the −40° C. or +60° C. type.
The different predetermined pressures used by the monitoring method in accordance with the invention thus may be determined according to the following criteria.
Second predetermined pressure P2 should be higher than the precharge pressure of accumulator 13 at a temperature more or less equal to 60° C.: P2>PP+60° C..
Likewise, third predetermined pressure P3 is lower than the precharge pressure of the accumulator at a temperature more or less equal to −40° C.: P3<PP−40° C..
By way of non-limitative example, when PP+20° C. is approximately equal to 133 bars, the value of PP−40° C. is on the order of 106 bars and the value PP+60° C. is on the order of 152 bars.
First predetermined pressure P1 should be higher than second predetermined pressure P2 while remaining lower than operating pressure PF of the fluid system.
Finally, the difference between first predetermined pressure P1 and second predetermined pressure P2 is more or less equal to the difference between third predetermined pressure P3 and fourth predetermined pressure P4: (P1−P2)=(P3−P4).
In this way, the necessary time taken by the fluid system to drop by the same pressure variation, on both sides of precharge pressure PP of accumulator 13 at 20° C. is observed and measured.
In practice, if first time Δt1 is greater than second time Δt2, in a comparison step it is deduced therefrom that the accumulator is in an operational status, that is to say that the accumulator is releasing hydraulic energy to the fluid system between first pressure P1 and second pressure P2.
On the contrary, if first time Δt1 is less than second time Δt2, that means that the accumulator is not releasing any energy to the fluid system and thus the accumulator no longer is operational.
Typically, processing unit 17 indicates to the operator the operational or non-operational status of the accumulator, in order to bring about a maintenance activity, if need be, when accumulator 13 no longer is operational.
By way of purely illustrative example, in an aircraft with a fluid system having a rated pressure of 206 bars, the typical values of predetermined pressures used in the method for monitoring the status of an accumulator may be the following:
Of course, many modifications may be introduced in the exemplary implementation described above without departing from the context of the invention.
| Number | Date | Country | Kind |
|---|---|---|---|
| 0852826 | Apr 2008 | FR | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/FR09/00419 | 4/10/2009 | WO | 00 | 10/22/2010 |
