CN203322353U - Dynamic commutator for airplane - Google Patents
Dynamic commutator for airplane Download PDFInfo
- Publication number
- CN203322353U CN203322353U CN2013203626164U CN201320362616U CN203322353U CN 203322353 U CN203322353 U CN 203322353U CN 2013203626164 U CN2013203626164 U CN 2013203626164U CN 201320362616 U CN201320362616 U CN 201320362616U CN 203322353 U CN203322353 U CN 203322353U
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- spool
- flow outlet
- rear side
- groove
- downside
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Abstract
A dynamic commutator for an airplane is characterized by comprising a reversing valve and a hydraulic motor, wherein the reversing valve comprises a valve body and a valve core; an airflow inlet is formed in the front end of the valve body, a rear side airflow outlet is formed in the rear end, and a lower side airflow outlet is also formed in the lower side of the valve body; the valve core penetrates through the valve body in a left direction and a right direction, and a through groove is formed in the valve core in an axial direction perpendicular to the valve core; when the valve core is in a working state that the valve core exhausts gas backwards, the through groove passing through the valve core communicates the airflow inlet with the rear side airflow outlet, but the lower side airflow outlet is blocked; when the valve core is in a working state that the valve core exhausts gas downwards, the through groove passing through the valve core is communicated with the airflow inlet and the lower side airflow outlet, but the rear side airflow outlet is blocked; in a process of switching of two working states of the valve core, the through groove passing through the valve core is always maintained to be communicated with the airflow inlet, the rear side airflow outlet and the lower side airflow outlet simultaneously; and the hydraulic motor driving valve core is switched between the two working states. The dynamic commutator is suitable for being mounted on the motor of the airplane, so that the direction of airflows exhausted by the motor is changed.
Description
Technical field
The utility model relates to a kind of aircraft power reverser, and this aircraft power reverser is for being arranged on the direction of discharging air-flow on airplane engine to change motor.
Background technique
Existing aircarrier aircraft can not vertical takeoff and landing, need to purchase the airport landing, and the construction on airport drops into huge, though and the military aircraft of U.S.'s osprey formula and F-35 can vertical takeoff and landing, work done during landing is all unidirectional work done, the external conversion safety coefficient is lower.In general, the key of the problems referred to above be existing airplane engine the discharge airflow direction be fixed as towards rearward, can not change the switching airflow direction, if from the jet work done earthward vertically downward of principle airplane engine, coordinate again the design of fuselage, can be parked in the aircraft holder in the air, guarantee quiet dynamic flight, be expected to realize the function of vertical takeoff and landing and hovering.
Summary of the invention
The utility model purpose is to provide a kind of aircraft power reverser, so that airplane engine is discharged, airflow direction is changeable to be turned to.
For achieving the above object, the technical solution adopted in the utility model is: a kind of aircraft power reverser comprises selector valve and oil hydraulic motor; Described selector valve comprises valve body and spool, and described valve body front end is airflow inlet, and its rear end is the rear side flow outlet, and the valve body downside also offers the downside flow outlet; Described spool is a cylindrical body of rod, and it is placed through on valve body valve body relatively along left and right directions and is rotationally connected, and axially offers a groove perpendicular to spool on spool; Described spool has two working staties: exhaust work state and exhaust work state backward downwards; When spool is in backward the exhaust work state, through the groove conducting airflow inlet of spool to the rear side flow outlet, but shutoff downside flow outlet; When spool is in downward exhaust work state, through the groove conducting airflow inlet of spool to the downside flow outlet, but shutoff rear side flow outlet; In the transfer process of spool two working staties, remain that through the groove of spool airflow inlet is to rear side flow outlet and the conducting simultaneously of downside flow outlet, to avoid occurring rear side flow outlet and the shutoff simultaneously of downside flow outlet; Described oil hydraulic motor connection function, on spool, drives spool to change between two working staties.
In such scheme, preferred version is that the groove bottom of described groove coincides with the diameter of spool on the radial cross section of spool; It is tangent that described airflow inlet passes to straight hole upper wall and the spool circumference at spool place, and it is also tangent with the spool circumference that described rear side flow outlet passes to the straight hole upper wall at spool place, and that the downside flow outlet passes to the straight hole front panel at spool place is also tangent with the spool circumference.
The utility model design principle and effect are: the utility model adopts the selector valve of particular design, in the transfer process of two working staties of this selector valve, do not exist air-flow to close dead angle, and adopt especially oil hydraulic motor to drive the selector valve switching, to be applicable to airplane engine.So-called air-flow is closed dead angle and is referred to the rear side flow outlet of selector valve and the situation of downside flow outlet shutoff simultaneously, it is the air inlet of selector valve when work airflow inlet or from rear side flow outlet pass-out, from downside flow outlet pass-out, moreover be exactly a part from rear side flow outlet pass-out another part from downside flow outlet pass-out, can not occur air-flow by shutoff in inner situation.
The utility model is to be installed on the flow outlet of airplane engine while using, the airflow inlet that is about to selector valve connects the air-flow that airplane engine is discharged, motor is switched to vertically downward towards the ground exhaust to final vacuum, from principle, the aircraft jet design that coordinates again fuselage towards ground vertically downward, the aircraft holder can be parked in the air, guarantee quiet dynamic flight, be expected to realize the function of vertical takeoff and landing and hovering.In addition, the words of the inversion airplane engine that flow outlet arranges forward if also be equipped with on aircraft during use, also can install the utility model additional forward on the flow outlet arranged of this inversion airplane engine, make aircraft forward and jet towards below, also be expected to realize the function of aircraft inverted flight.
The accompanying drawing explanation
Fig. 1 is that the utility model is installed on the use view on aircraft;
Fig. 2 is that the utility model is while being used and the connection diagram of airplane engine;
Fig. 3 is the utility model embodiment one selector valve complete section schematic diagram, and Fig. 3 a means exhaust work state backward, and Fig. 3 b means exhaust work state and the transfer process between the exhaust work state backward downwards, and Fig. 3 c means downward exhaust work state;
Fig. 4 is the utility model embodiment two selector valve complete section schematic diagram, and Fig. 4 a means exhaust work state backward, and Fig. 4 b means exhaust work state and the transfer process between the exhaust work state backward downwards, and Fig. 4 c means downward exhaust work state;
Fig. 5 is the utility model embodiment three selector valve complete section schematic diagram, and Fig. 5 a means exhaust work state backward, and Fig. 5 b means exhaust work state and the transfer process between the exhaust work state backward downwards, and Fig. 5 c means downward exhaust work state;
Fig. 6 is the utility model embodiment four selector valve complete section schematic diagram, and Fig. 6 a means exhaust work state backward, and Fig. 6 b means exhaust work state and the transfer process between the exhaust work state backward downwards, and Fig. 6 c means downward exhaust work state.
In above figure: 1, selector valve; 2, oil hydraulic motor; 3, valve body; 4, spool; 5, airflow inlet; 6, rear side flow outlet; 7, downside flow outlet; 8, groove; 9, semi-circular holding body; 10, semi-circular holding body; 11, airplane engine.
Embodiment
Below in conjunction with drawings and Examples, the utility model is further described:
Embodiment one: shown in Fig. 1-3:
A kind of aircraft power reverser, be comprised of selector valve 1, oil hydraulic motor 2 and mechanism for installing.
Described selector valve 1 comprises valve body 3 and spool 4, and described valve body 3 front ends are airflow inlet 5, and its rear end is rear side flow outlet 6, and valve body 3 downsides also offer downside flow outlet 7; Described spool 4 is a cylindrical body of rod, and it is placed through on valve body 3 valve body 3 relatively along left and right directions and is rotationally connected, and axially offers a groove 8 perpendicular to spool 4 on spool 4.Described spool 4 has two working staties: exhaust work state and exhaust work state backward downwards; When spool 4 is in backward the exhaust work state, see Fig. 3 a, through the groove 8 conducting airflow inlets 5 of spool 4 to rear side flow outlet 6, but shutoff downside flow outlet 7; When spool 4 is in downward exhaust work state, see Fig. 3 c, through the groove 8 conducting airflow inlets 5 of spool 4 to downside flow outlet 7, but shutoff rear side flow outlet 6; In the transfer process of 4 liang of working staties of spool, see Fig. 3 b, remain that through the groove 8 of spool 4 airflow inlet 5 is to rear side flow outlet 6 and 7 conductings simultaneously of downside flow outlet, to avoid occurring rear side flow outlet 6 and 7 shutoff simultaneously of downside flow outlet.As shown in Figure 3, the groove bottom of described groove 8 coincides with the diameter of spool 4 concrete further structure on the radial cross section of spool 4; It is tangent that described airflow inlet 5 passes to straight hole upper wall and spool 4 circumference at spool 4 places, it is also tangent with spool 4 circumference that described rear side flow outlet 6 passes to the straight hole upper wall at spool 4 places, and that downside flow outlet 7 passes to the straight hole front panel at spool place is also tangent with spool 4 circumference.
Described oil hydraulic motor 2 connection functions, on spool 4, drive spool 4 to change between two working staties.
During work, assumed initial state is to be in the final vacuum working state as Fig. 3 a selector valve 1, and airflow inlet 5 is to groove 8 conductings of rear side flow outlet 6 through spool 4.As long as primer fluid pressure motor 2 drives spool 4 to rotate counterclockwise 90 ° as shown in Fig. 3 a upward arrow, can switch to downward exhaust work state as shown in Figure 3 c when wanting switching direction, airflow inlet 5 is to groove 8 conductings of downside flow outlet 7 through spool 4.In the time will gaining to final vacuum, as long as clockwise rotate 90 ° as shown in Fig. 3 c upward arrow, return back to as Fig. 3 a final vacuum working state.No matter be to switch to downward exhaust work state from the final vacuum working state, or from the exhaust work state switch to exhaust work state backward, in the middle of it, transition state, as shown in Fig. 3 b, not there will be the situation of rear side flow outlet 6 and 7 shutoff simultaneously of downside flow outlet.
Described mechanism for installing as shown in Figure 2, it is a clamping device, by two of left and right semi-circular holding body 9,10 be connected fastening piece and form, semi-circular holding body 9,10 clampings in two of left and right are encircled on airplane engine 11 peripheries, by mechanism for installing, the present embodiment aircraft power reverser are fixed on the outlet end of airplane engine 11.In reality, the mechanism for installing concrete structure is not limit, and can be other linkage structures, and even the present embodiment aircraft power reverser also can directly be arranged at airplane engine 11 enclosure interior, with airplane engine 11 one, is connected.
Embodiment two: shown in Figure 4:
A kind of aircraft power reverser, be comprised of selector valve 1, oil hydraulic motor 2 and mechanism for installing.With embodiment one difference, be: described selector valve 1 internal structure is slightly different, be mainly groove 8 offer ground darker, the degree of depth of groove 8 surpasses the diameter of spool 4, and it is not tangent with spool 4 circumference that described airflow inlet 5 passes to the straight hole upper wall at spool 4 places, it is also not tangent with spool 4 circumference that described rear side flow outlet 6 passes to the straight hole upper wall at spool 4 places, and that downside flow outlet 7 passes to the straight hole front panel at spool place is also not tangent with spool 4 circumference, but still guarantee when spool 4 is in backward the exhaust work state, see Fig. 4 a, through the groove 8 conducting airflow inlets 5 of spool 4 to rear side flow outlet 6, but shutoff downside flow outlet 7, when spool 4 is in downward exhaust work state, see Fig. 4 c, through the groove 8 conducting airflow inlets 5 of spool 4 to downside flow outlet 7, but shutoff rear side flow outlet 6, in the transfer process of 4 liang of working staties of spool, see Fig. 4 b, remain that through the groove 8 of spool 4 airflow inlet 5 is to rear side flow outlet 6 and 7 conductings simultaneously of downside flow outlet, to avoid occurring rear side flow outlet 6 and 7 shutoff simultaneously of downside flow outlet.
Other,, with embodiment one, repeat no more here.
Embodiment three: shown in Figure 5:
A kind of aircraft power reverser, be comprised of selector valve 1, oil hydraulic motor 2 and mechanism for installing.With embodiment one difference, be: described selector valve 1 internal structure is slightly different, be mainly groove 8 offer ground darker, the degree of depth of groove 8 surpasses the diameter of spool 4, and it is not tangent with spool 4 circumference that downside flow outlet 7 passes to the straight hole front panel at spool place, but still can guarantee when spool 4 is in backward the exhaust work state, see Fig. 5 a, through the groove 8 conducting airflow inlets 5 of spool 4 to rear side flow outlet 6, but shutoff downside flow outlet 7; When spool 4 is in downward exhaust work state, see Fig. 5 c, through the groove 8 conducting airflow inlets 5 of spool 4 to downside flow outlet 7, but shutoff rear side flow outlet 6; In the transfer process of 4 liang of working staties of spool, see Fig. 5 b, remain that through the groove 8 of spool 4 airflow inlet 5 is to rear side flow outlet 6 and 7 conductings simultaneously of downside flow outlet, to avoid occurring rear side flow outlet 6 and 7 shutoff simultaneously of downside flow outlet.
Other,, with embodiment one, repeat no more here.
Embodiment four: shown in Figure 6:
A kind of aircraft power reverser, be comprised of selector valve 1, oil hydraulic motor 2 and mechanism for installing.With embodiment one difference, be: described selector valve 1 internal structure is slightly different, be mainly groove 8 offer ground more shallow, the degree of depth of groove 8 is less than the diameter of spool 4, but still can guarantee when spool 4 is in backward the exhaust work state, see Fig. 6 a, through the groove 8 conducting airflow inlets 5 of spool 4 to rear side flow outlet 6, but shutoff downside flow outlet 7; When spool 4 is in downward exhaust work state, see Fig. 6 c, through the groove 8 conducting airflow inlets 5 of spool 4 to downside flow outlet 7, but shutoff rear side flow outlet 6; In the transfer process of 4 liang of working staties of spool, see Fig. 6 b, remain that through the groove 8 of spool 4 airflow inlet 5 is to rear side flow outlet 6 and 7 conductings simultaneously of downside flow outlet, to avoid occurring rear side flow outlet 6 and 7 shutoff simultaneously of downside flow outlet.
Other,, with embodiment one, repeat no more here.
Above-described embodiment is only explanation technical conceive of the present utility model and characteristics, and its purpose is to allow the person skilled in the art can understand content of the present utility model and implement according to this, can not limit protection domain of the present utility model with this.All equivalences of doing according to the utility model Spirit Essence change or modify, within all should being encompassed in protection domain of the present utility model.
Claims (2)
1. an aircraft power reverser, is characterized in that: comprise selector valve and oil hydraulic motor;
Described selector valve comprises valve body and spool, and described valve body front end is airflow inlet, and its rear end is the rear side flow outlet, and the valve body downside also offers the downside flow outlet; Described spool is a cylindrical body of rod, and it is placed through on valve body valve body relatively along left and right directions and is rotationally connected, and axially offers a groove perpendicular to spool on spool; Described spool has two working staties: exhaust work state and exhaust work state backward downwards; When spool is in backward the exhaust work state, through the groove conducting airflow inlet of spool to the rear side flow outlet, but shutoff downside flow outlet; When spool is in downward exhaust work state, through the groove conducting airflow inlet of spool to the downside flow outlet, but shutoff rear side flow outlet; In the transfer process of spool two working staties, remain that through the groove of spool airflow inlet is to rear side flow outlet and the conducting simultaneously of downside flow outlet, to avoid occurring rear side flow outlet and the shutoff simultaneously of downside flow outlet;
Described oil hydraulic motor connection function, on spool, drives spool to change between two working staties.
2. aircraft power reverser according to claim 1, it is characterized in that: the groove bottom of described groove coincides with the diameter of spool on the radial cross section of spool; It is tangent that described airflow inlet passes to straight hole upper wall and the spool circumference at spool place, and it is also tangent with the spool circumference that described rear side flow outlet passes to the straight hole upper wall at spool place, and that the downside flow outlet passes to the straight hole front panel at spool place is also tangent with the spool circumference.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013203626164U CN203322353U (en) | 2013-06-24 | 2013-06-24 | Dynamic commutator for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013203626164U CN203322353U (en) | 2013-06-24 | 2013-06-24 | Dynamic commutator for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203322353U true CN203322353U (en) | 2013-12-04 |
Family
ID=49661705
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013203626164U Expired - Fee Related CN203322353U (en) | 2013-06-24 | 2013-06-24 | Dynamic commutator for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203322353U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736754A (en) * | 2014-12-10 | 2016-07-06 | 上海新跃仪表厂 | Sealed gas reversing device |
-
2013
- 2013-06-24 CN CN2013203626164U patent/CN203322353U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736754A (en) * | 2014-12-10 | 2016-07-06 | 上海新跃仪表厂 | Sealed gas reversing device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131204 Termination date: 20190624 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |