method for monitoring condition of a damper, and condition monitoring system of a damper

专利摘要:
method for monitoring the condition of a damper; and, condition monitoring system for a damper. a method and system for monitoring the condition of a damper detecting gas temperature, gas pressure and damper stroke during a landing event. Oil loss is determined based on a deviation of a transient pressure coefficient derived from transient gas pressures in two different strokes of a nominal coefficient value. Gas loss is determined based on the temperature-adjusted transient gas pressure in a selected stroke and a nominal gas pressure value in the selected stroke.
公开号:BR102015006125A2
申请号:R102015006125-0
申请日:2015-03-19
公开日:2019-01-22
发明作者:Amir M. Fazeli；Adnan Cepic；Susanne M. Reber
申请人:Goodrich Corporation；
IPC主号:

专利说明:

"METHOD FOR MONITORING THE CONDITION OF A SHOCK ABSORBER, AND, MONITORING SYSTEM FOR THE CONDITION OF A SHOCK ABSORBER"
CROSS REFERENCE TO RELATED REQUESTS [001] This order claims priority for US Interim Order
61 / 968.462, entitled “SERVICING MONITORING ALGORITHM FOR MIXED FLUID-GAS LANDING GEAR SHOCK STRUTS”, filed on March 21, 2014, which is incorporated by reference.
BACKGROUND [002] Shock absorption devices are used in a wide variety of vehicle suspension systems to control the movement of the vehicle and its tires in relation to the ground and to reduce the transmission of transient forces from the ground to the vehicle. Shock absorption dampers are a common and necessary component in most aircraft landing gear assemblies. The shock absorbers used on the aircraft's landing gear are generally subject to more stringent performance requirements than most, if not all, ground vehicle shock absorbers. In particular, shock absorbers must control the movement of the landing gear, and absorb and cushion loads imposed on the train during landing, taxiing and takeoff.
[003] A shock absorber generally performs these functions by compressing a fluid inside a sealed chamber formed by hollow telescopic cylinders. The fluid usually includes a gas and a liquid, such as oil or hydraulic fluid. One type of shock absorber generally uses an “air-on-oil” arrangement, in which a trapped volume of gas (nitrogen or air) is compressed when the shock is axially compressed, and a volume of oil is metered through an orifice. The gas acts as an energy storage device, like a spring, so that after the end of a compression force, the damper returns to its original length.
/ 16
Shock absorbers also dissipate energy by passing oil through the orifice, so as the damper is compressed or extended, its rate of movement is limited by the action of absorption from the orifice and the oil.
[004] Over time, gas and / or oil may leak from telescopic cylinders and cause a change in the performance characteristics of the shock absorber. While gas pressure can be easily monitored, it is not easily determined if a loss of gas pressure arises from the gas leak alone or from the gas and oil leak, unless external evidence of an oil leak is seen. noticed by maintenance personnel. If a low pressure condition is detected in the absence of external evidence of an oil leak, maintenance personnel would then restore the gas pressure to a level prescribed by the addition of gas. This, however, eventually leads to degraded damper performance if oil has actually escaped the damper. Even if evidence of an oil leak is observed, maintenance personnel cannot easily determine how much oil remains, or whether the remaining amount of oil meets specifications or is acceptable for operation.
[005] Functionality and performance of a landing gear shock absorber depends on its oil volume and gas pressure. To ensure that the landing gear's functionality is within an accepted range, oil volume and gas pressure must be kept within the project envelope. In the past, static gas pressure measurement was the basis for maintaining shock absorbers.
SUMMARY [006] A method for monitoring the maintenance condition of a shock absorber, the method comprises detecting the gas temperature, gas pressure and shock stroke during a landing event. The oil loss is determined based on a transient pressure coefficient deviation derived from transient gas pressures in two different strokes of a nominal value / 16. The gas loss is determined based on the temperature-adjusted transient gas pressure in a selected stroke and a nominal gas pressure value in the selected stroke. An outlet is provided that indicates the need for maintenance of the damper based on oil loss and gas loss.
[007] A system for monitoring the condition of maintenance of a shock absorber includes a gas temperature sensor, a gas pressure sensor, a stroke sensor and a digital processor that determines whether the shock needs maintenance. The digital processor includes a recorder, a landing detector and a health monitor. The recorder acquires data for detecting gas temperature, gas pressure and stroke over time and stores the data in a data matrix. The landing detector determines the occurrence of a landing event based on course data in the data matrix. The health monitor determines oil loss and gas loss based on the gas temperature, gas pressure and course data from the data matrix during the landing event. The health monitor determines oil loss based on a transient pressure coefficient derived from transient pressure data over two different strokes and the detection of the gas temperature. The health monitor determines the gas loss based on the gas pressure in a selected course, the detection of the gas temperature and an expected gas pressure value in the selected course.
BRIEF DESCRIPTION OF THE DRAWINGS [008] FIG. 1 is a block diagram of a monitoring system for determining the oil volume and gas pressure in a damper based on pressure / temperature measurements of the transient gas.
[009] FIG. 2 is a graph of the transient pressure coefficient α as a function of the stroke s.
[0010] FIG. 3 is a graph of the transient pressure coefficient α as a function of the instantaneous compression ratio Cr (s).
/ 16
DETAILED DESCRIPTION [0011] In current practice during pre / post flight maintenance, gas pressure in the shock and travel in a static condition are measured, and any deviation from a theoretical static compressed air source curve of the shock is normally compensated for by maintenance. of the gas shock absorber. This approach is taken due to the reduced maintenance time associated only with the addition of gas to the damper. There are several problems with this method. First, investigations have shown that the pressure of the steady-state gas of the shock absorber depends on its operating conditions such as the compression rate during landing, oil saturation status in the fully extended position and the stroke in which maintenance is performed . As a result, depending on maintenance inspection conditions, a properly maintained damper with nominal amounts of gas pressure and oil volume may not follow the theoretical static compressed air source curve. Second, in the absence of visual signs of oil leakage, current practice assumes that the deviation from the static compressed air source curve is due to loss of gas and therefore could ignore an oil leak in the system.
[0012] A monitoring system and method are presented in which the pressure of the transient gas during landing in two strokes is used to detect and quantify the deviation of oil gas pressure and damper oil volume from the nominal values. A maintenance algorithm is performed by the monitoring system, based on the following parameters that are recorded at 100 Hz (or faster) continuously: (1) Gas pressure, (2) Gas temperature, and (3) Damper stroke . Using these parameters, oil loss (which requires oil and gas maintenance) and gas loss (which require gas maintenance) are determined and reported.
[0013] FIG. 1 shows a block diagram of monitoring system 10. Contrary to current practice, system 10 uses a / 16 gas pressure and transient temperature during the landing event and quantifies the oil volume and gas pressure in the shock absorber 12 Since gas pressure and oil volume are determined independently, they can be used for diagnostic and prognostic purposes. The rate of oil loss or gas loss can be used to schedule maintenance of the shock in the future. In addition, system 10 can be applied to any mixed fluid-gas buffer.
[0014] System 10 includes pressure sensor 14P, temperature sensor 14T, and stroke sensor 16 mounted on shock absorber 12 and digital processor 18. The pressure sensor 14P and temperature sensor 14T can be in the form of individual sensors or they can be in the form of a combined pressure / temperature sensor. The maintenance algorithm performed by processor 18 comprises the following sub-algorithms: recorder 20, landing detector 22, counter 24, health monitor 26 and data recorder 28.
[0015] The recorder 20 acquires the pressure and gas parameters of the pressure-temperature sensor 14 and the stroke parameter of the stroke sensor 16. The recorder 20 records the three parameters in a circular matrix or buffer that holds the readings for a certain period of time, for example, 15 seconds. A new set of recordings is added to the top of the matrix and the oldest data set is deleted from the bottom of the matrix to maintain the length of the matrix equivalent to 15 seconds of data. At any time, recorder 20 exports the matrix comprising the last 15 seconds of data to landing detector 22. At startup, when the length of the matrix is not equivalent to 15 seconds, recorder 20 sends a discrete signal of “false” detection 22, so that the landing detector 22 avoids using data from an incomplete matrix. Since the 15 seconds of measurements are available in the matrix, the discrete detection status signal turns to “true” and / 16 allows the landing detector 22 to use the measurements.
[0016] Once the landing detector 22 receives the data matrix, it checks the matrix against the following set of criteria:
(1) minimum stroke in the matrix is less than 0.2 inch (a selectable parameter), (1) maximum stroke in the matrix is greater than 10 inches (a selectable parameter), (3) stroke in the first five (5) seconds of the matrix is less than 0.2 inches (a selectable parameter), and (4) maximum stroke in the first ten (10) seconds of the matrix is greater than 9 inches (a selectable parameter).
[0017] The first two criteria ensure that the data set is associated with a landing, or a takeoff, or any other event that caused the shock absorber 12 to travel between 0.2 inches to 10 inches. The third criterion guarantees that the data set is associated with a landing event, because in the first (5) five seconds, the damper has been fully extended. The fourth criterion ensures that the chosen data set also includes five (5) seconds of measurements after compression. If the data matrix meets all of these criteria, it is categorized as a landing event and exported to health monitor 26. Counter 24 is also started to prevent landing detector 22 from receiving any new matrix for (5) five minutes (a selectable parameter). This relaxes the need for a high-speed processor since data acquisition and health monitoring will not be performed simultaneously. If the data matrix does not meet all the criteria, the landing detector 22 disregards the matrix and waits for the new data matrix.
[0018] Health monitor 26 requires real-time measurement of pressure, gas temperature and shock stroke during a landing event. Health monitor 26 determines oil loss using a / 16 oil level algorithm and gas loss using a gas level algorithm.
[0019] An oil level algorithm determines the volume of oil inside the damper 12 by first using the pressure of the transient gas in two predetermined strokes during landing to calculate a transient pressure coefficient, a. Then, the oil volume is determined by comparing the calculated α with its nominal value. The calculated oil volume is adjusted for temperature and the oil volume loss is determined. If no oil loss is detected, the gas level algorithm is activated.
[0020] The gas level algorithm uses the measured gas pressure and gas temperature in a given course to detect the gas level. The measured gas pressure is adjusted according to the measured temperature to obtain the resulting pressure in the environment. This value is compared to the expected pressure value using a calculation. The calculation output determines the gas level and can specify the amount by which the shock absorber 12 is over or under pressure.
[0021] Data logger 28 records the health monitor output for diagnostic and prognostic purposes. The volume of oil and gas pressure for each landing event is recorded by data logger 28. Data logger 28 determines the leak rate and predicts when damper 12 will require maintenance. Data logger 28 can provide indications that oil and gas maintenance is required (based on the detection of oil loss by the health monitor 26) or gas maintenance is required (based on the detection of gas loss by the health monitor health 26). For example, the loss of gas and loss of oil volume at each landing can be calculated and recorded, and the loss of oil volume and tendency to loss of gas can be used to predict when maintenance will be required [0022] Theoretical basis and experimental.
8/16 [0023] During the experiments it was found that a transient gas pressure in the damper during landing in the course domain is independent of its compression rate for compression rates above a certain threshold, and can be represented based on in the following equation:
PgaÁS ) = Xa (s _lf S _2f V _oih Y) ^S 2 S1
Eq. 1 in which are the transient gas flows in progress and a (s _lf s ₂ , V _oil , Y) during landing, and it is the coefficient of transient pressure that depends on strokes, ^Sa and ^S1 , volume of oil , ^{V <nl} , and oil saturation status in the fully extended position, £ independent of the gas pressure in the fully extended position.
s - 0 [0024] For the specific case where ¹ the above equation (Eq. 1) is rearranged as follows:
Eq. 2. 8 ™ (0) where is the gas pressure in the fully extended position. In a more general representation Eq. 2 is re-expressed as follows:
Eq. 3.
[0025] This equation for a shock absorber with a certain amount of oil volume and oil saturation level in the fully extended position is simplified as follows:
Eq. 4 oí (0, s, ν _{σί [} , γ) [0026] It was also verified that although the value is not affected by the gas pressure in a fully extended position, it is highly sensitive to the volume of oil.
[0027] Oil in the fully extended position can be in any of the following saturation states:
9/16 [0028] Subsaturated: The amount of gas dissolved in the oil is less than what is needed for saturation. The oil dissolves more gas over time to reach a saturated state. This state exists only before the first landing when the oil is newly replaced in the damper.
[0029] Saturated: the oil is in stable equilibrium with gas. There is no mass transfer at the gas / oil limit. This state exists after takeoffs with rapid extension rate specifically, for main landing gears where the extension rate is high enough to release all the extra gas dissolved in oil at high pressures in the previous landing.
[0030] Supersaturated: The amount of gas dissolved in the oil is more than the oil's capacity. The oil loses a little gas over time to reach a saturated state. For example, this state exists after takeoffs with slow extension rates specifically for the nose landing gear in which the extension rate and, consequently, the pressure drop rate is slow. As a result, the oil does not release all the extra gas dissolved in it at high pressures at the previous landing.
[0031] Thus, a shock gas pressure in the fully extended position is dependent on the oil saturation state. Even for a properly maintained shock absorber that has undergone new maintenance to compensate for gas-in-oil entrainment, the gas pressure will be less than the nominal value if the oil is oversaturated due to a slow extension rate at the previous takeoff.
[0032] The reference or nominal called below, is obtained with the nominal volume of oil while the oil is saturated with gas in the fully extended position. It has been found that, when the oil is supersaturated in the fully extended position, which occurs mostly ct (O, s) to _o (0, s) for the nose landing gear (NLG), it increases above. Since the oil in a properly maintained damper can be saturated at (0, s) or supersaturated, that calculated during landing is always greater than or
10/16 equal to “° ^í0 ' ^s5 for a serviced shock absorber. With reference to (0, s)
FIG. 2, since it is a non-linear function, the increase in the function of, it can be concluded that it is also always greater than or equal to a damper that has been maintained
ÜÍq C ^ l-f ^ 2 · ^ appropriately. it can be obtained experimentally for a damper that has been properly maintained with saturated oil in a fully extended position.
[0033] With reference to FIG. 2, falls below a _o (0, s)
If the oil volume is below the nominal value. In FIG. 2, up to 2% oil loss in a medium-sized aircraft landing gear causes the (o, s) <7 _o (0, s) crfO s to deviate significantly. Since 'is a nonlinear function, increasing the function of s, it can be concluded that = a (0, s ₂ ) / a (0, Si) ,, ..., Cf _o cs _lf s ₂ ) , also falls below for a shock absorber that has undergone little maintenance. Thus, comparing with reveals the loss of oil in a shock absorber.
[0034] In addition, it can also be used to quantify oil loss. It has also been found that it is linearly dependent on the compression rate on each stroke for a wide range of strokes FIG. 3, where the compression rate is defined as:
where is the volume of gas in the course ^s . Like this,
0: (0, ¾) ^ (¾) ^-
Eq. 5.
Eq. 6 where, and _S are the gas volumes in courses 0 and ⁵ for a damper that has been properly maintained. Thus, if it is calculated during landing, the volume of oil loss can also be estimated by calculating the change in the compression ratio.
[0035] The compression ratio is dependent on the volume of oil loss as follows:
11/16
Volume available to gas at 0 VÇg _ί13ι0 ÍCÕ + V _a gj ₀₃₃ ^r Volume available to gas at s Vgas, ^ ⁺ ^ οίϊ foss £ 03.1
Eq. 7 where, and are the gas volumes in the 0 and .s · courses for an a (si, s ₂ ) shock absorber that has been properly maintained. Thus, if it is calculated during landing, the volume of oil loss can also be estimated by calculating the change in the compression ratio.
[0036] Now based on these results, the algorithm is designed as follows:
The algorithm receives 15 seconds of data associated with a landing event. First, it ensures that the compression rate for the recorded landing event is greater than a threshold value, which is defined for each, j,. , jj rii, s ₂ j damper experimentally, and can be compared with because it is not dependent on the compression rate. In the next step, transient gas pressure in two strokes is required to derive ^S1 ' ^S2 . Thus, the (si, s ₂ ) £ calculated using the transient gas pressure during the landing as follows:
aCsi, s ₂ ) s ₂ where e
Eq- 8).
are predefined strokes that are chosen for each damper with the objective of reducing the error of the algorithm.
[0037] deviation from
In this phase, the volume of the oil loss is calculated using 0 to ₀ (s ₁ , s ₂ ) ~ ~ de and taking into account the thermal expansion / contraction of the oil:
£ .jíçi JIVj.iíoCSjl - 5 ΓΤ | | - ΊΪ, -, Γί -, .. J ^ -íhoCs J J | - [MS - (L + item, | J gg Ç
V „VgasoC ^S ) where, ⁰¹ ° ^ss is the estimated oil volume loss, 'are the nominal gas volumes in progress s, ^Cr ' ^otsí is the gas compression rate in progress for the damper that has been properly maintained, ⁰¹¹ is the oil temperature well before landing, ° ^1L0 is the nominal oil volume at ambient temperature ε and is the coefficient of volumetric thermal expansion of the oil. An
12/16 Since ⁰¹¹ is not available (without oil temperature sensor), it can be estimated using gas temperature knowing that the oil and gas temperature is almost the same before landing. Since the gas temperature measurement has a slow dynamics, temperature measurements before landing or in a fully extended position are not required. Thus, the oil temperature before landing that is necessary to determine the loss of oil volume (Eq. 9) can be estimated using the gas temperature recorded in the
Si course as follows:
Toii * TgaÁSl)
Eq. 10 [0038] If the volume of oil loss is above a certain threshold percentage value, then the damper needs to be maintained with oil and gas. The threshold value is determined for each train considering the performance requirement, operating temperature envelope, etc. In this case, there is no need to run the gas level algorithm since complete maintenance is required. If the volume of oil loss detected is below the threshold percentage value, the next step is to assess the gas level.
[0039] The gas level algorithm is activated if the oil level is within the acceptable range. Since the temperature measurement has a slow dynamics, the gas temperature recorded during landing basically represents the temperature of the gas before landing. Thus, the gas pressure measured in progress is adjusted to the temperature of the gas before landing based on the following equation:

where ^ / ^ 2) ^^ 3 (0), expected transient pressure for a serviced shock absorber is:
cί Uj) (Ο) Y ®o (0, -S ) Eq. 12.
(0), ~,,. ,. ~ ....... where and the nominal gas pressure in the fully extended position
13/16 and ^then · ⁰ '^ is determined experimentally for a shock absorber that has been properly maintained with saturated oil in a fully extended position. If q _ue is the gas loss is below a certain threshold, so no maintenance is required. Otherwise, the gas must be maintained.
Derivation of Eq, beta9 [0040] Test results show that the transient pressure coefficient α is a linear function of the compression ratio. Since the compression ratio is dependent on the volume of oil, variations in the compression ratio are used to determine the oil loss as follows. Equations 13 through 20 illustrate the progression of the equation to solve the loss of oil.
Ctp Cp.SjD C-γ pCs _a J o: _D C3 _L , s ₂ ) h _d Cd.s _l ] Cf-p [3,5
---- r hLd.SjJ
Cf (¾)
Lf Cs ^ jus.pk ^ + Vu ^ p - (v ₀ l £ _d -V _o j [+ -ιϊξ})
Eq. 13 gp 'A' ³ )
Eq. 14 «^ 1) (v _{JQJ d} ( _3l ) + V _{dí D} - (v _{oí D} -V _{DÍÍÍO £ i} Xl + _£ (r _oii -29sri) v 5Q _{£ D} (^) c; _D ú- _L .jn) (^ aj.pf ³ si ^_tr oiÍ.P ^ε ί ^ϊ οίί “298} + VDj [[0ÍE (1 + eCTd [[-298})) v5a;, ρΧ) ^E. p X) -vDíi „ps (T _D íi - 2 98) + Vp í; _{ioi £} [1 + s Cr ₀ ÍJ - 2 98))) v _{5ai D} Cs _s ) (^ as ^ Cl) ^- Xjíí.O ^s (Uii ^- 298) + Χ, ίΐ ^H (^ 1 ^ 2) ^ 0 ^ .. 11 (^ 1) (/jos.jjÇz) ^- K, É! / () 5 (^, 1 - 298) + Voé! Íc) j5J ^h ü ( ^S 1 ' ^S 2) ^ esas, (j ( ^S l) ^{- S} (-Cíi ^- 298) ') + Ιζ, ϋ ic · ^ ¹ 298)) ^ (^, ^) 1 / ^ (^) = ^, ¾) ^ ¾) (l / ej, ₀ (s _z ) - ΐχ ₀ ^ _{i !! P} ss (l + laugh _cÉ! - 298)> Χ, ^ „, ₀ (Χ)
U _{í! ÍO} ss (l + laugh _cÉ - 298)) at ₀ X, s _z ) l / _ej , ₀ X) - V _{eilI & 33} (1 + ί (Γ _οί! 298)) aX, X) i; _e3 , ₀ X) = «(s ^) ^^) (l / _Q3j0 (s ₂ ) - V _{eÉ! j0s} (T _QÍl - 298)) ^to 0 (- ^ 1, ¾) ^ 05,0 (^ 2) (ijM, o ( ^s i) ^- Uti..o ^£ (Uii ^- 298)) ^ crii íü-sj · .0 ^ 3 ^ ^- ^ DLÍjD ^£ ^ QLÍ ^{- -} . DD .D ^£ LC ^-
Eq. 15
Equation 16 (1 + ^ - 298).)) = (1 + ^ - 298))) (1 + _<EII T <T -298 _PEI)) +
Eq. 17.
Eq. 18).
Eq. 19
Eq. 20
Discussion of Possible Modalities / 16 [0041] The following are non-exclusive descriptions of possible modalities of the present invention.
[0042] A method for monitoring the condition of a shock absorber based on the detection of the gas temperature, gas pressure and stroke of the shock during a landing event; determining the oil loss based on a deviation from the transient pressure coefficient derived from transient gas pressures in two different strokes of a nominal coefficient value; determine the gas loss based on the temperature-adjusted transient gas pressure in a selected stroke and a nominal gas pressure value in the selected stroke; and providing an output indicating the need for maintenance of the damper based on oil loss and gas loss.
[0043] The method of the previous paragraph can optionally include, additionally and / or alternatively, any one or more of the following characteristics, configurations and / or additional components:
the detection of gas temperature, gas pressure and stroke comprises the detection of the damper; detecting the temperature of the transient gas inside the shock absorber during landing to provide steady state oil and gas temperature values before landing; detection of a first transient gas pressure of the shock absorber in a first stroke during a landing event; and detecting a second transient gas pressure from the shock in a second stroke during a landing event. [0044] The determination of oil loss comprises the derivation of a transient pressure coefficient based on the first and second transient gas pressure of the damper; calculating the volume of oil loss based on a deviation from the transient pressure coefficient from a nominal coefficient value.
[0045] Considering the thermal expansion / contraction of the oil to determine the loss of oil volume.
/ 16 [0046] The calculation of the oil loss volume based on the thermal expansion or contraction of the oil is performed using the gas temperature value during landing.
[0047] The determination of gas loss comprises: if the volume of oil loss is within an acceptable range, adjustment of the second transient gas pressure based on the gas temperature value; determination of gas loss based on the second adjusted transient gas pressure and a second nominal gas pressure value.
[0048] Providing an output comprises: providing an indication that the damper needs to be maintained for oil and gas if the volume of oil loss exceeds an oil loss threshold, and providing an indication that the damper needs to be maintained for the gas if the gas loss exceeds a gas loss threshold.
[0049] A system for monitoring the maintenance conditions of a shock absorber includes a gas temperature sensor for detecting gas temperature in the shock absorber; a gas pressure sensor for detecting gas pressure in the shock; a travel sensor for detecting the shock travel; and a digital processor to determine if the shock needs maintenance. The digital processor includes a recorder, a landing detector and a health monitor. The recorder acquires data for detecting gas temperature, gas pressure and stroke from the gas temperature sensor, gas pressure sensor, and stroke sensor over time and stores the data in a data matrix. The landing detector determines the occurrence of a landing event based on course data in the data matrix. The health monitor determines oil loss and gas loss based on the gas temperature, gas pressure and course data from the data matrix during the landing event. The health monitor determines oil loss based on a transient pressure coefficient derived from transient pressure data over two different strokes and the detection of the gas temperature. The health monitor determines the gas loss based on the / 16 gas pressure in a selected course, the detection of the gas temperature and an expected gas pressure value in the selected course.
[0050] The system of the previous paragraph can optionally include, additionally and / or alternatively, any one or more of the following characteristics, configurations and / or additional components:
[0051] The digital processor also includes a data recorder that records the outputs of the health monitor for diagnostic and prognostic purposes. [0052] The digital processor includes a counter that prevents the landing detector from receiving new matrix data for a period of time after a landing event.
[0053] The landing detector determines the occurrence of a landing event based on maximum and minimum stroke data in the data matrix.
[0054] The health monitor provides an indication that the damper needs to be serviced for oil and gas if the oil loss exceeds an oil loss threshold.
[0055] The health monitor determines the loss of gas if the loss of oil is within an acceptable range.
[0056] The health monitor provides an indication that the damper needs to be serviced for gas if the gas loss exceeds a gas loss threshold.
[0057] While the invention is described with reference to exemplary modalities, it will be understood by those skilled in the art that various changes can be made and equivalents can be replaced by elements thereof without departing from the scope of the invention. In addition, many modifications can be made to adapt a specific situation or material to the teachings of the invention without departing from its essential scope. Therefore, it is intended that the invention is not limited to the particular disclosed modality, but that the invention will include all embodiments falling within the scope of the added claims.

权利要求:
Claims (15)
[1]
1. Method for monitoring the condition of a shock absorber, the method characterized by the fact that it comprises:
detect gas temperature, gas pressure and shock stroke during a landing event;
determining the oil loss based on a transient pressure coefficient deviation derived from transient gas pressures in two different strokes of a nominal coefficient value;
determine the gas loss based on the temperature-adjusted transient gas pressure in a selected stroke and a nominal gas pressure value in the selected stroke; and providing an outlet that indicates the need for maintenance of the damper based on oil loss and gas loss.
[2]
2. Method, according to claim 1, characterized by the fact that the detection of gas temperature, gas pressure and stroke comprises:
detection of the shock travel;
detection of gas temperature inside the damper to provide oil and gas temperature values before landing;
detection of a first transient gas pressure of the shock absorber in a first stroke during a landing event; and detecting a second transient gas pressure from the shock in a second stroke during a landing event.
[3]
3. Method, according to claim 2, characterized by the fact that determining the oil loss comprises:
derive a transient pressure coefficient based on the first and second transient gas pressure of the damper;
calculate the volume of oil loss based on a deviation of the transient pressure coefficient from a nominal coefficient value.
2/4
[4]
4. Method, according to claim 3, characterized by the fact that the calculation of the oil loss volume is also based on the thermal expansion or contraction of the oil.
[5]
5. Method, according to claim 4, characterized by the fact that the calculation of the oil loss volume based on the thermal expansion or contraction of the oil is carried out using the gas temperature value before landing.
[6]
6. Method, according to claim 3, characterized by the fact that determining the gas loss comprises:
if the volume of the oil loss is within an acceptable range, adjust the second pressure of the transient gas based on the gas temperature value before landing; and determining the gas loss based on the second adjusted transient gas pressure and second nominal gas pressure value.
[7]
7. Method according to claim 6, characterized by the fact that providing an outlet comprises:
provide an indication that the damper needs to be serviced for oil and gas if the volume of oil loss exceeds an oil loss threshold; and provide an indication that the damper needs to be serviced for gas if the gas loss exceeds a gas loss threshold.
[8]
8. Method according to claim 1, characterized by the fact that providing an outlet comprises:
provide an indication that the damper needs to be serviced based on oil volume loss and gas loss trend data.
[9]
9. Damper condition monitoring system, the system characterized by the fact that it comprises:
3/4 a gas temperature sensor for detecting gas temperature in the shock;
a gas pressure sensor for detecting gas pressure in the shock;
a travel sensor for detecting the travel of the shock absorber; and a digital processor to determine if the shock needs maintenance, the digital processor including:
a recorder that acquires data for detecting gas temperature, gas pressure and stroke from the gas temperature sensor, gas pressure sensor, and stroke sensor over time and stores the data in a data matrix;
a landing detector that determines the occurrence of a landing event based on course data in the data matrix; and a health monitor that determines oil loss and gas loss based on gas temperature, gas pressure and stroke data from data in the data matrix during the landing event; where the health monitor determines oil loss based on a transient pressure coefficient derived from transient pressure data in two different strokes and the gas temperature felt; and determines the gas loss based on the gas pressure in a selected stroke, the gas temperature felt and an expected gas pressure value in the selected stroke.
[10]
10. System, according to claim 9, characterized by the fact that the digital processor still includes:
a data recorder that records the output of the health monitor for diagnostic and prognostic purposes.
[11]
11. System, according to claim 9, characterized by the fact that the digital processor still includes:
a counter that prevents the landing detector from receiving new matrix data for a period of time after a landing event.
4/4
[12]
12. System, according to claim 9, characterized by the fact that the landing detector determines the occurrence of a landing event based on maximum and minimum stroke data in the data matrix.
[13]
13. System according to claim 9, characterized by the fact that the health monitor provides an indication that the damper needs maintenance for oil and gas if the oil loss exceeds an oil loss threshold.
[14]
14. System according to claim 9, characterized by the fact that the health monitor determines the loss of gas if the loss of oil is within an acceptable range.
[15]
15. System according to claim 9, characterized by the fact that the health monitor provides an indication that the damper needs to be serviced for gas if the gas loss exceeds a gas loss threshold.

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---

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---

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---

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---

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---

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---

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---

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---

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---

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---

VanGilder et al.2013|Experimental measurement of server thermal effectiveness for compact transient data center models

---

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---

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---

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---

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---

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---

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---

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---

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---

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---

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同族专利:

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公开号 | 公开日

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---

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---

US20150267769A1|2015-09-24|

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CA2882387C|2021-09-07|

引用文献:

---

公开号 | 申请日 | 公开日 | 申请人 | 专利标题

---

---

US7650210B2|1995-06-07|2010-01-19|Automotive Technologies International, Inc.|Remote vehicle diagnostic management|

---

US6128951A|1997-04-15|2000-10-10|Trinity Airweighs, L.L.C.|Aircraft weight and center of gravity indicator|

---

US6032090A|1997-05-06|2000-02-29|General Electrodynamics Corporation|System and method for on-board determination of aircraft weight and load-related characteristics|

---

WO2004028902A1|2002-09-25|2004-04-08|Goodrich Corporation|Aircraft shock strut having a fluid level monitor|

---

CA2487704A1|2004-11-18|2006-05-18|R. Kyle Schmidt|Method and system for health monitoring of aircraft landing gear|

---

US7274310B1|2005-03-29|2007-09-25|Nance C Kirk|Aircraft landing gear kinetic energy monitor|

---

CA2509742A1|2005-06-10|2006-12-10|Messier-Dowty Inc.|System and method for determining aircraft hard landing events from inertial and aircraft reference frame data|

---

US8528400B2|2005-07-26|2013-09-10|Goodrich Corporation|Aircraft shock strut having a fluid level monitor|

---

US8695764B2|2005-07-26|2014-04-15|Goodrich Corporation|Aircraft shock strut having a fluid level monitor|

---

GB0517351D0|2005-08-24|2005-10-05|Airbus Uk Ltd|Landing load monitor for aircraft landing gear|

---

US20080033607A1|2006-06-01|2008-02-07|Bob Zeliff|Monitoring system for aircraft landing system|

---

MX2009002271A|2006-08-30|2009-07-02|Messier Dowty Inc|Hydraulic/pneumatic charging valve with integrated pressure transducer.|

---

US7716964B2|2007-01-08|2010-05-18|Kulite Semiconductor Products, Inc.|Leak detector for a pressurized cylinder|

---

GB0704878D0|2007-03-14|2007-04-18|Trw Ltd|Aircraft landing gear monitoring apparatus|

---

US8275515B2|2007-12-12|2012-09-25|Honeywell International Inc.|Shock absorber health and condition monitoring device|

---

US8042765B1|2008-05-20|2011-10-25|Nance C Kirk|Aircraft landing gear compression rate monitor|

---

US8903572B1|2009-08-11|2014-12-02|The Boeing Company|Aircraft landing evaluation system|

---

US8712634B2|2010-08-11|2014-04-29|The Boeing Company|System and method to assess and report the health of landing gear related components|

---

US9045237B2|2010-08-31|2015-06-02|C. Kirk Nance|Automated inspection of aircraft landing gear internal fluid levels|

---

US8565968B2|2010-08-31|2013-10-22|C. Kirk Nance|Automated inspection of aircraft landing gear internal fluid levels|

---

US8565965B2|2011-04-01|2013-10-22|C. Kirk Nance|Aircraft landing gear automated inspection for presence of internal oxygen contamination|

---

GB2496426B|2011-11-11|2013-12-25|Messier Dowty Ltd|Gauge|

---

GB201207322D0|2012-04-27|2012-06-13|Airbus Uk Ltd|Measuring the volume of fluid in a pressurised vessel|

---

GB201209490D0|2012-05-29|2012-07-11|Airbus Operations Ltd|Device and method for checking an aircraft landing gear shock absorber|

---

GB201209502D0|2012-05-29|2012-07-11|Airbus Operations Ltd|System, kit and method for indicating the pressure in an aircraft landing gear shock absorber|

---

GB2514336A|2013-05-16|2014-11-26|Airbus Operations Ltd|Suspension strut servicing|

---

EP2921403B1|2014-03-19|2017-03-01|Safran Landing Systems UK Limited|A shock absorber and a method of determining the level of liquid in a shock absorber|

---

US9773357B2|2014-03-21|2017-09-26|Goodrich Corporation|Aircraft landing gear shock strut performance monitoring|GB2496426B|2011-11-11|2013-12-25|Messier Dowty Ltd|Gauge|

---

DE102014104481A1|2014-03-31|2015-10-01|Steinel Normalien Ag|Gas spring|

---

JP6448403B2|2015-02-17|2019-01-09|住友精密工業株式会社|Electric hydraulic actuator system for lifting and lowering aircraft legs|

---

US9915314B2|2015-11-06|2018-03-13|Goodrich Corporation|Shock strut fluid adjustment assisting system|

---

US9856038B2|2015-12-15|2018-01-02|Goodrich Corporation|Servicing assisting system for shock struts with positive dead volume|

---

US10017276B2|2015-12-15|2018-07-10|Goodrich Corporation|Servicing assisting system for shock struts with negative dead volume|

---

BE1023406B1|2016-01-21|2017-03-09|Safran Aero Boosters S.A.|Aircraft turbomachine|

---

US9803576B2|2016-02-16|2017-10-31|Robert Bosch Gmbh|System and method to predict calibration values based on existing calibrations|

---

US10641685B2|2016-08-30|2020-05-05|Goodrich Corporation|Shock strut service monitoring using gas pressure and temperature sensors, combined with physical strut measurement and taking into account gas absorption/desorption in a fluid|

---

US10186093B2|2016-12-16|2019-01-22|Caterpillar Inc.|System and method for monitoring machine hauling conditions at work site and machine including same|

---

US10395445B2|2016-12-16|2019-08-27|Caterpillar Inc.|System and method for monitoring payload distribution and machine including same|

---

US10266256B2|2017-03-24|2019-04-23|Goodrich Corporation|Dual-stage, pressure-activated, mixed fluid gas shock strut servicing monitoring system|

---

US10269189B2|2017-07-05|2019-04-23|Goodrich Corporation|Dual-stage, separated gas/fluid shock strut servicing monitoring system using one pressure/temperature sensor|

---

US10272993B2|2017-07-05|2019-04-30|Goodrich Corporation|Dual-stage, stroke-activated, mixed fluid gas shock strut servicing monitoring system|

---

US10865848B2|2017-07-05|2020-12-15|Goodrich Corporation|Dual-stage, separated gas/fluid shock strut servicing|

---

US10269188B2|2017-07-05|2019-04-23|Goodrich Corporation|Dual-stage, separated gas/fluid shock strut servicing monitoring system using two pressure/temperature sensors|

---

EP3498603B1|2017-12-13|2022-01-26|Safran Landing Systems UK Ltd|Method of servicing an aircraft landing gear shock absorbing strut|

---

KR20210130162A|2019-02-01|2021-10-29|에이스 컨트롤스 인코포레이티드|A system for predicting failure of shock absorbers|

---

US20200249129A1|2019-02-05|2020-08-06|Goodrich Corporation|Shock strut service monitoring using sensors and physical strut measurement|

---

DE102019202332A1|2019-02-21|2020-08-27|Festo Se & Co. Kg|Stop device and method for operating a stop device|

---

FR3093322B1|2019-02-28|2021-07-09|Airbus Helicopters|Motorized landing gear and aircraft|

---

EP3819211A1|2019-11-11|2021-05-12|Safran Landing Systems UK Ltd|Trend monitoring of a shock absorber condition|

法律状态:
2019-01-22| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|

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2019-02-05| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|

---

2020-05-05| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|

优先权:

---

申请号 | 申请日 | 专利标题

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US201461968462P| true| 2014-03-21|2014-03-21|

---

US61/968462|2014-03-21|

---

US14/318,055|US9285007B2|2014-03-21|2014-06-27|Servicing monitoring system for mixed fluid-gas shock struts|

---

US14/318055|2014-06-27|

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