Office Action 2: Notice of Allowance (2025-03-10)

CLAIMS:
AMENDMENTS TO THE CLAIMS:

This listing of claims will replace all prior versions and listings of claims in the application:

1\. (Currently Amended). A method of controlling an aircraft, comprising:receiving, during flight, first sensor data indicating at least one attribute of high voltage wiring of the aircraft;
receiving, during flight, a state of operation of the aircraft;
determining, during flight, a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and
controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.

2\. (Original) The method of claim 1, wherein the at least one attribute comprises at least one of: a temperature of the high voltage wiring, a wing ambient temperature, or a current through the high voltage wiring.

3\. (Original) The method of claim 1, wherein the at least one attribute comprises a temperature of high voltage wiring received from a temperature sensor on the high voltage wiring, and wherein the high voltage wiring is configured to provide power to at least one of: an electric propulsion unit or a battery pack.

4\. (Original) The method of claim 1, wherein the at least one attribute comprises a wing ambient temperature and a current through the high voltage wiring.

5\. (Original) The method of claim 1, wherein the state of operation comprises at least one of a flight phase or an emergency condition status.

6\. (Original) The method of claim 5, wherein the state of operation comprises an emergency condition status indicating whether a battery back is providing backup power.

7\. (Original) The method of claim 1, wherein the state of operation comprises a flight phase comprising at least one of: hover, takeoff, or forward flight.

8\. (Original) The method of claim 1, wherein the state of operation is based on at least one of: airspeed measurements, altitude measurements, ground speed measurements, propeller tilt angle measurements, or GPS measurements.

9\. (Original) The method of The method of wherein the state of operation comprises at least two upcoming flight phases;
and wherein determining the proximity to the temperature limit comprises considering an impact of the at least two upcoming flight phases on the high voltage wiring temperature.

10\. (Original) The method of claim 1, wherein the proximity to the temperature limit is determined based on at least one of a model or a lookup table.

11\. (Original) The method of claim 1, wherein the proximity to the temperature limit is based on a proximity to a curve proportional to (current of the high voltage wiring)^2 \* (a temperature of the high voltage wiring).

12\. (Original) The method of claim 1, wherein the proximity to the temperature limit is determined based on a model or lookup table, and wherein inputs to the model or lookup table comprise: a temperature of the high voltage wiring, a current through the high voltage wiring, and a flight phase of the aircraft.

13\. (Original) The method of claim 1, wherein the proximity to the temperature limit is a time until the high voltage wiring temperature reaches the temperature limit.

14\. (Original) The method of claim 1, wherein determining the proximity to the temperature limit and controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit is performed more than once while the aircraft is in flight.

15\. (Original) The method of claim 1, wherein controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit comprises controlling a plurality of electric propulsion units according to a priority scheme.

16\. (Original) The method of The method of wherein the high voltage wiring is configured to provide power to a first electric propulsion unit; and

wherein controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit comprises reducing a thrust provided by the first electric propulsion unit in comparison to a second electric propulsion unit as the determined proximity to the temperature limit increases.

17\. (Original) The method of claim 1, wherein controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit comprises de-rating a battery state of a battery pack associated with the high voltage wiring and controlling the at least one electric propulsion unit based on the de-rated battery state.

18\. (Original) The method of claim 17, wherein the de-rated battery state is a de-rated state of power of the battery pack associated with the high voltage wiring.

19\. (Currently Amended) The method of claim 1, wherein receiving first sensor data comprises receiving first sensor data for each of a plurality of high voltage wiring sections associated with a plurality of battery packs;wherein determining the proximity to the temperature limit comprises determining a proximity of each high voltage wiring section to a respective temperature limit; and
wherein controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit comprises:
adjusting a battery pack state of each of the plurality of battery packs based on the proximity of its respective high voltage wiring section to the respective temperature limit, and allocating power across a plurality of electric propulsion units based on the adjusted battery pack states.

20\. (Original) The method of claim 19, further comprising: wherein each of the plurality of high voltage wiring sections comprises high voltage wiring feeding an electric propulsion unit.

21\. (Original) The method of claim 1, wherein controlling the at least one electric propulsion unit of the aircraft comprises managing the power draw of the at least one electric propulsion unit to prevent the electric propulsion unit from exceeding the temperature limit based on the determined proximity.

22\. (Original) The method of claim 1, wherein controlling the at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit comprises managing the power draw of each of a plurality of electric propulsion units of the aircraft to prevent each electric propulsion unit from exceeding the temperature limit based on the determined proximity, while maintaining stability of the aircraft.

23\. (Currently Amended) A system for controlling an aircraft comprising at least one processor configured to execute instructions to cause the system to:receive, during flight, first sensor data indicating at least one attribute of high voltage wiring of the aircraft;
receive, during flight, a state of operation of the aircraft;
determine, during flight, a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and
control at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.

24\. (Currently Amended) A computer-readable storage medium storing instructions which, when executed by at least one processor, cause the at least one processor to:receive, during flight, first sensor data indicating at least one attribute of high voltage wiring of \[\[the\]\]an aircraft;
receive, durinq flight, a state of operation of the aircraft;
determine, durinq flight, a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and
control at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.


25\. (Currently Amended) An aircraft comprising:a first sensor;
at least one electric propulsion unit;
high voltage wiring;
at least one processor configured to execute instructions to:receive, during flight, sensor data from the first sensor indicating at least one attribute of the high voltage wiring;
receive, during flight, a state of operation of the aircraft;
determine, during flight, a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and control the at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.

OFFICE ACTION:
DETAILED ACTION
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
Allowable Subject Matter
The following is an examiner’s statement of reasons for allowance:
In regard to the independent claims 1 & 23-25, ANDERSON et al., US 20200225684 A1, teaches PERSISTENT AERIAL COMMUNICATION AND CONTROL SYSTEM, taken either individually or in combination with other prior art of record fails to teach or render obvious “controlling an aircraft to avoid overheating components such as controlling the electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.” as inventive differences emphasized in claims 1 & 23-25.
Claim 1 (with common inventive elements of claims 23-25): “A method /A system of controlling an aircraft, comprising: receiving, during flight, first sensor data indicating at least one attribute of high voltage wiring of the aircraft; receiving, during flight, a state of operation of the aircraft; determining, during flight, a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.”
Further prosecution of the amended claims revealed that some of the claim elements may not have been disclosed by any prior art as a whole. There are some prior art which provides “A motor/battery control of an electric aircraft”, with addressing some of the claimed limitations, however, fail to teach or render obvious ALL claim elements, especially “receiving, during flight: “high voltage wiring” data & “a state of operation”  of the aircraft; determining, during flight, a proximity of a temperature of the high voltage wiring” providing either alone or in combination with other prior art of record; in regard to the independent claims 1 & 23-25 limitations.
Therefore, Applicant’s arguments, see Applicant Arguments/Remarks pages 7-12, filed on 02/18/2025, with respect to claims 1-25 have been fully considered and are persuasive;
the objection of claim 19  have been withdrawn.
the rejection of claims 1-25,  under 35 USC § 102 & 103, have been withdrawn.
Some of the closest prior art found on search which all are fail to disclose above limitations;
ANDERSON; Bretton E. et al.	US 20200225684 A1	PERSISTENT AERIAL COMMUNICATION AND CONTROL SYSTEM;
Remarks: Discloses systems and operational methods for powering and controlling flight of an unmanned aerial vehicle. The control station and aerial vehicle include power management systems and control circuits to control takeoff, flight operation and landing of the vehicle. However, fails to disclose the claim elements at steps 1-2 above.
Hirono, Daisuke	US 20040124808 A1	Motor control system;
Remarks: Discloses a motor control system for driving a motor with a PWM control using an electric power converter such as a three-phase inverter, etc. Junction temperature reduction processing is performed to make the junction temperature equal to or less than the temperature limit, whereby the switching elements can effectively be used to their maximum temperature limit, thus expanding the operating range of a motor. However, fails to disclose the claim elements at steps 1-2 above.
Followell; David Allan et al., US 9784638 B1, Method and system for diagnoses and prognoses of low temperature limit control valve;
Remarks: Discloses a method and system for diagnosing and predicting performance below a specified performance level of a low temperature limit valve in an environmental control system (ECS). However, fails to disclose the claim elements at steps 1-2 above.
The Examiner reasoning based on this specific claim limitation clearly present in the allowed claims which is neither taught nor suggested by the prior art as a whole, either alone or in combination.
As a result, claims 1-25 are allowed;
Claims 1 & 23-25 is allowed independent claims.
Claims 2-22 are allowed due to dependencies to the allowed claim 1.
Invention Drawings:
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Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee. Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance”.
Conclusion

APPLICANT REBUTTAL: REMARKS
I.   Status of the Claims
In the Non-Final Office Action dated September 16, 2024 (the "Office Action"),1 the Office:
i.   objected to Claim 19;
ii.  rejected Claims 1-10 and 12-25 under 35 U.S.C. §§ 102(a)(1) and
102(a)(2) as allegedly being anticipated by Anderson et al. (US
2020/0225684) ("Anderson et al.");
iii.  rejected Claim 11 under 35 U.S.C. § 103 as allegedly being obvious over
Anderson et al. in view of Hirono (US 2004/0124808) ("Hirono").
By this response, Applicant amends claims 1, 19, and 23-25. The amendments are supported by at least the originally filed claims, specification paragraphs %% [010]- [011] and [033]-[039], and Figs. 4A-5D. No new matter has been introduced. Upon entry of the amendments, claims 1-25 will be pending and under examination, of which claims
1 and 23-25 are independent. In view of the amendments and the following remarks, Applicant respectfully requests withdrawal of the rejections. II.  Summary of Interviews
Applicant thanks Examiner Coduroglu for the courtesies extended during the telephonic interview on January 29, 2025. During the interview, Applicant's representative, Annmarie Dressler (80,028), discussed the rejections under 35 U.S.C. § 102 with the Examiner. Applicant's representative explained the differences between the prior art and the claim language and the Examiner listened to the arguments
reflecting characterizations of the related art and the claims.
is identified herein, Applicant declines to automatically
tion in the Office Action.
detailing the differences. Applicant's representative and the Examiner then discussed potential amendments that would further distinguish over the prior art, including a clarification that the claimed steps are performed "during flight". The Examiner agreed that the discussed claim language would overcome the cited prior art.
Applicant appreciates the Examiner's discussion during the interview. The above amendments and the following remarks are consistent with that discussion. III.  Claim Objections
The Office objected to claim 19 for including two instances of "wherein". The claim language has been amended to delete one instance of the word. Therefore, Applicant respectfully requests that the Examiner withdraw the objection. IV.  Rejection Under 35 U.S.C. § 102
The Office rejected claims 1-10 and 12-25 under 35 U.S.C. § 102 as allegedly anticipated by Anderson et al. Office Action, 2. Applicant respectfully traverses the rejection.
"A claim is anticipated only if each and every element as set forth in the claim is found, either expressly or inherently described, in a single prior art reference." MPEP § 2131 (quoting Verdegaal Bros. v. Union Oil Co. of California, 814 F.2d 628, 631 (Fed. Cir. 1987)) (internal quotations omitted). Furthermore, "[t]he identical invention must be shown in as complete detail as is contained in the . . . claim." See id. (quoting Richardson v. Suzuki Motor Co., 868 F.2d 1226, 1236 (Fed. Cir. 1989)). However, Anderson et al. fails to teach Applicant's claim 1 and 23-25. Nevertheless, solely to advance prosecution and without acquiescing to the rejection, Applicant amends claims
1 and 23-25 to further distinguish them from Anderson et al.
Applicant submits that Anderson et al. does not teach each element of the
subject matter recited by the unamended pending claims. For example, claim 1 recites "receiving first sensor data indicating at least one attribute of high voltage wiring of the aircraft." The Office asserts that Anderson et al. teaches this subject matter, citing Anderson et al. at paragraph [0271], which describes that "[a] triplexer also routes data from the vehicle to the control station including sensor data, payload data and telemetry from the aerial vehicle to the control station." Office Action pgs. 3-4. Anderson et al., however, does not disclose that its "sensor data, payload data and telemetry" "indicat[es] at least one attribute of high voltage wiring of the aircraft," as recited by claim 1 (emphasis added). Claim 1 is therefore distinct from Anderson et al. for this first reason.
Additionally, claim 1 recites "determine ... a proximity of a temperature of the
high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft." The Office asserts that Anderson et al. teaches this subject matter, citing Anderson et al. at paragraphs [0175], [0177], and [0178]. Office Action pg.
4. However, these paragraphs of Anderson et al. are directed to testing a cooling system for a HiPer spooler. Paragraphs [0173]-[0178] detail procedures for "experimental tests" and paragraph [0178] ultimately concludes that "the cooling appeared to be adequate in the flat spool design." There is no determination of "a proximity of a temperature of the high voltage wiring to a temperature limit," let alone a determination of this proximity being "based on the first sensor data and the state of operation of the aircraft." Additionally, even if the testing procedures in Anderson et al. disclosed determining a proximity, which Applicant does not concede, there is no
indication that the proximity is used, as recited in the claims, for "controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity" (emphasis added).
Solely to advance prosecution and without agreeing or acquiescing to any
position taken in the Office Action, Applicant has amended the claim language to state that the receiving and determining steps are performed "during flight", as discussed in the Examiner interview. In Anderson et al. there is no indication that the proximity is determined "during flight" or based on first sensor data and a state of operation of the aircraft received "during flight". In fact, Anderson et al. describes "experimental tests" (Anderson et al. at   [0175]) in a lab setting, as depicted in Fig. 13E and throughout the reference.
In view of the above, Anderson et al. fails to teach the subject matter of amended claim 1. Accordingly, claim 1 is allowable over Anderson et al. Independent claims 23-25, although different in scope from claim 1, recite similar subject matter, so they are also allowable for at least the same reasons. Claims 2-22 each depend from claim 1 and are allowable over the cited references by at least virtue of their respective dependencies. These claims also recite additional elements distinguishing them over the art of record.
For at least these reasons, Applicant respectfully requests that the Examiner
withdraw the rejections of claims 1-10 and 12-25 under 35 U.S.C. § 102 and allow the claims.
V.   Rejections Under 35 U.S.C. § 103
Applicant respectfully traverses the rejections of claim 11 under 35 U.S.C. § 103 as allegedly unpatentable over the asserted combination of Anderson et al. and Hirono. Office Action at pgs. 19-21. No prima facie case of obviousness has been established for at least the reason that the Office Action has neither properly determined the scope and content of the prior art nor properly ascertained the differences between the prior art and the claimed combinations.
The Office cited Anderson et al. in the rejection of claim 11. This claim depends from claim 1 which, as noted above, has been amended with subject matter that Anderson et al. fails to disclose. Hirono fails to cure the above-noted deficiencies of Anderson et al. Accordingly, claim 11 is allowable over the cited references by at least virtue of its dependence.
For at least these reasons, Applicant respectfully requests that the Examiner withdraw the rejection of claims 11 under 35 U.S.C. § 103 and allow the claim. VI.  Conclusion


