CN103883664A - Throttle valve for helicopter - Google Patents
Throttle valve for helicopter Download PDFInfo
- Publication number
- CN103883664A CN103883664A CN201210563740.7A CN201210563740A CN103883664A CN 103883664 A CN103883664 A CN 103883664A CN 201210563740 A CN201210563740 A CN 201210563740A CN 103883664 A CN103883664 A CN 103883664A
- Authority
- CN
- China
- Prior art keywords
- throttle valve
- spool
- helicopter
- valve seat
- fixed cover
- 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.)
- Pending
Links
Images
Abstract
The invention belongs to the technical field of landing gears of aircrafts, particularly relates to the technical field of shock absorbers for landing gears of helicopters, and discloses a throttle valve for a helicopter. The throttle valve comprises an elastic assembly (11), a fixing cover (12), a valve element (13) and a valve seat (16). The valve element (13) is a hollow part, a fixed oil hole (14) is formed in an end of the valve element (13), the valve seat (16) is a hollow part, a variable oil hole (15) is formed in an end of the valve seat (16), the fixing cover (12) is a hollow part, the elastic assembly (11), the fixing cover (12) and the valve element (13) are mounted in a cavity of the valve seat (16), the fixing cover (12) is fixed onto the valve seat (16), one surface of the elastic assembly (11) is fixedly butted onto the fixing cover (12), the other surface of the elastic assembly (11) is fixedly butted to the certain end of the valve element (13), the fixed oil hole is not formed in the certain end of the valve element (13), and the outer surface of the end, where the fixed oil hole is formed, of the valve element (13) is matched with the inner surface of the variable oil hole (15). The throttle valve has the advantages that requirements on landing load and overload control from a low speed to a high speed can be met, and the throttle valve is simple in structure.
Description
Technical field
The invention belongs to the technical field of undercarriage, particularly relate to the buffer technology field that helicopter landing gear is used.
Background technique
Undercarriage is for the special arrangement of taking off landing.In aircraft landing process, always with certain speed colliding surface, undercarriage bears and slows down this shock, thereby alleviates the stand under load of aircraft.The critical component that undercarriage slows down this bump stroke is exactly buffer.Buffer is by the damping hole landing energy that dissipates, and the buffer oilhole generally using is at present stand oil hole.
As shown in Figure 1, aircraft landing bump stroke passes to wheel fork 2 by wheel 1 to the tail undercarriage of certain type helicopter, then passes to buffer 4 by rocking arm 3.Compression by buffer these Impact energies that absorb, dissipate.The working medium of buffer is fluid and gas.Typical buffer configuration as shown in Figure 3, comprise piston 5, gas 6, piston rod 7, urceolus 8, oilhole 9 and fluid 10, wherein, the relative urceolus 8 of piston rod 7 compresses, fluid 10 is by stand oil hole 9, the landing energy thereby the damping of generation fluid dissipates, fluid can promote floating piston 5 pressurized gass 6 and absorb landing energy simultaneously.This buffer typically with stand oil hole, for some fixing landing speeds, or landing speed excursion is little time, and stand oil hole can meet dissipation energy, reduces load and controls the requirement of overload.For thering is larger velocity range, if need to meet the landing requirement of little speed and large speed, need oilhole oilhole when speed is little little, when speed is large, oilhole is large, and this is contradiction to stand oil hole.
Summary of the invention
(1) object of the present invention: to have dissipation energy, the reduction load of larger landing speed scope in order meeting and to control the requirement of transshipping, spy proposes the throttle valve that a kind of helicopter is used.
(2) technological scheme of the present invention: the throttle valve that a kind of helicopter is used, it is characterized in that, this throttle valve comprises elastic member 11, fixed cover 12, spool 13 and valve seat 16, wherein, spool 13 is hollow piece, there is stand oil hole 14 one end of spool 13, valve seat 16 is hollow piece, there is the oilhole 15 of change valve seat 16 one end, fixed cover 12 is hollow piece, elastic member 11, fixed cover 12 and spool 13 are arranged in the cavity of valve seat 16, fixed cover 12 is fixed on valve seat 16, the one side of elastic member 11 is even at the cost of one's life on fixed cover 12, another side is even at the cost of one's life at the non-stand oil nose end of spool 13, the outer surface of the stand oil nose end of spool 13 coordinates with change oilhole 15 internal surfaces.
Described elastic member 11 is an official document or note reed or spring.
On described spool 13 non-stand oil nose end outside and fixed cover 12, be useful on the deck structure of elastic member 11 even at the cost of one's life.Further, described deck structure is draw-in groove or step.
The stand oil nose end outer surface of described change oilhole 15 internal surfaces and the spool 13 being mated is conical surface or sphere.
Described fixed cover 12 and valve seat 16 are fixedly connected with by outer, internal surface screw thread or screw.
Described hollow piece fixed cover 12, spool 13 and valve seat 16 is all tubular elements.Further, described tubular elements is square tube or cylinder.
(3) beneficial effect of the present invention: by this throttle valve that changes the outfit on the piston rod of buffer, landing load and the overload that can realize from little speed to large speed are controlled requirement, and simple in structure, and the design parameter that throttle valve provides is abundant.
Accompanying drawing explanation:
Fig. 1 is the tail undercarriage schematic diagram of certain type helicopter, and wherein, 1 is wheel, and 2 is wheel fork, and 3 is rocking arm, and 4 is buffer;
Fig. 2 is the configuration schematic diagram of typical bumper; Wherein, 5 is piston, and 6 is gas, and 7 is piston rod, and 8 is urceolus, and 9 is oilhole, and 10 is fluid;
Fig. 3 is the buffer structure figure of stand oil cellular type; Wherein, 5 is piston, and 6 is gas, and 7 is piston rod, and 8 is urceolus, and 10 is fluid, and 17 is threaded, and 18 is supporting sleeve, and 19 is pin, and 20 is throttle valve, and 21 is fixed cover;
Fig. 4 is throttle-valve structure figure of the present invention; Wherein, 11 is elastic member, and 12 is fixed cover, and 13 is spool, and 14 is stand oil hole, and 15 for becoming oilhole, and 16 is valve seat;
Fig. 5 is the buffer structure figure of throttle valve of the present invention of changing the outfit, and wherein, 5 is piston, and 6 is gas, and 7 is piston rod, and 8 is urceolus, and 10 is fluid, and 17 is threaded, and 18 is supporting sleeve, and 19 is pin, and 20 is throttle valve, and 21 is fixed cover.
Embodiment:
By specific embodiment and accompanying drawing, the present invention is described in detail:
The throttle valve that a kind of helicopter is used, it is characterized in that, this throttle valve comprises elastic member 11, fixed cover 12, spool 13 and valve seat 16, wherein, spool 13 is hollow piece, there is stand oil hole 14 one end of spool 13, valve seat 16 is hollow piece, there is the oilhole 15 of change valve seat 16 one end, fixed cover 12 is hollow piece, elastic member 11, fixed cover 12 and spool 13 are arranged in the cavity of valve seat 16, fixed cover 12 is fixed on valve seat 16, the one side of elastic member 11 is even at the cost of one's life on fixed cover 12, another side is even at the cost of one's life at the non-stand oil nose end of spool 13, the outer surface of the stand oil nose end of spool 13 coordinates with change oilhole 15 internal surfaces.
Described elastic member 11 is spring.
On described spool 13 non-stand oil nose end outside and fixed cover 12, be useful on the step deck structure of elastic member 11 even at the cost of one's life.
The stand oil nose end outer surface of described change oilhole 15 internal surfaces and the spool 13 being mated is conical surface.
Described fixed cover 12 is fixedly connected with by outer, internal surface screw thread with valve seat 16.
Described hollow piece fixed cover 12, spool 13 and valve seat 16 is all cylinder.
