CN113864508A - Electric mechanism for aviation fuel valve - Google Patents
Electric mechanism for aviation fuel valve Download PDFInfo
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- CN113864508A CN113864508A CN202110980910.0A CN202110980910A CN113864508A CN 113864508 A CN113864508 A CN 113864508A CN 202110980910 A CN202110980910 A CN 202110980910A CN 113864508 A CN113864508 A CN 113864508A
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- aviation fuel
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- 230000007246 mechanism Effects 0.000 title claims abstract description 65
- 239000000446 fuel Substances 0.000 title claims abstract description 37
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 40
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 22
- 239000010959 steel Substances 0.000 claims abstract description 22
- 238000001514 detection method Methods 0.000 claims description 8
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- 239000003990 capacitor Substances 0.000 claims description 6
- 230000004907 flux Effects 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 4
- 230000005355 Hall effect Effects 0.000 claims description 3
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- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 230000004927 fusion Effects 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 claims description 2
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- 230000005540 biological transmission Effects 0.000 description 4
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- 230000007774 longterm Effects 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- 230000005855 radiation Effects 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
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- 230000002035 prolonged effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K31/00—Actuating devices; Operating means; Releasing devices
- F16K31/02—Actuating devices; Operating means; Releasing devices electric; magnetic
- F16K31/04—Actuating devices; Operating means; Releasing devices electric; magnetic using a motor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K37/00—Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Electrically Driven Valve-Operating Means (AREA)
Abstract
The invention provides an electric mechanism for an aviation fuel valve, which belongs to the technical field of valve adjustment control and comprises a motor, a shell, a speed reducer, magnetic steel, a pointer, a Hall sensor, a relay and an electric connector, wherein the motor is connected with the shell; the output end of the motor is connected with the speed reducer, the pointer and the output end of the speed reducer are coaxially fixed, the magnetic steel and the pointer are fixedly connected and coaxially rotate, the Hall sensor is arranged along the motion track of the pointer, and the electric connector is connected with the power supply, a superior system of the host and the relay; after receiving the designated position signal of a superior system, the electric mechanism for the aviation fuel valve judges the current shaft locking position of the output shaft according to the position signal combination of the Hall sensors at different positions, further judges the current switch position of the ball valve assembly, judges the rotation direction of the motor after comparing with the given position, and realizes the reversing operation of the motor through the relay. Compared with the prior art, the invention has high reliability and strong anti-interference capability, and meets the requirements of aviation product reliability and long endurance.
Description
Technical Field
The invention relates to the technical field of valve adjustment control, in particular to an electric mechanism for an aviation fuel valve.
Background
The fuel valve is widely applied to the aerospace field, and the fuel valve is widely applied by taking an electric mechanism as a match of an aviation system product. The requirement of the aviation field on an airborne equipment system is different from aerospace, and the requirement of the aviation field on the airborne equipment system is taken as an example, the requirement of the aviation field on the life of a product is far higher than that of an aerospace product, the reliability requirement is extremely high, and the product design is required to meet the requirements of high reliability, long endurance, light weight and the like of an aviation product.
The existing fuel valve electric mechanism adopts a large number of electronic components to realize detection and control requirements, has high requirements on system temperature control, weak anti-interference capability, and is respectively used for detection and control, the control precision can still meet the requirements, but the reliability and the service life are limited, and the requirements of aviation products on reliability and higher requirements in long-term aviation can not be met, so that the improvement is necessary.
Disclosure of Invention
The invention provides an electric mechanism for an aviation fuel valve, and aims to solve the problem that the prior art cannot meet the requirements of aviation product reliability and long endurance.
The purpose of the invention is realized by the following technical scheme:
an electric mechanism for an aviation fuel valve comprises a motor, a shell, a speed reducer, magnetic steel, a pointer, a Hall sensor, a relay and an electric connector; the output end of the motor is connected with the speed reducer, the magnetic steel, the pointer and the Hall sensor are arranged in the shell, the magnetic steel and the output end of the speed reducer are coaxially fixed, the pointer and the magnetic steel are fixedly connected and coaxially rotate, the Hall sensor is arranged along the motion track of the pointer, and the electric connector is connected with the power supply, the upper-level system of the host and the filter; an output shaft of the electric mechanism for the aviation fuel valve is connected with a valve core of a ball valve assembly of the fuel valve on-off system, and the output shaft is vertical to a channel of a pipeline where the ball valve assembly is located; after receiving the designated position signal of a superior system, the electric mechanism for the aviation fuel valve judges the current shaft locking position of the output shaft according to the position signal combination of the Hall sensors at different positions, further judges the current switch position of the ball valve assembly, judges the rotation direction of the motor after comparing with the given position, and realizes the reversing operation of the motor through the relay.
Furthermore, the electric mechanism for the aviation fuel valve adopts non-contact position detection, double-position accurate detection is realized by detecting magnetic flux, the pointer is fixed on an output shaft of a motor rotor reducer, magnetic steel is embedded in the inner side of the pointer, Hall position sensors are respectively arranged at opening and closing positions, and after the pointer is in place, the magnetic steel triggers a sensing point in the sensor due to the Hall effect, outputs a place signal and cuts off a motor power supply.
Further, the electric mechanism adopts a controller-free brush direct current motor.
Furthermore, the electric mechanism adopts a brush direct current motor with a brake, the motor comprises the brake and a motor body, the motor body and the brake share a power supply, and the brake is arranged at the tail part of the motor.
Furthermore, the brake adopts a power-off brake, the motor shaft is in a locked state by means of spring force under the condition of no power-on, the motor shaft is in an unlocked state by means of electromagnetic force under the condition of power-on, and the lock shaft is fixed after power-off in place; when the motor body is electrified and works, the brake is unlocked, the brake loses the braking effect, and the motor works normally; when the motor body is powered off, the brake is locked to lock the motor body and the motor body does not work.
Further, the speed reducer is a two-stage speed reducer and comprises a first-stage harmonic speed reducer and a first-stage gear speed reducer.
Furthermore, the relay is sealed by laser fusion welding and is provided with two groups of switching contacts, and the contact type is a dynamic break contact.
Furthermore, the electric mechanism for the aviation fuel valve further comprises a filter, wherein the filter adopts a differential mode inductor and an X, Y capacitor, and the filtering is realized through the combination of components.
Furthermore, the signal filtering of the filter circuit adopts high-frequency magnetic beads and grounding capacitors.
Further, the shell is sealed to the outside, and the shell of the shell is coated with an anticorrosive coating.
The beneficial technical effects obtained by the invention are as follows:
the controller-free electromechanical system design is adopted, so that the use of electronic components is reduced to the maximum extent, and the temperature requirement of the system is met; the sensor adopts a high-precision non-contact type double-output Hall sensor, has rapid response, strong anti-interference capability and high control precision, and simultaneously realizes position information feedback and controls the starting and stopping of the motor; the motor is started and stopped in a double control mode, an output shaft feeds back an in-place signal after in-place, a host can control the action condition of the mechanism, the mechanism can lock the shaft after in-place power failure, and the normal action of the valve body is ensured; the relay is adopted for reversing, the rotating direction of the motor is changed according to the requirement of the host, and the on-off of the valve body is further controlled.
Compared with the prior art, the technical scheme provided by the invention has the advantages of high reliability and strong anti-interference capability, reduces the difficulty of system temperature control, solves the problems in the prior art, and has outstanding substantive characteristics and remarkable progress.
Drawings
FIG. 1 is a functional block diagram of an electric machine in accordance with one embodiment of the present invention;
FIG. 2 is an electrical schematic of one embodiment of the present invention;
fig. 3 is a schematic structural diagram of an electric mechanism according to an embodiment of the present invention.
Detailed Description
The technical solution of the present invention will be further described in detail with reference to the accompanying drawings and the detailed description. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the invention without making creative efforts, shall fall within the scope of the claimed invention.
A specific embodiment of an electric mechanism for an aviation fuel valve adopts a controller-free brush direct current motor electric mechanism, and comprises a brush direct current motor with a brake, a two-stage speed reducer, a Hall sensor, a relay, a filter and an electric connector. The brush DC motor electric mechanism without the controller has the advantages of high control precision, light weight, small volume, high integration degree, safety and reliability. The main performance technical indexes of the brush direct current motor electric mechanism without the controller in the embodiment are shown in the table 1.
TABLE 1 technical indices of electric mechanism
In the embodiment, the electric mechanism for the fuel on-off valve is driven by a controller-free brushed direct current motor, is connected with an output shaft for transmission through a two-stage speed reducer and outputs torque, and the two-stage speed reducer comprises a first-stage harmonic speed reducer and a first-stage gear speed reducer. And feeding back a position signal through the Hall sensor at the current position at different working positions and realizing the in-place power-off of the motor. The motor is prevented from being started in an accidental situation through a brake, the brake is arranged at the tail of the motor, the motor shaft is in a locked state through spring force under the condition of no power supply, the motor shaft is in an unlocked state through electromagnetic force under the condition of power supply, and the lock shaft is fixed after power supply is in place and power off.
As shown in fig. 1, the superior system controls the ball valve assembly through an electric mechanism that includes a filter assembly, a hall sensor, a relay, a motor, a reducer assembly, a pointer, and magnetic steel. The superior system sends a valve on-off instruction, the Hall sensor detects the current position, if the current position is consistent with the instruction, the motor is not moved, and the Hall sensor feeds a current position signal back to the superior system; if the current position is inconsistent with the instruction, the rotating direction of the motor is judged through the Hall sensor, the motor rotates according to the instruction, after the motor reaches the instruction position, the brake locks the shaft, and the Hall sensor feeds back the current position information to a superior system.
The electric mechanism realizes the reversing operation of the motor through the relay, and after the electric mechanism receives the appointed position signal of the superior system, the current shaft locking position of the output shaft is judged according to the position signal combination of the Hall sensors at different positions, so that the current switch position of the valve body is judged, and the rotation direction of the motor is judged after the current switch position is compared with the given position.
In the embodiment, the mechanism has quick response and quick motor starting, and can realize the switching between the on position and the off position (namely the on-off of the fuel valve) within 1S. The motor is rotated forward and backward through the relay, the power-off shaft is locked when the motor reaches a specified position, and a current position signal is fed back to the host. The electric mechanism is connected with a valve core of the ball valve assembly through an output shaft, and the output shaft is vertical to a channel of a pipeline where the ball valve assembly is located.
When the airplane has special flight requirements, the on-off of the fuel valve is adjusted through the output shaft switch of the flow distribution electric mechanism, so that the pipeline fuel can be quickly, accurately and reliably cut off, and the flight safety is guaranteed. The electric mechanism receives the action instruction of the host, reaches the fixed position of the output shaft of the electric mechanism according to the instruction requirement, locks the shaft, simultaneously drives the valve body of the fuel ball valve to realize the in-place of the specified position through the transmission mechanism, and feeds the in-place signal back to the host to participate in the whole flight control system.
As shown in fig. 2, the filter assembly comprises two parts, namely an electric connector and a filter, wherein the electric connector and the filter are connected through screws, the socket comprises 6 pins which are respectively 28V on, 28V off, on position, off position, power ground and signal ground, the 28V on and 28V off are on-off commands of an upper-level system, and the on position and the off position are current position information fed back by the hall sensor. Two hall switches of hall sensor inside mutually perpendicular's position integration, be switch 1 and switch 2 respectively, the magnet steel is through gluing in the embedding pointer, it is rotatory along with the output shaft together with the pointer, current position information is judged through the change of response magnet steel magnetic flux to switch 1 and switch 2, generate control signal, the relay passes through the fix with screw on the casing, position signal through receiving hall sensor judges the contact and switches the combination, thereby change motor current direction, realize the positive and negative direction rotation of motor.
When the pin B is connected with the power supply, the motor power supply in the Hall sensor switch 2 at the position shown in figure 2 is connected, the current drives the motor to rotate forwards (the forward rotation direction can be defined according to the product requirement, the performance is not influenced) through the relay, the output shaft of the product is driven to rotate forwards through the two-stage speed reducer, when the Hall sensor switch 2 rotates to the appointed 'on' position, the motor power supply in the Hall sensor switch 2 is disconnected through the electromagnetic effect, the output shaft locks the shaft, and the pin D and the pin F output 'on' position signals. When the C contact pin is connected with the power supply, the Hall sensor switch 1 is connected with the power supply of the motor, the current drives the motor to rotate reversely through the relay, the output shaft of the product is driven to rotate reversely through the speed reducer, when the output shaft rotates to the 'off' position, the Hall sensor switch 1 is disconnected with the power supply of the motor, the feedback signal is connected, and the E contact pin and the F contact pin output 'off' position signals. The filter in the circuit is used for preventing electromagnetic interference generated by residual electromotive force when the motor is reversed in the circuit switching process, and the electromagnetic compatibility of the system is improved.
As shown in fig. 3, the electromechanical mechanism system in this embodiment includes a brushed dc motor with a brake, a housing, a two-stage reducer, magnetic steel, a pointer, a hall sensor, a relay, a filter, and an electrical connector. The brush direct current motor is connected to the two-stage speed reducer through the brake, the two-stage speed reducer, the magnetic steel, the pointer and the Hall sensor are arranged in the shell, the magnetic steel is coaxially fixed with an output shaft of the speed reducer, the pointer and the magnetic steel are connected, fixed and coaxially rotated, and the Hall sensor is arranged along the motion track of the pointer.
The electric connector and the filter are integrally designed, are connected with the mechanism body in a direct-insertion mode, conduct interference test is conducted on interference signals on a 28V power line, and filtering from 100kHz to 1GHz needs to be considered for electromagnetic interference generated by the motor. Because the factors such as withstand voltage, inductance and capacitance of components are comprehensively considered, the components mainly adopted by the filter circuit are a differential mode inductor and an X, Y capacitor, and filtering is realized by combining the components. For signal filtering, because the signal line is affected by power line coupling and space radiation, and the main interference is higher harmonic coupling, etc., the filter circuit in this embodiment can effectively suppress electromagnetic interference coupled on the signal line and prevent radiation emission from exceeding the standard by adopting high frequency magnetic beads and grounded capacitors.
In the embodiment, non-contact position detection is adopted, double-position accurate detection is realized by detecting magnetic flux, a reluctance type Hall position sensor is a key component of an electric mechanism, a pointer for detecting the position is fixed on an output shaft of a motor rotor reducer, magnetic steel is embedded in the inner side of the pointer, the Hall position sensors are respectively arranged at opening and closing positions, when the pointer is in place, the magnetic steel triggers a sensing point in the sensor due to Hall effect, an in-place signal is output, a motor power supply is cut off, and a brake locks a shaft.
In the specific embodiment, the brush direct current motor comprises a brake and a motor body, wherein the motor body and the brake share a power supply, and the brake belongs to a power-off brake, namely when the motor body is electrified and works, the brake is unlocked, the brake loses the braking action, and the motor works normally; when the motor body is powered off, the motor stops working, the brake is locked, and the motor body is locked and does not work.
In the embodiment, the relay is sealed by laser fusion welding and is provided with two groups of switching contacts, the low level of the load current is as low as 3A, the contact is a dynamic-break contact, namely after the relay acts, the contact is broken, a new loop is formed after the contact is broken, the current of the motor is reverse to the original current, and the forward and reverse rotation of the motor is controlled.
In the specific embodiment, one stage of the two-stage speed reducer adopts a gear speed reducer, and the speed reduction ratio is 66 ÷ 19 ═ 3.4; the second stage adopts a harmonic reducer, the model selection reduction ratio is 80, and the total reduction ratio is 3.4 multiplied by 80 to 272.
And (3) performance checking: the rated output calculated output torque of the motor is as follows:
TS＝TN×iZ×η＝0.023×272×45％＝2.8Nm
in the formula, TN-motor rated torque,
eta-the transmission efficiency of the reducer is 45%;
iz-reducer reduction ratio;
calculating rated output speed:
the requirement that the conversion time of the product from an open position (0 ℃) to a closed position (90 ℃) is less than or equal to 1s is met.
The beneficial technical effects obtained by the specific embodiment are as follows:
1. the double-position control of 'on' and 'off' is realized through the non-contact Hall sensor, the Hall realizes the position control through the magnetic flux of the sensing element by induction, no mechanical contact exists, the current position signal is fed back after the Hall is in place, the position precision can reach +/-1 degrees, and the service life of the electric mechanism is effectively prolonged while the precision is ensured.
2. The circuit is optimally designed, the electrical principle is simple, the relay is used for reversing, the number of elements is small, the power supply of the motor is cut off after the motor and other elements are in place, the motor and other elements are in a standby state when not in work, the power-on time of the electrical elements is reduced, the working loss is reduced, and the reliability of the long-term work of the electric mechanism is improved.
3. The electric mechanism is subjected to weight reduction design according to aviation standards, and through structural optimization, speed reducer optimization and material optimization, on the premise of ensuring structural strength and durability, the mechanism is compact in layout and easy to cooperate with aviation fuel pipelines for installation.
4. The design of the direct-insert power filter is used for effectively filtering a switching command and an in-place signal, shielding and protecting a motor, a speed reducer, a brake and the like, electromagnetic leakage is greatly reduced, the whole electric mechanism meets the conduction and radiation requirements under a complex electromagnetic environment, and the electromagnetic compatibility test passes the electromagnetic emission and sensitivity requirements of CE102, RE102 and other tests.
5. And an output end braking mode is adopted. The electric mechanism carries out effective braking from the transmission shaft at the middle end of the speed reducer, and moves the braking point to the output rear end, so that the electric mechanism is compact in structural layout, the mechanical environment adaptability of the electric mechanism is improved, the electric mechanism can adapt to the high-magnitude and long-time vibration environment of airborne equipment, and the maintenance is convenient.
6. The shell of the electric mechanism is sealed to the outside, the electromagnetic compatibility shielding performance is good, the temperature environment range is wide, the mechanical environment adaptability is strong, the structure is compact and the weight is light, the electric mechanism is suitable for long-term work, the shell is coated with an anticorrosive coating, the electric mechanism can be well suitable for marine climate corrosion, can be applied to multi-model valve control systems in various fields such as aviation, ships and the like, and can reliably work in different complex working environments such as air, sky, sea and land.
Claims (10)
1. An electric mechanism for an aviation fuel valve is characterized by comprising a motor, a shell, a speed reducer, magnetic steel, a pointer, a Hall sensor, a relay and an electric connector;
the output end of the motor is connected with the speed reducer, the magnetic steel, the pointer and the Hall sensor are arranged in the shell, the pointer and the output end of the speed reducer are coaxially fixed, the magnetic steel and the pointer are fixedly connected and coaxially rotate, the Hall sensor is arranged along the motion track of the pointer, and the electric connector is connected with the power supply, the superior system of the host and the filter; an output shaft of the electric mechanism for the aviation fuel valve is connected with a valve core of a ball valve assembly of the fuel valve on-off system, and the output shaft is vertical to a channel of a pipeline where the ball valve assembly is located;
after receiving the designated position signal of a superior system, the electric mechanism for the aviation fuel valve judges the current shaft locking position of the output shaft according to the position signal combination of the Hall sensors at different positions, further judges the current switch position of the ball valve assembly, judges the rotation direction of the motor after comparing with the given position, and realizes the reversing operation of the motor through the relay.
2. The electric mechanism for the aviation fuel valve as recited in claim 1, wherein: the electric mechanism for the aviation fuel valve adopts non-contact position detection, realizes double-position accurate detection by detecting magnetic flux, the pointer is fixed on an output shaft of a motor rotor reducer, magnetic steel is embedded in the inner side of the pointer, Hall position sensors are respectively installed at opening and closing positions, and when the pointer is in place, the magnetic steel triggers a sensing point in the sensor due to Hall effect, outputs a signal in place and cuts off a motor power supply.
3. The electric mechanism for the aviation fuel valve as recited in claim 2, wherein: the electric mechanism adopts a brush direct current motor without a controller.
4. An electric mechanism for an aircraft fuel valve as claimed in claim 3, wherein: the electric mechanism adopts a brush direct current motor with a brake, the electric mechanism comprises a brake and a motor body, the motor body and the brake share a power supply, and the brake is arranged at the tail part of the motor.
5. The electric mechanism for the aviation fuel valve as recited in claim 4, wherein: the brake adopts a power-off brake, the motor shaft is in a locked state by means of spring force under the condition of no power-on, the motor shaft is in an unlocked state by means of electromagnetic force under the condition of power-on, and the lock shaft is fixed after power-off in place;
when the motor body is electrified and works, the brake is unlocked, the brake loses the braking effect, and the motor works normally; when the motor body is powered off, the brake is locked to lock the motor body and the motor body does not work.
6. The electric mechanism for the aviation fuel valve according to any one of claims 1 to 5, wherein: the speed reducer is a two-stage speed reducer and comprises a first-stage harmonic speed reducer and a first-stage gear speed reducer.
7. The electric mechanism for the aviation fuel valve according to any one of claims 1 to 5, wherein: the relay is sealed by laser fusion welding and is provided with two groups of conversion contacts, and the contact type is a dynamic break contact.
8. The electric mechanism for the aviation fuel valve according to any one of claims 1 to 5, wherein: the electric mechanism for the aviation fuel valve further comprises a filter, wherein the filter adopts a differential mode inductor and an X, Y capacitor, and filtering is realized through combination of components.
9. The electric mechanism for the aviation fuel valve as recited in claim 8, wherein: and the signal filtering of the filter circuit adopts high-frequency magnetic beads and a grounding capacitor.
10. The electric mechanism for the aviation fuel valve according to any one of claims 1 to 5, wherein: the shell is sealed to the outside, and the shell of the shell is coated with an anticorrosive coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110980910.0A CN113864508A (en) | 2021-08-25 | 2021-08-25 | Electric mechanism for aviation fuel valve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110980910.0A CN113864508A (en) | 2021-08-25 | 2021-08-25 | Electric mechanism for aviation fuel valve |
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| CN113864508A true CN113864508A (en) | 2021-12-31 |
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| CN202110980910.0A Pending CN113864508A (en) | 2021-08-25 | 2021-08-25 | Electric mechanism for aviation fuel valve |
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Citations (8)
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|---|---|---|---|---|
| US4304256A (en) * | 1978-11-21 | 1981-12-08 | Nova Scotia Research Foundation Corporation | Torque transmitting assembly for rotary valve member |
| FR2786244A1 (en) * | 1998-11-24 | 2000-05-26 | Snecma | Direct control fuel valve for fuel injection circuit in aircraft jet engines, has brushless electric motor controlling the rotational position of rotary slide valve in fuel valve |
| US6435169B1 (en) * | 2000-03-17 | 2002-08-20 | Borgwarner Inc. | Integrated motor and controller for turbochargers, EGR valves and the like |
| US20130104844A1 (en) * | 2011-11-01 | 2013-05-02 | Dh Holdings Co., Ltd. | Air cutoff valve and restart stabilization method using the same |
| CN211901745U (en) * | 2019-11-11 | 2020-11-10 | 北京精密机电控制设备研究所 | Electric mechanism based on Hall zero position sensor |
| CN112460315A (en) * | 2019-09-06 | 2021-03-09 | 精刻株式会社 | Actuator and exhaust valve drive device |
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| WO2021121897A1 (en) * | 2019-12-18 | 2021-06-24 | Pierburg Gmbh | Valve device |
-
2021
- 2021-08-25 CN CN202110980910.0A patent/CN113864508A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4304256A (en) * | 1978-11-21 | 1981-12-08 | Nova Scotia Research Foundation Corporation | Torque transmitting assembly for rotary valve member |
| FR2786244A1 (en) * | 1998-11-24 | 2000-05-26 | Snecma | Direct control fuel valve for fuel injection circuit in aircraft jet engines, has brushless electric motor controlling the rotational position of rotary slide valve in fuel valve |
| US6435169B1 (en) * | 2000-03-17 | 2002-08-20 | Borgwarner Inc. | Integrated motor and controller for turbochargers, EGR valves and the like |
| US20130104844A1 (en) * | 2011-11-01 | 2013-05-02 | Dh Holdings Co., Ltd. | Air cutoff valve and restart stabilization method using the same |
| CN112460315A (en) * | 2019-09-06 | 2021-03-09 | 精刻株式会社 | Actuator and exhaust valve drive device |
| CN211901745U (en) * | 2019-11-11 | 2020-11-10 | 北京精密机电控制设备研究所 | Electric mechanism based on Hall zero position sensor |
| WO2021121897A1 (en) * | 2019-12-18 | 2021-06-24 | Pierburg Gmbh | Valve device |
| CN112483710A (en) * | 2020-12-04 | 2021-03-12 | 浙江银轮机械股份有限公司 | Electric water valve locked-rotor control method and controller |
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| Title |
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| 董峰: "方向舵调整片操纵装置研究", 《航空科学技术》, vol. 29, no. 10, 15 October 2018 (2018-10-15) * |
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