CITED REFERENCE SUMMARIES: Ref US6106966A: Claims:
A device for solid-oxide electrolytic-cell and fuel-cell applications comprising the following components: a single-crystal solid-oxide component having a first surface facing a first enclosure and a second surface facing a second enclosure; electrode material applied to each of said first and second surfaces; electrical connections to each of said surfaces to establish an electrical potential across the surfaces when the device is used as an electrolytic cell or produce an electrical potential across the surfaces when the device is used as a fuel cell; and inlet and outlet ports connected to said first and second enclosures to provide feed gas and exhaust product gas from the device.
a single-crystal solid-oxide component having a first surface facing a first enclosure and a second surface facing a second enclosure;
electrode material applied to each of said first and second surfaces;
electrical connections to each of said surfaces to establish an electrical potential across the surfaces when the device is used as an electrolytic cell or produce an electrical potential across the surfaces when the device is used as a fuel cell; and
inlet and outlet ports connected to said first and second enclosures to provide feed gas and exhaust product gas from the device.
The device of claim 1, wherein said solid-oxide component consists of stabilized zirconia.
The device of claim 1, wherein said electrode material consists of platinum.
The device of claim 1, wherein said solid-oxide component consists of stabilized zirconia and said electrode material consists of platinum.
The device of claim 1, further comprising a heater adapted to maintain said single-crystal solid-oxide component and said first and second enclosures substantially at a predetermined temperature.
A multilayered device for solid-oxide electrolytic-cell and fuel-cell applications comprising: (a) a plurality of axially stacked cells, each cell comprising a first grille defining a first peripheral enclosure; a second grille defining a second peripheral enclosure; a single-crystal solid-oxide component having a first surface facing said first grille and a second surface facing said second grille, said solid-oxide component being adapted to mate the first surface with said first grille and the second surface with said second grille to form sealed connections; electrode material applied to each of said first and second surfaces of the solid-oxide component; and electrical connections to said first and second surfaces of the solid-oxide component to establish an electrical potential across the surfaces when the device is used as an electrolytic cell or produce an electrical potential across the surfaces when the device is used as a fuel cell; (b) diaphragm means for connecting pairs of said cells in sealed pile arrangement to form a stack of cells; (c) a first end plate adapted to mate with said first grille, such as to seal a first end of said stack of cells; (d) a second end plate adapted to mate with said second grille, such as to seal a second end of said stack of cells; and (e) inlet and outlet ports connected to said first and second grilles to provide feed gas to the device and exhaust product gas from the device.
(a) a plurality of axially stacked cells, each cell comprising
a first grille defining a first peripheral enclosure; a second grille defining a second peripheral enclosure;
a single-crystal solid-oxide component having a first surface facing said first grille and a second surface facing said second grille, said solid-oxide component being adapted to mate the first surface with said first grille and the second surface with said second grille to form sealed connections;
electrode material applied to each of said first and second surfaces of the solid-oxide component; and
electrical connections to said first and second surfaces of the solid-oxide component to establish an electrical potential across the surfaces when the device is used as an electrolytic cell or produce an electrical potential across the surfaces when the device is used as a fuel cell; (b) diaphragm means for connecting pairs of said cells in sealed pile arrangement to form a stack of cells; (c) a first end plate adapted to mate with said first grille, such as to seal a first end of said stack of cells; (d) a second end plate adapted to mate with said second grille, such as to seal a second end of said stack of cells; and (e) inlet and outlet ports connected to said first and second grilles to provide feed gas to the device and exhaust product gas from the device.
(b) diaphragm means for connecting pairs of said cells in sealed pile arrangement to form a stack of cells;
(c) a first end plate adapted to mate with said first grille, such as to seal a first end of said stack of cells;
(d) a second end plate adapted to mate with said second grille, such as to seal a second end of said stack of cells; and
(e) inlet and outlet ports connected to said first and second grilles to provide feed gas to the device and exhaust product gas from the device.
The device of claim 6, wherein said single-crystal solid-oxide component consists of stabilized zirconia.
The device of claim 6, wherein said electrode material consists of platinum.
The device of claim 6, wherein said first and second grilles, said diaphragm means, and said first and second end plates are made of platinum.
The device of claim 6, wherein said solid-oxide component consists of stabilized zirconia, said electrode material consists of platinum, and said first and second grilles, said diaphragm means, and said first and second end plates are made of platinum.
The device of claim 6, wherein said inlet and outlet ports include manifolds connecting all cells through perforations in said first and second grilles, said single-crystal solid-oxide components, and said diaphragm means.
The device of claim 6, wherein said first and second grilles comprise flow channels to control fluid flow within the grilles.
The device of claim 10, wherein said inlet and outlet ports include manifolds connecting all cells through perforations in said first and second grilles, said single-crystal solid-oxide components, and said diaphragm means.
The device of claim 13, wherein said first and second grilles comprise flow channels to control fluid flow within the grilles.
Ref US6314790B1: Claims:
An oxygen concentration detecting apparatus comprising:
a limit current type oxygen sensor provided in an exhaust system of an internal combustion engine, said sensor having an oxygen concentration detecting element for outputting a limit current proportional to oxygen concentration, and a heater for heating said detecting element;
heater control means for controlling energization of said heater to activate said oxygen sensor;
fuel varying means for varying fuel supply to said internal combustion engine; and
sensor diagnostic means for performing diagnosis of said oxygen sensor in accordance with a change in an output value from said oxygen sensor, said change being caused when said fuel supply is varied by said fuel varying means.
An oxygen concentration detecting apparatus according to claim 1 , wherein said predetermined range, used by said sensor diagnostic means to perform said diag nosis of said oxygen sensor, is set in accordance with a variation in said fuel supply cau sed by said fuel varying means.
An oxygen concentration detecting apparatus according to claim 1 , wherein said heater control means controls an amount of energization of said heater in accordance with operating conditions of said internal combustion engine.
An oxygen concentration detecting apparatus according to claim 3 , wherein said operating conditions of said internal combustion engine include load and speed.
An oxygen concentration detecting apparatus according to claim 1 , further comprising:
heater power supply estimating means for estimating an accumulation of heater power supply from starting of energization of said heater;
wherein said sensor diagnostic means is for performing said diagnosis of said oxygen sensor if said accumulation of said heater power supply estimated by said heater power supply estimating means is at least a predetermined value.
An oxygen concentration detecting apparatus according to claim 5 , wherein said heater power supply estimating means estimates said accumulation of said heater power supply based on an elapsed time following starting of said internal combustion engine.
An oxygen concentration detecting apparatus according to claim 1 , wherein said diagnosis is performed in accordance with whether said change in said output value falls in a predetermined range.
An oxygen concentration detecting apparatus according to claim 1 , wherein:
said output value from said oxygen sensor increases with a slope as a voltage applied to said oxygen sensor increases, and becomes constant when said output value corresponds to said limit current; and
said slope changes in accordance with a temperature such that a first slope at a first temperature is larger than a second slope at a second temperature lower than said first temperature.
An oxygen concentration detecting apparatus according to claim 1 , wherein when said change in said output value is smaller than a first magnitude, said sensor diagnostic means determines that an abnormality has occurred because the temperature of said oxygen sensor is low.
An oxygen concentration detecting apparatus according to claim 9 , wherein when said change in said output value is larger than a second magnitude, said sensor diagnostic means determines that an abnormality has occurred because the mperature of said oxygen sensor is high.
Ref US20040124808A1: Claims:
A motor control system for driving a motor with a PWM control using an electric power converter such as a three-phase inverter, etc., comprising: junction temperature calculating means for calculating a junction temperature of a switching element of the electric power converter; and junction temperature reducing means for comparing the junction temperature calculated by the junction temperature calculating means with a preset temperature limit and for performing junction temperature reduction processing to make the junction temperature equal to or less than the temperature limit when the junction temperature exceeds the temperature limit.
junction temperature calculating means for calculating a junction temperature of a switching element of the electric power converter; and
junction temperature reducing means for comparing the junction temperature calculated by the junction temperature calculating means with a preset temperature limit and for performing junction temperature reduction processing to make the junction temperature equal to or less than the temperature limit when the junction temperature exceeds the temperature limit.
A motor control system for driving a motor with a PWM control using an electric power converter such as a three-phase inverter, etc., comprising: loss calculating means for calculating a loss of a switching element of the electric power converter; and loss reducing means for comparing the loss calculated by the loss calculating means with a preset loss limit and for performing loss reduction processing to make the loss equal to or less than the loss limit when the loss exceeds the loss limit.
loss calculating means for calculating a loss of a switching element of the electric power converter; and
loss reducing means for comparing the loss calculated by the loss calculating means with a preset loss limit and for performing loss reduction processing to make the loss equal to or less than the loss limit when the loss exceeds the loss limit.
A motor control system for driving a motor with a PWM control using an electric power converter such as a three-phase inverter, etc., comprising: temperature detecting means for detecting a temperature of a switching element of the electric power converter; junction temperature calculating means for calculating a junction temperature of the switching element of the electric power converter when the temperature detected by the temperature detecting means is between a maximum temperature limit of the switching element and a predetermined temperature which is lower than the maximum temperature limit; junction temperature reducing means for comparing the junction temperature calculated by the junction temperature calculating means with a preset temperature limit when the temperature detected by the temperature detecting means is between the maximum temperature limit of the switching element and the predetermined temperature which is lower than the maximum temperature limit and for performing junction temperature reduction processing when the junction temperature exceeds the temperature limit; loss calculating means for calculating a loss of the switching element of the electric power converter when the temperature detected by the temperature detecting means is equal to or less than the predetermined temperature; and loss reducing means for comparing the loss calculated by the loss calculating means with a preset loss limit when the temperature detected by the temperature detecting means is equal to or less than the predetermined temperature and for performing loss reduction processing to make the loss equal to or less than the loss limit when the loss exceeds the loss limit.
temperature detecting means for detecting a temperature of a switching element of the electric power converter;
junction temperature calculating means for calculating a junction temperature of the switching element of the electric power converter when the temperature detected by the temperature detecting means is between a maximum temperature limit of the switching element and a predetermined temperature which is lower than the maximum temperature limit;
junction temperature reducing means for comparing the junction temperature calculated by the junction temperature calculating means with a preset temperature limit when the temperature detected by the temperature detecting means is between the maximum temperature limit of the switching element and the predetermined temperature which is lower than the maximum temperature limit and for performing junction temperature reduction processing when the junction temperature exceeds the temperature limit;
loss calculating means for calculating a loss of the switching element of the electric power converter when the temperature detected by the temperature detecting means is equal to or less than the predetermined temperature; and
loss reducing means for comparing the loss calculated by the loss calculating means with a preset loss limit when the temperature detected by the temperature detecting means is equal to or less than the predetermined temperature and for performing loss reduction processing to make the loss equal to or less than the loss limit when the loss exceeds the loss limit.
A motor control system for driving a motor with a PWM control using an electric power converter such as a three-phase inverter, etc., comprising: loss calculating means for calculating a loss of a switching element of the electric power converter; junction temperature calculating means for calculating a junction temperature of the switching element of the electric power converter; loss reducing means for comparing the loss calculated by the loss calculating means with a preset loss limit and for performing loss reduction processing to make the loss equal to or less than the loss limit when the loss exceeds the loss limit; and junction temperature reducing means for comparing, when it is determined by said comparison that the loss is equal to or less than the loss limit or when the loss becomes equal to or less than the loss limit by the loss reduction processing, the junction temperature calculated by the junction temperature calculating means with a preset temperature limit and for performing junction temperature reduction processing to make the junction temperature equal to or less than the temperature limit when the junction temperature exceeds the temperature limit.
loss calculating means for calculating a loss of a switching element of the electric power converter;
junction temperature calculating means for calculating a junction temperature of the switching element of the electric power converter;
loss reducing means for comparing the loss calculated by the loss calculating means with a preset loss limit and for performing loss reduction processing to make the loss equal to or less than the loss limit when the loss exceeds the loss limit; and
junction temperature reducing means for comparing, when it is determined by said comparison that the loss is equal to or less than the loss limit or when the loss becomes equal to or less than the loss limit by the loss reduction processing, the junction temperature calculated by the junction temperature calculating means with a preset temperature limit and for performing junction temperature reduction processing to make the junction temperature equal to or less than the temperature limit when the junction temperature exceeds the temperature limit.
The motor control system according to claim 1 , 3 or 4 , wherein said junction temperature reducing means carries out the junction temperature reduction processing by means of at least one of a method for reducing a number of switchings per unit time and a method for reducing an electric current flowing through the switching element.
The motor control system according to claim 2 , 3 or 4 , wherein said loss reducing means carries out the loss reduction processing by means of at least one of a method for reducing a number of switchings per unit time and a method for reducing an electric current flowing through the switching element.
The motor control system according to claim 5 , wherein the number of switchings is reduced by lowering a frequency of a base carrier used for generation of a PWM signal.
The motor control system according to claim 6 , wherein the number of switchings is reduced by lowering a frequency of a base carrier used for generation of a PWM signal.
The motor control system according to claim 5 , wherein the electric current is reduced by decreasing a duty cycle of a PWM signal.
The motor control system according to claim 6 , wherein the electric current is reduced by decreasing a duty cycle of a PWM signal.
Ref US9784638B1: Claims:
A method, comprising: during operation of an environmental control system (ECS) for a vehicle, sensing current operation parameters related to the ECS; retrieving historical operation parameters related to the ECS; and determining a probability of below-specified performance of a low temperature limit valve of the ECS, based on a predetermined relationship between the sensed current operation parameters and the probability of below-specified performance, wherein the predetermined relationship is based on the current operation parameters, the historical operation parameters, and the probability of below-specified performance of the low temperature limit valve.
during operation of an environmental control system (ECS) for a vehicle, sensing current operation parameters related to the ECS;
retrieving historical operation parameters related to the ECS; and
determining a probability of below-specified performance of a low temperature limit valve of the ECS, based on a predetermined relationship between the sensed current operation parameters and the probability of below-specified performance, wherein the predetermined relationship is based on the current operation parameters, the historical operation parameters, and the probability of below-specified performance of the low temperature limit valve.
The method of claim 1 , further comprising: calculating the predetermined relationship between the sensed current operation parameters, the historical operation parameters, and 
[Truncated to input limit]