Install time of the present invention, referring to Fig. 3, a kind of buffer structure figure of stand oil cellular type.Formed the inner chamber of sealing by piston rod 7,8 two cylindrical shells of urceolus and outer seal structure supporting sleeve 18.Threaded 17 is fixed on fixed support cover 18 on urceolus.Inner chamber filling fluid 10 and gas 6.Floating piston 5 is by fluid and gas barrier.Supporting sleeve and floating piston are all provided with seal ring, for sealing the gentle body of fluid.The throttle valve 20 of stand oil cellular type is fixed on piston rod by fixed cover 21 and pin 19.When aircraft landing, buffer compression, the relative urceolus axial motion of piston rod, makes fluid produce fluid damping by throttle valve.Change the outfit after throttle valve of the present invention, buffer structure as shown in Figure 5, can be realized the landing load control from little speed to large speed.
Working principle of the present invention is: when aircraft landing, and buffer compression, the relative urceolus axial motion of piston rod, makes fluid produce fluid damping by throttle valve.In the time of aircraft slow landing, fluid damping force suffered when fluid flows through throttle valve is less, and spool is not opened, and is stand oil hole 14.In the time of aircraft fast landing, fluid damping force suffered when fluid flows through throttle valve is larger, and spool is opened, and for becoming oilhole 15, has increased fluid damping hole, can reduce fluid damping force, and then reduces landing load.
Fixedly be stamped certain screw-down torque requirement, to control the decrement of an official document or note reed, for guaranteeing that spool opens in the larger compression speed of buffer.An official document or note reed has certain rigidity and stroke requirement, to guarantee the unlatching situation of spool.
In embodiment of throttle valve of invention, hole 14 is 13.5mm, and hole 15 is 20.5mm.The total kilometres of an official document or note reed 11 are 2mm, global stiffness 1000N/mm～4000N/mm, and throttle valve pretightening force is 200N～1000N.
Claims (8)
1. the throttle valve that helicopter is used, it is characterized in that, this throttle valve comprises elastic member (11), fixed cover (12), spool (13) and valve seat (16), wherein, spool (13) is hollow piece, there is stand oil hole (14) one end of spool (13), valve seat (16) is hollow piece, there is change oilhole (15) valve seat (16) one end, fixed cover (12) is hollow piece, elastic member (11), fixed cover (12) and spool (13) are arranged in the cavity of valve seat (16), fixed cover (12) is fixed on valve seat (16), the one side of elastic member (11) is even at the cost of one's life on fixed cover (12), another side is even at the cost of one's life at the non-stand oil nose end of spool (13), the outer surface of the stand oil nose end of spool (13) coordinates with change oilhole (15) internal surface.
2. the throttle valve that a kind of helicopter as claimed in claim 1 is used, is characterized in that, described elastic member (11) is an official document or note reed or spring.
3. the throttle valve that a kind of helicopter as claimed in claim 1 is used, is characterized in that, on described spool (13) non-stand oil nose end outside and fixed cover (12), is useful on the deck structure of elastic member (11) even at the cost of one's life.
4. the throttle valve that a kind of helicopter as claimed in claim 3 is used, is characterized in that, described deck structure is draw-in groove or step.
5. the throttle valve that a kind of helicopter as claimed in claim 4 is used, is characterized in that, the stand oil nose end outer surface of described change oilhole (15) internal surface and the spool (13) being mated is conical surface or sphere.
6. the throttle valve that a kind of helicopter as claimed in claim 1 is used, is characterized in that, described fixed cover (12) and valve seat (16) are fixedly connected with by outer, internal surface screw thread or screw.
7. the throttle valve that a kind of helicopter as described in one of claim 1-6 is used, is characterized in that, described hollow piece fixed cover (12), spool (13) and valve seat (16) are all tubular elements.
8. the throttle valve that a kind of helicopter as claimed in claim 7 is used, is characterized in that, the square tube that described tubular elements is or cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210563740.7A CN103883664A (en) | 2012-12-21 | 2012-12-21 | Throttle valve for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210563740.7A CN103883664A (en) | 2012-12-21 | 2012-12-21 | Throttle valve for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103883664A true CN103883664A (en) | 2014-06-25 |
Family
ID=50952725
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210563740.7A Pending CN103883664A (en) | 2012-12-21 | 2012-12-21 | Throttle valve for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103883664A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106837908A (en) * | 2017-03-24 | 2017-06-13 | 中国北方车辆研究所 | High-power damper valve |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3751023A (en) * | 1970-09-02 | 1973-08-07 | J Thomas | Suspension devices |
| US20060163427A1 (en) * | 2003-01-10 | 2006-07-27 | Messier-Dowty Sa | Landing gear strut damper, and gear with independent struts comprising same |
| CN101012007A (en) * | 2007-02-06 | 2007-08-08 | 南京航空航天大学 | Two-stage series connection two-chamber buffer |
| CN101016926A (en) * | 2007-02-06 | 2007-08-15 | 南京航空航天大学 | Undercarriage bumper having inner flow regulating valve |
| CN102060106A (en) * | 2010-12-21 | 2011-05-18 | 南京航空航天大学 | Buffer landing leg for planet detector |
| CN102198866A (en) * | 2011-04-22 | 2011-09-28 | 南京航空航天大学 | Telescopic landing leg expanding mechanism for planetary probe |
-
2012
- 2012-12-21 CN CN201210563740.7A patent/CN103883664A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3751023A (en) * | 1970-09-02 | 1973-08-07 | J Thomas | Suspension devices |
| US20060163427A1 (en) * | 2003-01-10 | 2006-07-27 | Messier-Dowty Sa | Landing gear strut damper, and gear with independent struts comprising same |
| CN101012007A (en) * | 2007-02-06 | 2007-08-08 | 南京航空航天大学 | Two-stage series connection two-chamber buffer |
| CN101016926A (en) * | 2007-02-06 | 2007-08-15 | 南京航空航天大学 | Undercarriage bumper having inner flow regulating valve |
| CN102060106A (en) * | 2010-12-21 | 2011-05-18 | 南京航空航天大学 | Buffer landing leg for planet detector |
| CN102198866A (en) * | 2011-04-22 | 2011-09-28 | 南京航空航天大学 | Telescopic landing leg expanding mechanism for planetary probe |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106837908A (en) * | 2017-03-24 | 2017-06-13 | 中国北方车辆研究所 | High-power damper valve |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107339360B (en) | A kind of undercarriage buffer | |
| KR101348135B1 (en) | Shock absorber for spacecraft lander | |
| CN108974333B (en) | Full-oil buffer and compensation device | |
| CN203614510U (en) | Hydraulic buffering oil cylinder | |
| CN203836056U (en) | Buffer for helicopter | |
| CN202245751U (en) | Hydraulic damping device of bridge crane | |
| CN206802183U (en) | Adjustable damping device | |
| CN101293567A (en) | Overhang spindle bumper absorber for airliner undercart | |
| CN102602534A (en) | Shimmy damping device for landing gear | |
| CN201273355Y (en) | Self-protecting variable-damping hydraulic buffer | |
| CN104930015A (en) | Oil gas type load reduction pneumatic actuator cylinder and load reduction method thereof | |
| CN105020316A (en) | Undercarriage buffer | |
| CN105626738A (en) | Aircraft undercarriage mixed damping method | |
| CN2835699Y (en) | Hydro-pneumatic buffer | |
| CN103883664A (en) | Throttle valve for helicopter | |
| CN104500636A (en) | Sensing variable-frequency vibration absorber | |
| CN201723641U (en) | Novel magnetorheological fluid shock absorber | |
| CN204403249U (en) | A kind of double-acting shock absorber | |
| CN109296586A (en) | A kind of hydraulic cylinder | |
| CN203611678U (en) | Integrated inert suspension fork for vehicle | |
| CN110043596A (en) | A kind of thrust bearing energy-consumption damper peculiar to vessel and its assembly method | |
| CN205837180U (en) | A kind of buffering undercarriage | |
| CN204512282U (en) | A kind of two rod hydraulic damper | |
| CN204419758U (en) | A kind of buffering hydraulic cylinder | |
| CN208719248U (en) | A kind of general-purpose aircraft spring hydraulic composite damping device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140625 |