CN117963145A - Pilot-operated type quick-response multi-nozzle propeller - Google Patents
Pilot-operated type quick-response multi-nozzle propeller Download PDFInfo
- Publication number
- CN117963145A CN117963145A CN202410361625.4A CN202410361625A CN117963145A CN 117963145 A CN117963145 A CN 117963145A CN 202410361625 A CN202410361625 A CN 202410361625A CN 117963145 A CN117963145 A CN 117963145A
- Authority
- CN
- China
- Prior art keywords
- pilot
- containing cavity
- main
- nozzle
- shell
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000000694 effects Effects 0.000 abstract description 6
- 230000036544 posture Effects 0.000 description 10
- 238000000034 method Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000004308 accommodation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The application relates to a pilot type quick-response multi-nozzle propeller which comprises a shell, a main valve, a plurality of nozzles and pilot type electromagnetic valves, wherein the pilot type electromagnetic valves are arranged corresponding to the nozzles, and each pilot type electromagnetic valve is used for controlling the on-off of one nozzle respectively; the main valve comprises an air source pipeline and a plurality of main valve cores which are arranged corresponding to the nozzles, a plurality of air cavities which are communicated with the nozzles are formed in the shell, each main valve core is correspondingly arranged in the space behind the main valve core in the air cavity to form a fourth cavity, a second cavity which is communicated with the air cavities is formed in the shell, the pilot electromagnetic valve is arranged between the air source pipeline and the corresponding main valve core, the flow channel in the pilot electromagnetic valve is communicated with the fourth cavity, the flow channel in the pilot electromagnetic valve is controlled to be in atmospheric pressure with the on-off state of the second cavity so as to establish the pressure difference between the second cavity and the fourth cavity, and the main valve core is moved along the axis of the corresponding nozzle under the action of the pressure difference so as to control the on-off state of the second cavity and the corresponding nozzle. The application has the effect of realizing multidirectional posture adjustment of the propeller.
Description
Technical Field
The application relates to the field of jet propellers, in particular to a pilot type rapid-response multi-nozzle propeller.
Background
Jet propulsion is a method for realizing the movement of an object by means of the reaction force transmitted to the object by the momentum of the jet material, and jet propellers are commonly used in the fields of aviation, aerospace, military weapons and the like.
Lightweight, miniaturized, and fast response are trends in modern weaponry. And the jet propeller is used as a power source for generating thrust, and the response speed of the jet propeller directly influences the quick response performance of weapon equipment. At present, most of jet propellers are nozzles, only thrust can be generated in one direction, and posture adjustment cannot be performed. If the multi-directional thrust generation is required to be realized by connecting different propellers in parallel, the volume and the weight of the system are increased, and meanwhile, the reliability and the response speed of the system are reduced.
Disclosure of Invention
In order to improve the response speed of the jet propeller on the basis of the multi-gesture adjusting function, the application provides a pilot type rapid-response multi-nozzle propeller.
The application provides a pilot type quick-response multi-nozzle propeller which adopts the following technical scheme:
a pilot type quick-response multi-nozzle propeller comprises a shell, a main valve, a plurality of nozzles and pilot type electromagnetic valves which are arranged corresponding to the nozzles, wherein each pilot type electromagnetic valve is used for controlling the on-off of one nozzle respectively;
the main valve comprises an air source pipeline and a plurality of main valve cores which are arranged corresponding to the nozzles, a plurality of air cavities which are communicated with the nozzles are formed in the shell, each main valve core is correspondingly arranged in the air cavity, a main spring is arranged between the tail part of the main valve core and the bottom wall of the air cavity, so that a space behind the main valve core forms a fourth cavity, a second cavity which is communicated with the air cavities is formed in the shell, the second cavity is communicated with the air source pipeline, the pilot electromagnetic valve is arranged between the air source pipeline and the corresponding main valve core, a runner in the pilot electromagnetic valve is communicated with the fourth cavity, and the pressure difference between the second cavity and the fourth cavity is established by controlling the on-off of the runner in the pilot electromagnetic valve and the second cavity and the on-off of the internal cavity and the atmospheric pressure of the pilot electromagnetic valve, and the main valve core is subjected to the pressure difference so as to move along the axis corresponding to the nozzles to control the on-off of the second cavity and the corresponding nozzles.
By adopting the technical scheme, one pilot electromagnetic valve respectively controls the on-off of one nozzle, the control modes of the pilot electromagnetic valves are consistent, and the control mode of one pilot electromagnetic valve is firstly used for illustration: firstly, gas in a gas source pipeline is respectively introduced into a second containing cavity at the front ends of a plurality of main valve cores, when a pilot electromagnetic valve is controlled to be closed, the second containing cavity is communicated with a runner in the pilot electromagnetic valve, the runner in the pilot electromagnetic valve is disconnected from the atmospheric pressure, and under the action of internal and external pressure differences, the gas in the runner in the pilot electromagnetic valve flows into a fourth containing cavity, so that the pressure in the fourth containing cavity is higher than the pressure in the second containing cavity, the main valve cores are pushed to move towards a nozzle, and the outlet of the nozzle is plugged; when the pilot type electromagnetic valve is controlled to be opened, the second containing cavity is closed and is not communicated with the flow channel in the pilot type electromagnetic valve, at the moment, the flow channel in the pilot type electromagnetic valve is communicated with the atmospheric pressure, gas left in the flow channel is discharged, gas flowing in from the gas source pipeline is sealed in the second containing cavity, and along with gradual increase of the gas flowing in the second containing cavity, the pressure in the second containing cavity is greater than the pressure in the fourth containing cavity so as to push the main valve core to move in a direction away from the nozzle, the second containing cavity is communicated with the outlet of the nozzle, and the gas is sprayed out from the nozzle; the pilot electromagnetic valve is adopted to open the pilot valve core preferentially, larger thrust is provided on the premise of light weight and small volume, the thrust can be generated in different postures by combining the opening and closing methods of different pilot electromagnetic valves, and the multi-posture adjustment of the propeller is realized.
Preferably, the pilot electromagnetic valve comprises an electromagnet assembly, a pilot valve seat, a pilot valve rod and a pilot valve core capable of sliding between the pilot valve rod and the pilot valve seat, a third flow passage communicated with the second containing cavity is formed in the pilot valve seat, a fifth containing cavity is formed between the pilot valve core and the shell and communicated with the fourth containing cavity, a fifth flow passage communicated with the outside is formed in the pilot valve rod, and the pilot valve core is used for plugging the third flow passage or enabling the third flow passage to be communicated with the fifth containing cavity under the drive of the pilot valve rod.
By adopting the technical scheme, when the pilot-operated electromagnetic valve is closed: the pilot valve core moves upwards, so that the lower end of the pilot valve core is opened, namely, a third flow passage is communicated with a fifth containing cavity, gas entering from a gas source pipeline is dispersed into a second containing cavity corresponding to a plurality of nozzles, the gas in the second containing cavity is transmitted into the fifth containing cavity along the third flow passage, upward pressure is generated by the gas in the passage, the upper end of the pilot valve core is sealed with a pilot valve rod, the gas in the fifth containing cavity cannot be discharged from the fifth flow passage, the gas in the fifth containing cavity enters a fourth containing cavity communicated with the fifth containing cavity, rightward pressure is generated on the main valve core by the gas in the fourth containing cavity, the second containing cavity is sealed by the main valve core, namely, the second containing cavity is not communicated with a nozzle outlet, and the gas cannot be sprayed out from the nozzle position; when the pilot electromagnetic valve is opened: the pilot valve core moves downwards under the action of the pilot push rod, so that the outlet of the third flow channel is sealed at the lower end of the pilot valve core, at the moment, gas in the third flow channel cannot enter the fifth containing cavity, due to the lack of pressure for sealing the upper end of the pilot valve core in the fifth containing cavity, the gas in the fifth containing cavity is discharged along the fifth flow channel, a pressure difference is generated between the fifth containing cavity and the fourth containing cavity, the gas in the fourth containing cavity is enabled to flow back to the fifth containing cavity and be discharged through the fifth flow channel, and due to the fact that a gas source pipeline continuously introduces the gas into the second containing cavity, the pressure difference is quickly built between the second containing cavity and the fourth containing cavity, the main valve core moves leftwards and is opened under the action of the gas pressure in the second containing cavity, the second containing cavity is communicated with the outlet of the nozzle, the gas accumulated in the second containing cavity is ejected from the nozzle, and accordingly thrust is generated.
Preferably, the pilot valve rod comprises a first valve rod section and a second valve rod section, an exhaust runner for communicating the fifth runner with the external atmospheric pressure exists between the first valve rod section and the second valve rod section, and the cross-sectional area of the inlet end of the fifth runner is smaller than or equal to the cross-sectional area of the discharge end of the fifth runner.
By adopting the technical scheme, in order to quickly establish the pressure difference between the second containing cavity and the fourth containing cavity, the propeller is prevented from generating throttling, the gas stored in the fifth containing cavity is required to be quickly discharged when the pilot electromagnetic valve is opened, and the gas in the fifth flow channel is conveniently and quickly discharged by designing the cross section area of the inlet end of the fifth flow channel to be less than or equal to the cross section area of the discharge end of the fifth flow channel.
Preferably, the fifth containing cavity is communicated with the fourth containing cavity through a fourth flow channel, the second containing cavity is communicated with the third flow channel through a second flow channel, the cross-sectional area of the discharge end of the third flow channel is smaller than or equal to that of the inlet end of the third flow channel, and the cross-sectional area of the inlet end of the second flow channel is smaller than or equal to that of the first flow channel.
By adopting the technical scheme, along the flowing direction of the gas, the cross-sectional area of the flow channel is gradually reduced, so that the speed of the gas flowing into the fifth containing cavity is reduced, the volume of the gas in the fifth containing cavity is reduced, the pressure difference between the second containing cavity and the fourth containing cavity is conveniently and rapidly established when the pilot electromagnetic valve is opened, and the response speed of the propeller is further improved.
Preferably, a main spring for pushing the main valve core to move forwards and backwards is arranged in the fourth containing cavity, a pilot spring for pushing the pilot valve core to move between the pilot valve seat and the pilot valve rod is arranged in the fifth containing cavity, the lengths of the main spring and the pilot spring are 6-9cm, and the diameters of the main spring and the pilot spring are 3-5cm.
Through adopting above-mentioned technical scheme, through setting up length and the diameter of main spring and guide spring respectively, can be under the prerequisite that satisfies main spring and guide spring design performance index and appearance chamber, reduce the volume in fourth appearance chamber and fifth appearance chamber to gas is held the chamber and hold between the chamber and fourth to the second and is held the chamber and build up pressure fast, with promoting main valve core action, be convenient for with gas quick blowout.
Preferably, the main valve core comprises a main body section and a flow control section formed at the front end of the main body section, and the diameter of the flow control section is smaller than that of the main body section, so that a step is formed between the main body section and the flow control section, and the area of the step is matched with the elastic coefficient and the length of the main spring.
By adopting the technical scheme, the area of the step is matched with the elastic coefficient and the length of the main spring, the opening speed of the main valve core is accelerated on the basis of meeting the design performance of the main spring, and the quick response performance of the propeller is improved.
On the basis of meeting the design performance of the main spring, the opening speed of the main valve core is increased, and the quick response performance of the propeller is improved.
Preferably, the housing comprises a bottom housing and an upper housing, the pilot valve rod and the electromagnet assembly are installed in the upper housing, the upper housing is provided with an exhaust port for communicating the fifth flow passage with the external atmospheric pressure, and the upper housing is detachably connected with the bottom housing.
Through adopting above-mentioned technical scheme, the axis coincidence of guide's valve rod, guide's case and guide's disk seat to its axis is perpendicular with the axis of air supply pipeline, and the axis of main valve core is perpendicular with the axis of pilot valve, sets up the upper portion shell that is used for installing guide's valve rod and electro-magnet subassembly, saves more space, is convenient for realize the miniaturization of propeller, and the upper portion shell is removable, is convenient for carry out the change of each part of guide's solenoid valve, has realized the modularized design of the propeller of this application.
Preferably, the nozzle comprises a main nozzle and auxiliary nozzles, wherein the main nozzle coincides with the axis of the air source pipeline, the auxiliary nozzles are symmetrically distributed on two sides of the main nozzle, an included angle is formed between the axis of the auxiliary nozzle and the axis of the air source pipeline, a plurality of nozzles are fixed on a quick-dismantling square shell, and the quick-dismantling square shell is fixedly connected with the bottom shell through screws.
By adopting the technical scheme, the auxiliary nozzles symmetrically arranged at two sides of the main nozzle spray out the gas forming an included angle with the propeller so as to adjust the posture of the propeller; the nozzles are detachably fixed on the bottom shell through the quick-dismantling square shell, so that the nozzles can be replaced conveniently, the integrated design of different nozzle models on one propeller can be realized, and the propeller can obtain better propelling and posture adjusting effects conveniently.
In summary, the present application includes at least one of the following beneficial technical effects:
The pilot electromagnetic valve is used for controlling the on-off of the plurality of nozzles and the air source pipeline, larger thrust is provided on the premise of light weight and small volume, different thrust can be provided for different directions through the multi-nozzle and multi-directional thrust design, and the thrust can be generated in different postures through the combination of the opening and closing methods of the different pilot electromagnetic valves;
According to the application, the volumes of the second containing cavity, the fourth containing cavity and the fifth containing cavity are reasonably set, and the cross-sectional areas of the third flow channel, the fifth flow channel and the first flow channel are optimally designed, so that when the pilot electromagnetic valve is opened, gas in the fifth containing cavity is conveniently and rapidly discharged through the fifth flow channel, so that the pressure difference between the second containing cavity and the fourth containing cavity is rapidly established, the main valve core is moved and opened under the action of the pressure difference, the gas is rapidly discharged, and the rapid response of the propeller is realized;
According to the application, the nozzles are integrated on the quick-dismantling square shell, and the quick-dismantling square shell is detachably connected with the bottom shell, so that the nozzles can be conveniently replaced, the integrated design of different nozzle types on one propeller can be realized, and the propeller can conveniently obtain better propelling and posture adjusting effects.
Drawings
Fig. 1 is a schematic view of the overall structure of the present application.
Fig. 2 is a top view of the overall structure of the present application.
Fig. 3 is a schematic partial cross-sectional view of the present application.
Fig. 4 is a schematic cross-sectional structure of an example of any one of the pilot-operated solenoid valves.
Fig. 5 is a partial enlarged view of an internal flow passage of the pilot operated solenoid valve shown in fig. 4.
Fig. 6 is a partial enlarged view of a structure of the main spool in fig. 4.
Reference numerals illustrate: 1. a housing; 11. a bottom shell; 12. an upper case; 121. an exhaust port; 13. quick-dismantling the square shell; 14. a screw; 2. a main valve; 21. an air source pipeline; 22. a main spool; 221. a main body section; 222. a flow control section; 3. a nozzle; 31. a main nozzle; 32. a sub-nozzle; 4. a pilot-operated solenoid valve; 41. an electromagnet assembly; 42. a pilot valve seat; 43. a pilot valve stem; 431. a first valve stem section; 432. a second valve stem section; 45. a pilot spool; 51. a first cavity; 52. a first flow passage; 53. a second cavity; 54. a second flow passage; 55. a third cavity; 56. a third flow passage; 57. a fourth flow passage; 58. a fourth cavity; 59. a fifth cavity; 510. a fifth flow passage; 511. an exhaust runner; 6. a main spring; 7. and a pilot spring.
Detailed Description
The application is described in further detail below with reference to fig. 1-6.
The embodiment of the application discloses a pilot type quick-response multi-nozzle propeller. Referring to fig. 1 to 3, the pilot type rapid response multi-nozzle propeller includes a housing 1, a main valve 2, a plurality of nozzles 3, and pilot type solenoid valves 4 provided corresponding to the nozzles 3, each of the pilot type solenoid valves 4 controlling on/off of one of the nozzles 3, respectively.
Referring to fig. 4 to 6, the control modes of the pilot type solenoid valves 4 are identical, and the control mode of only one pilot type solenoid valve 4 will be described as an example. The main valve 2 comprises an air source pipeline 21 and a plurality of main valve cores 22 which are correspondingly arranged with the nozzles 3, a plurality of air chambers which are communicated with the nozzles 3 are arranged in the shell 1, each main valve core 22 is correspondingly arranged in the air chamber, a main spring 6 is arranged between the tail part of the main valve core 22 and the bottom wall of the air chamber, a fourth containing cavity 58 is formed in the space behind the main valve core 22, a second containing cavity 53 which is communicated with the air chamber is arranged in the shell 1, the second containing cavity 53 is communicated with the air source pipeline 21, and the pilot type electromagnetic valve 4 is arranged between the air source pipeline 21 and the corresponding main valve core 22.
The casing 1 is provided with an exhaust port 121 for communicating a flow passage inside the pilot type solenoid valve 4 with the outside air pressure. The pilot electromagnetic valve 4 is opened or closed so as to control the on-off of the flow passage and the atmospheric pressure in the pilot electromagnetic valve, thereby establishing the pressure difference between the second containing cavity 53 and the fourth containing cavity 58, and enabling the main valve core 22 to move along the axis of the corresponding nozzle 3 under the action of the pressure difference, so as to control the on-off of the second containing cavity 53 (namely the air source pipeline 21) and the corresponding nozzle 3.
Referring to fig. 4 and 5, specifically, the pilot solenoid valve 4 includes a solenoid assembly 41, a pilot valve seat 42, a pilot valve stem 43, and a pilot valve spool 45 slidable between the pilot valve stem 43 and the pilot valve seat 42. A sealing system is provided between the pilot valve seat 42, the pilot valve element 45, the pilot valve stem 43, the main valve element 22, and the housing 1. The air source pipeline 21 is fixed on the shell 1, a first containing cavity 51 communicated with the air source pipeline 21 is formed in the shell 1, and a plurality of first flow passages 52 which are in one-to-one correspondence with the plurality of nozzles 3 are formed in the side wall of the first containing cavity 51. The end of the first flow channel 52 communicates with the second chamber 53. A third flow passage 56 is formed in the pilot valve seat 42, an annular third containing cavity 55 is formed between the outer wall of the pilot valve seat 42 and the housing 1, and the second containing cavity 53 is communicated with the third containing cavity 55 and the third flow passage 56 through the second flow passage 54. A fifth chamber 59 is formed between the side wall of the pilot spool 45 and the housing 1. A fifth flow passage 510 communicating with the outside is formed in the pilot valve stem 43. The fifth chamber 59 communicates with the fourth chamber 58 through the fourth flow passage 57. When the pilot electromagnetic valve is opened or closed, the pilot valve core 45 is driven by the pilot valve rod 43 to move downwards to block or upwards move the third flow passage 56 so as to enable the third flow passage 56 to be communicated with the fifth containing cavity 59, so that a pressure difference between the fourth containing cavity 58 and the second containing cavity 53 is established, when the pressure in the fourth containing cavity 58 is greater than the pressure in the second containing cavity 53, the main valve core 22 moves towards the direction of the nozzle 3 under the pressure of gas in the fourth containing cavity 58, and the nozzle 3 is blocked to disconnect the passage between the nozzle 3 and the gas source pipeline 21; when the pressure in the second chamber 53 is greater than the pressure in the fourth chamber 58, the main valve 22 will be moved away from the nozzle 3 by the pressure of the gas in the second chamber 53 to connect the second chamber 53 and the nozzle 3, so that the gas flowing into the second chamber 53 from the gas source pipe 21 is ejected from the nozzle 3.
Specifically, the circulation route of the gas in the cavity is as follows: when the pilot electromagnetic valve 4 is closed, the pilot valve core 45 moves upwards, so that the lower end of the pilot valve core 45 is opened, namely, the third flow channel 56 and the fifth flow channel 59 are in a communication state, gas introduced from the gas source pipeline 21 is uniformly dispersed into the second flow channel 53 corresponding to the plurality of nozzles 3 through the first flow channel 51 and the first flow channel 52, so that the gas in the second flow channel 53 is introduced into the third flow channel 55 along the second flow channel 54, and then introduced into the third flow channel 56 from the third flow channel 55 and finally introduced into the fifth flow channel 59, and the gas in the fifth flow channel 59 generates upward pressure, so that the upper end of the pilot valve core 45 is sealed with the pilot valve rod 43, and the inlet of the fifth flow channel 510 is blocked. Thus, the pressure difference between the fifth containing cavity 59 and the fourth containing cavity 58 can be utilized to enable the gas to enter the fourth containing cavity 58 through the fourth flow channel 57, the gas in the fourth containing cavity 58 generates rightward pressure on the main valve core 22, so that the main valve core 22 seals the second containing cavity 53, that is, the second containing cavity 53 is not communicated with the outlet of the nozzle 3, and the gas cannot be ejected from the position of the nozzle 3. When the pilot electromagnetic valve 4 is opened, the pilot valve core 45 moves downwards under the action of the pilot push rod, so that the outlet of the third flow channel 56 is sealed by the lower end of the pilot valve core 45, at this time, gas in the third flow channel 56 cannot enter the fifth flow channel 59, due to the lack of pressure in the fifth flow channel 59, which seals the upper end of the pilot valve core 45, the gas in the fifth flow channel 59 is discharged along the fifth flow channel 510, a pressure difference is generated between the fifth flow channel 59 and the fourth flow channel 58, the gas in the fourth flow channel 58 flows back to the fifth flow channel 59 and is discharged through the fifth flow channel 510, and as the gas source pipeline 21 continuously introduces the gas into the second flow channel 53, a pressure difference is quickly established between the second flow channel 53 and the fourth flow channel 58, the main valve core 22 moves leftwards to be opened under the action of the gas pressure in the second flow channel 53, the second flow channel 53 is communicated with the outlet of the nozzle 3, and the gas accumulated in the second flow channel 53 is ejected from the nozzle 3, so that the thrust is generated.
In order to reasonably utilize the positions in the housing 1, the positions of the three pilot-operated solenoid valves 4 are reasonably distributed, on the basis that the internal structure of the pilot valve is not affected, each pilot-operated solenoid valve 4 corresponds to two first flow passages 52, and the two first flow passages 52 are symmetrically arranged on two sides of the pilot valve core 45. Preferably, the first flow channel 52 is arcuate in design, which is more advantageous for achieving the miniaturization of the propeller of the present application.
A pilot spring 7 for urging the pilot spool 45 to move between the pilot valve seat 42 and the pilot valve stem 43 is placed in the fifth accommodation chamber 59. In order to increase the response speed of the propeller according to the application, i.e. the speed at which gas enters from the gas source conduit 21 and is ejected from the corresponding nozzle 3. This is mainly dependent on how long main valve spool 22 is open, i.e. how fast a pressure difference is established between fourth volume 58 and second volume 53. The optimization should be designed from several aspects:
First, the volumes of the fifth chamber 59 and the fourth chamber 58 should be designed as small as possible on the premise of meeting the design performance indexes and the space of the main spring 6 and the pilot spring 7. Through design optimization, the lengths of the main spring 6 and the pilot spring 7 are 6-9cm, and the diameters of the main spring 6 and the pilot spring 7 are 3-5cm.
Second, the pilot valve stem 43 includes a first valve stem section 431 and a second valve stem section 432, and an exhaust flow passage 511 for communicating the fifth flow passage 510 with the outside atmospheric pressure exists between the first valve stem section 431 and the second valve stem section 432. When the pilot solenoid valve 4 is opened, the gas flowing into the fifth flow passage 510 is discharged through the exhaust flow passage 511, and is depressurized. In order to quickly establish the pressure difference between the second chamber 53 and the fourth chamber 58 and increase the response speed of the propeller, the gas entering the fifth flow channel 510 should be quickly discharged, so that the cross-sectional area of the inlet end of the fifth flow channel 510 is less than or equal to the cross-sectional area of the discharge end of the fifth flow channel 510. The cross-sectional area of the discharge end of the fifth flow passage 510=the cross-sectional area of the exhaust flow passage 511.
Third, it is also contemplated that the cross-sectional area of the discharge end of the third flow passage 56 is less than or equal to the cross-sectional area of the inlet end of the third flow passage 56 and less than or equal to the cross-sectional area of the inlet end of the second flow passage 54 and less than or equal to the cross-sectional area of the first flow passage 52. Along the flow direction of the gas, the cross-sectional area of the flow channel gradually decreases, so that the speed of the gas flowing into the fifth containing cavity 59 is reduced, the volume of the gas in the fifth containing cavity 59 is reduced, the pressure difference between the second containing cavity 53 and the fourth containing cavity 58 is conveniently and rapidly established when the pilot electromagnetic valve 4 is opened, and rapid response is realized.
Fourth, when the nozzle 3 is disconnected from the air source pipe 21, the sum of the pressure in the fourth chamber 58 and the elastic force of the main spring 6 when stretched is greater than the pressure in the air pressure fourth chamber 58 in the second chamber 53. When the nozzle 3 is connected to the air supply line 21, the pressure in the second chamber 53 is greater than the elastic force of the main spring 6 when compressed. It is necessary to rationally design the spring force coefficient of the main spring 6, the length of the main spring 6, the distance the main spool 22 moves (which can be further understood as the volume difference between the second chamber 53 and the fourth chamber 58) so that a pressure difference is quickly established between the second chamber 53 and the fourth chamber 58.
The main valve core 22 comprises a main body section 221 and a flow control section 222 formed at the front end of the main body section 221, wherein the diameter of the flow control section 222 is smaller than that of the main body section 221, so that a step is formed between the main body section 221 and the flow control section 222. Assuming that the diameter of the main body section 221 is A and the diameter of the flow control section 222 is B, the cross-sectional area of the step is. Since the main spool 22 is subject to gas pressure, circumferential and bore wall friction forces, and spring forces, the friction forces are negligible relative to the spring forces and gas pressure in the present invention. By analyzing the force relationship when main spool 22 opens:
When main spool 22 is closed: At this time, the force value is directed to the right, and the main valve core 22 is closed;
when main valve spool 22 is open: At this point the force is directed to the left and main valve spool 22 is open. /(I) P is the pressure in the second chamber 53, which is the elastic force of the main spring 6.
It is then necessary to design the value of the force of the main spring 6Relation to the thrust exerted by main spool 22:
Assuming that the length of the main spring 6 is y in the closed state of the valve core, the opening displacement of the main valve core 22 is x when the main valve core 22 is opened, the rigidity of the main spring 6 is k, and the design pressure of the main spring force should satisfy the force value of the closed state of the main valve core 22: main spool 22 on state force value: /(I) 。
Therefore, the area of the step is matched with the elastic coefficient and the length of the main spring 6, the opening speed of the main valve core 22 is accelerated on the basis of meeting the design performance of the main spring 6, and the quick response performance of the propeller is improved.
The housing 1 includes a bottom housing 11 and an upper housing 12, and a pilot valve stem 43 and an electromagnet assembly 41 are mounted in the upper housing 12. The upper case 12 is provided with exhaust ports 121 for communicating the exhaust fifth flow passage 510 with the outside atmospheric pressure, and the exhaust ports 121 are also provided in correspondence with the number of the pilot type solenoid valves 4. The cross section of the upper shell 12 is in a convex shape, and three pilot valve rods 43 are arranged in a mountain shape in the upper shell 12 so as to reasonably utilize the space in the outer shell 1 and reduce the whole volume of the propeller.
The nozzle 3 comprises a main nozzle 31 which is coincident with the axis of the air source pipeline 21 and auxiliary nozzles 32 which are symmetrically distributed on two sides of the main nozzle 31, wherein the axis of the auxiliary nozzle 32 forms an included angle with the axis of the air source pipeline 21. The auxiliary nozzles 32 symmetrically arranged at both sides of the main nozzle 31 are used for conveniently adjusting the posture of the propeller by spraying gas forming an included angle with the propeller. The present application will be described by taking the example that the main nozzle 31 is provided with one and the sub-nozzle 32 is symmetrically provided with two. The spray nozzles 3 are fixed on the quick-release square shell 13, and the quick-release square shell 13 is fixedly connected with the bottom shell 11 through screws 14. The novel propeller is convenient to replace the nozzle 3, can realize the integrated design of different nozzle 3 models on one propeller, and is convenient for the propeller to obtain better propelling and posture adjusting effects. The upper shell 12 and the bottom shell 11 are also detachably connected, so that the replacement of all parts of the pilot-operated electromagnetic valve 4 is facilitated, and the modular design of the propeller is realized.
The implementation principle of the pilot type quick-response multi-nozzle propeller provided by the embodiment of the application is as follows: the application designs a main nozzle 31 which is coincident with the axis of the air source pipeline 21 and two auxiliary nozzles 32 which form an included angle with the axis of the air source pipeline 21, and can realize the thrust generation with different postures by combining opening and closing methods of different pilot electromagnetic valves 4. The pilot electromagnetic valve 4 preferentially opens the pilot valve core 45, and provides larger thrust on the premise of light weight and small volume. And by optimally designing the volumes of the fourth containing cavity 58 and the fifth containing cavity 59, optimally designing the cross-sectional areas of the first flow passage 52, the second flow passage 54, the third flow passage 56 and the fifth flow passage 510 and optimally designing the cross-sectional areas of the flow control section 222 of the main valve core 22, the pressure difference between the second containing cavity 53 and the fifth containing cavity 59 can be quickly established, the quick response capability of the propeller is improved, and the propeller can be quickly opened and closed. The flow channel and the cavity after design optimization can realize that the opening and closing response time is within 20 ms. The nozzles 3 are detachably fixed on the bottom shell 11 through the quick-dismantling square shell 13, so that the nozzles 3 can be conveniently replaced, the integrated design of different types of the nozzles 3 on one propeller can be realized, and the propeller can conveniently obtain better propelling and posture adjusting effects.
The above embodiments are not intended to limit the scope of the present application, so: all equivalent changes in structure, shape and principle of the application should be covered in the scope of protection of the application.
Claims (8)
1. A pilot-operated, fast-responding, multi-nozzle propeller, characterized by: the device comprises a shell (1), a main valve (2), a plurality of nozzles (3) and pilot electromagnetic valves (4) which are arranged corresponding to the nozzles (3), wherein each pilot electromagnetic valve (4) respectively controls the on-off of one nozzle (3);
The main valve (2) comprises an air source pipeline (21) and a plurality of main valve cores (22) which are correspondingly arranged with the nozzles (3), a plurality of air cavities which are correspondingly arranged with the nozzles (3) are formed in the shell (1), each main valve core (22) is correspondingly arranged in the air cavity, a main spring (6) is arranged between the tail part of the main valve core (22) and the bottom wall of the air cavity, so that a fourth containing cavity (58) is formed in the space behind the main valve core (22), a second containing cavity (53) which is correspondingly communicated with the air cavities is formed in the shell (1), the second containing cavity (53) is correspondingly communicated with the air source pipeline (21), the pilot electromagnetic valve (4) is arranged between the air source pipeline (21) and the corresponding main valve core (22), and the flow passage inside the pilot electromagnetic valve is correspondingly communicated with the fourth containing cavity (58), and the on-off of the second containing cavity (53) and the on-off of the inner containing cavity and the air pressure of the space form a second containing cavity (53) so as to establish the second containing cavity (53) which is correspondingly connected with the air pressure difference (3) along the axis (3) and the pressure difference (53) which is correspondingly controlled by the pressure difference (3).
2. The piloted fast response multi-nozzle propeller of claim 1, wherein: the pilot electromagnetic valve (4) comprises an electromagnet assembly (41), a pilot valve seat (42), a pilot valve rod (43) and a pilot valve core (45) capable of sliding between the pilot valve rod (43) and the pilot valve seat (42), a third flow passage (56) communicated with the second containing cavity (53) is formed in the pilot valve seat (42), a fifth containing cavity (59) is formed between the pilot valve core (45) and the shell (1), the fifth containing cavity (59) is communicated with the fourth containing cavity (58), a fifth flow passage (510) communicated with the outside is formed in the pilot valve rod (43), and the pilot valve core (45) is used for being driven by the pilot valve rod (43) to seal the third flow passage (56) or enable the third flow passage (56) to be communicated with the fifth containing cavity (59).
3. The piloted fast response multi-nozzle propeller of claim 2, wherein: the pilot valve rod (43) comprises a first valve rod section (431) and a second valve rod section (432), an exhaust flow passage (511) used for communicating the fifth flow passage (510) with the outside atmosphere is arranged between the first valve rod section (431) and the second valve rod section (432), and the cross-sectional area of the inlet end of the fifth flow passage (510) is smaller than or equal to the cross-sectional area of the discharge end of the fifth flow passage (510).
4. The piloted fast response multi-nozzle propeller of claim 2, wherein: the fifth containing cavity (59) is communicated with the fourth containing cavity (58) through a fourth flow channel (57), the second containing cavity (53) is communicated with the third flow channel (56) through a second flow channel (54), and the cross-sectional area of the discharge end of the third flow channel (56) is smaller than or equal to that of the inlet end of the third flow channel (56), and the cross-sectional area of the inlet end of the second flow channel (54) is smaller than or equal to that of the first flow channel (52).
5. The piloted fast response multi-nozzle propeller of claim 2, wherein: a pilot spring (7) for pushing the pilot valve core (45) to move between the pilot valve seat (42) and the pilot valve rod (43) is arranged in the fifth containing cavity (59), the lengths of the main spring (6) and the pilot spring (7) are 6-9cm, and the diameters of the main spring (6) and the pilot spring (7) are 3-5cm.
6. The piloted fast response multi-nozzle propeller of claim 1, wherein: the main valve core (22) comprises a main body section (221) and a flow control section (222) formed at the front end of the main body section (221), the diameter of the flow control section (222) is smaller than that of the main body section (221), a step is formed between the main body section (221) and the flow control section (222), the difference value of the cross section area of the flow control section (222) and the cross section area of the main body section (221) is in direct proportion to the response speed, and the elastic coefficient of the main spring (6) is in inverse proportion to the response speed.
7. The piloted fast response multi-nozzle propeller of claim 2, wherein: the shell (1) comprises a bottom shell (11) and an upper shell (12), wherein the pilot valve rod (43) and the electromagnet assembly (41) are installed in the upper shell (12), the upper shell (12) is provided with an exhaust port (121) for communicating a fifth flow channel (510) with external atmospheric pressure, and the upper shell (12) is detachably connected with the bottom shell (11).
8. The piloted fast response multi-nozzle propeller of claim 7, wherein: the air source pipeline is characterized in that the nozzle (3) comprises a main nozzle (31) and auxiliary nozzles (32), the main nozzle (31) is coincident with the axis of the air source pipeline (21), the auxiliary nozzles (32) are symmetrically distributed on two sides of the main nozzle (31), the axis of the auxiliary nozzles (32) and the axis of the air source pipeline (21) form an included angle, a plurality of nozzles (3) are fixed on the quick-dismantling square shell (13), and the quick-dismantling square shell (13) is fixedly connected with the bottom shell (11) through screws (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410361625.4A CN117963145B (en) | 2024-03-28 | 2024-03-28 | Pilot-operated type quick-response multi-nozzle propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410361625.4A CN117963145B (en) | 2024-03-28 | 2024-03-28 | Pilot-operated type quick-response multi-nozzle propeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117963145A true CN117963145A (en) | 2024-05-03 |
| CN117963145B CN117963145B (en) | 2024-06-07 |
Family
ID=90853712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410361625.4A Active CN117963145B (en) | 2024-03-28 | 2024-03-28 | Pilot-operated type quick-response multi-nozzle propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117963145B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3181818A (en) * | 1964-05-15 | 1965-05-04 | United Aircraft Corp | Shock wave position controller |
| CN101727108A (en) * | 2008-10-30 | 2010-06-09 | 北京航空航天大学 | Low-flow gas control device and using method thereof |
| CN102756805A (en) * | 2011-03-29 | 2012-10-31 | 郑鹏 | Traction energy transmission type duct rotor wing fly lifter |
| CN209780748U (en) * | 2019-04-09 | 2019-12-13 | 苏州市职业大学 | Frequency-adjustable resonance type hydraulic rock drill |
| CN114000873A (en) * | 2021-10-20 | 2022-02-01 | 中煤科工开采研究院有限公司 | Coal seam drilling, cutting and punching integrated equipment and hole expanding method thereof |
| CN114455105A (en) * | 2022-04-13 | 2022-05-10 | 国科大杭州高等研究院 | micro-Newton-level gem-based double-gas-capacity variable-thrust closed-loop cold air thruster and operation method thereof |
| CN117307727A (en) * | 2023-09-26 | 2023-12-29 | 河南航天液压气动技术有限公司 | Pilot-operated electromagnetic valve and working method thereof |
| CN117646640A (en) * | 2023-12-31 | 2024-03-05 | 中国矿业大学 | Hydraulic support electrohydraulic proportional control system and method based on independent pilot liquid supply valve |
-
2024
- 2024-03-28 CN CN202410361625.4A patent/CN117963145B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3181818A (en) * | 1964-05-15 | 1965-05-04 | United Aircraft Corp | Shock wave position controller |
| CN101727108A (en) * | 2008-10-30 | 2010-06-09 | 北京航空航天大学 | Low-flow gas control device and using method thereof |
| CN102756805A (en) * | 2011-03-29 | 2012-10-31 | 郑鹏 | Traction energy transmission type duct rotor wing fly lifter |
| CN209780748U (en) * | 2019-04-09 | 2019-12-13 | 苏州市职业大学 | Frequency-adjustable resonance type hydraulic rock drill |
| CN114000873A (en) * | 2021-10-20 | 2022-02-01 | 中煤科工开采研究院有限公司 | Coal seam drilling, cutting and punching integrated equipment and hole expanding method thereof |
| CN114455105A (en) * | 2022-04-13 | 2022-05-10 | 国科大杭州高等研究院 | micro-Newton-level gem-based double-gas-capacity variable-thrust closed-loop cold air thruster and operation method thereof |
| CN117307727A (en) * | 2023-09-26 | 2023-12-29 | 河南航天液压气动技术有限公司 | Pilot-operated electromagnetic valve and working method thereof |
| CN117646640A (en) * | 2023-12-31 | 2024-03-05 | 中国矿业大学 | Hydraulic support electrohydraulic proportional control system and method based on independent pilot liquid supply valve |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117963145B (en) | 2024-06-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20200284219A1 (en) | Generation of a Pulsed Jet by Jet Vectoring Through a Nozzle with Multiple Outlets | |
| US10024626B2 (en) | Compressed gas gun | |
| CN109915263B (en) | Axisymmetric bimodal air inlet for combined engine and modal switching method | |
| JP2010528222A (en) | Gas mixing ejector with variable injection cross section | |
| CN201326477Y (en) | Two-control-in-one-position pneumatic pilot-valve used in gelled-propellant supply system | |
| CN108035824A (en) | A kind of pulsed secondary jet thrust vector control system | |
| CN110631051A (en) | Powder fluidization powder supply device | |
| CN117963145B (en) | Pilot-operated type quick-response multi-nozzle propeller | |
| EP1735532A2 (en) | Thrust vector control system for a plug nozzle rocket engine | |
| CN106499543A (en) | The apparatus and method that a kind of ejector exhaust pipe thruster vector control is adjusted with area | |
| CN109611236B (en) | Pneumatic adjusting adjustable spray pipe with flexible throat insert | |
| US20090321667A1 (en) | Servo valve modules and torque motor assemblies | |
| EP2883263B1 (en) | Passive recirculation device | |
| CN112594091B (en) | Solid attitude and orbit control engine gas valve and control method thereof | |
| EP0258370B1 (en) | Reaction jet control system | |
| CN112343734A (en) | Pneumatic combination valve of rocket engine, rocket engine and carrier rocket | |
| CN114109643B (en) | Multi-adjoint vector thrust engine | |
| CN114165354B (en) | Design method of multi-adjoint vector thrust engine | |
| CN214698532U (en) | Small valve pilot type sheet-mounted integrated large-flow vacuum generator | |
| JP3203343U (en) | Shooting device that launches using air pressure | |
| CN211145447U (en) | Shunt valve controlled double-jet pipe electro-hydraulic servo valve | |
| CN110848420A (en) | Method for controlling jet flow splitter valve and dual-jet-pipe electro-hydraulic servo valve controlled by splitter valve | |
| CN106342142B (en) | High-temperature fuel gas valve | |
| CN113464310A (en) | Passive secondary flow multi-axis coupling thrust vectoring nozzle | |
| KR20140036591A (en) | Pilot type solenoid valve |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |