CN107719642A - A kind of airplane hydraulic pressure mechanical load mechanism - Google Patents
A kind of airplane hydraulic pressure mechanical load mechanism Download PDFInfo
- Publication number
- CN107719642A CN107719642A CN201710817393.9A CN201710817393A CN107719642A CN 107719642 A CN107719642 A CN 107719642A CN 201710817393 A CN201710817393 A CN 201710817393A CN 107719642 A CN107719642 A CN 107719642A
- Authority
- CN
- China
- Prior art keywords
- rocking arm
- spring
- cam
- housing
- hydraulic pressure
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Control Devices (AREA)
Abstract
The invention belongs to aircraft to be mechanically operated by field, particularly a kind of airplane hydraulic pressure mechanical load mechanism.The hydraulic machinery control feel simulator is made up of housing 1, restraint rocking arm 2, diaphragm 3, spring 4, throttle slide valve 5, piston 6, push rod 7, spring 8, rocking arm 9, rocking arm 10, rocking arm 11, spring 12, cam 13, rocking arm 14, roller 15, housing 17.The shortcomings that overcoming the shortcomings that conventional hydraulic machines control feel simulator can not change with flying speed and change steering force, and, installation coordination complexity high to each component processing required precision, the easy clamping stagnation of mechanism etc. can be overcome easily to trigger flight safety.
Description
Technical field
The invention belongs to be mechanically operated by field, particularly a kind of airplane hydraulic pressure mechanical load mechanism.
Background technology
Conventional hydraulic machines control feel simulator is spring rod-pulling type mechanism, there is provided aesthesia not with flight parameter (H, V, M,
Qc) change, to meet the requirement of the stick force under different flying speeds, and be designed as multiple spring series models, this is hit by a bullet to mechanism
Fit precision has high requirements between the linearity of spring, surface quality and spring and spring base, guide rod.These factors are equal
Steering force can be influenceed.Larger fit clearance can cause work unstable, and too small gap can produce very big frictional force, and
Easily cause mechanism clamping stagnation, trigger flight safety.
The content of the invention
The mechanism of the present invention overcomes conventional springs rod-pulling type hydraulic machinery control feel simulator, it is impossible to flying speed change
The shortcomings that changing steering force, and, installation coordination complexity high to each component processing required precision, the easy clamping stagnation of mechanism etc. can be overcome easily
The shortcomings that triggering flight safety.
Technical problems to be solved：
The hydraulic machinery control feel simulator of the present invention overcomes conventional whip formula hydraulic machinery control feel simulator, it is impossible to flight speed
The shortcomings that degree changes and changes steering force, and can overcome to each component processing required precision height, installation coordination is complicated, and mechanism is easy
Clamping stagnation etc. easily triggers the shortcomings that flight safety.
Flight control power can be reached with flying speed to change, while solve, installation high to parts machining required precision
Coordinate complicated, the problems such as mechanism easy clamping stagnation, be effectively improved flight quality.
Technical scheme：
A kind of airplane hydraulic pressure mechanical load mechanism, including：Housing (1), restraint rocking arm (2), diaphragm (3), spring A (4), section
It is fluent valve (5), piston (6), push rod (7), spring B (8), rocking arm A (9), rocking arm B (10), rocking arm C (11), spring C (12), convex
Take turns (13), rocking arm D (14), roller (15), housing (17) composition；Wherein, connecting rod (2) and diaphragm (3) bolt connection, diaphragm (3)
Connection embedded with spring A (4), spring A (4) connections embedded with choke valve (5), rocking arm E (16) and cam (13 bolt connections, rolling
Wheel (15) contacts with cam (13), roller (15) is installed on rocking arm B (10) by bolt respectively, on rocking arm C (11), rocking arm C
(11) connect with the embedded connections of spring C (12), rocking arm B (10) with rocking arm A (9) bolt connection, rocking arm A (9) and spring B (8) insertion
Connect, rocking arm A (9) contacts with push rod (7).Cam (13), rocking arm A (9), rocking arm B (10), rocking arm C (11), spring B (8), spring C
(12) it is installed on housing (17).
In the hydraulic machinery control feel simulator, spring A, spring B, spring C belong to cylindrical spring.
(iii) beneficial effect
Compared with prior art, overcoming conventional hydraulic machines control feel simulator the beneficial effects of the invention are as follows the mechanism can not
The shortcomings that changing with flying speed and changing steering force, and can overcome and coordinate multiple to each component processing required precision height, installation
It is miscellaneous, easy clamping stagnation of mechanism etc. easily trigger flight safety the shortcomings that.
, it is effectively improved flight quality.
Brief description of the drawings
Fig. 1 is hydraulic machinery control feel simulator front view
The push rod of 1 housing, 2 connecting rod, 3 diaphragm, 4 spring A, 5 throttle slide valves, 6 piston 7
The spring C of 8 spring B, 9 rocking arm A, 10 rocking arm B, 11 rocking arm C 12
The housings of 13 cam, 14 rocking arm D, 15 rollers, 16 rocking arm E 17
Fig. 2 is hydraulic machinery control feel simulator left view
Fig. 3 is hydraulic machinery control feel simulator top view
Specific embodiment
The present invention is described in further detail with embodiment below in conjunction with the accompanying drawings：A kind of airplane hydraulic pressure machinery carries
Lotus mechanism, including：Housing (1), connecting rod (2), diaphragm (3), spring A (4), throttle slide valve (5), piston (6), push rod (7), spring
B (8), rocking arm A (9), rocking arm B (10), rocking arm C (11), spring C (12), cam (13), rocking arm D (14), roller (15), housing
(17) form；Wherein, connecting rod (2) and diaphragm (3) bolt connection, diaphragm (3) connection embedded with spring A (4), spring A (4) and section
Flowing the embedded connection of valve (5), rocking arm E (16) and cam, (13 bolt connections, roller (15) contact with cam (13), roller (15) point
Rocking arm B (10) is not installed on by bolt, on rocking arm C (11), the embedded connections of rocking arm C (11) and spring C (12), rocking arm B (10)
Contacted with rocking arm A (9) bolt connection, rocking arm A (9) connections embedded with spring B (8), rocking arm A (9) with push rod (7).Cam (13),
Rocking arm A (9), rocking arm B (10), rocking arm C (11), spring B (8), spring C (12) are installed on housing (17).
Pilot passes motion to roller 15 by stepping on rocking arm 16 with moving cam 13, rotates rocking arm 10, transmits motion
To rocking arm 9, rocking arm 9 passes motion to push rod 7, and push rod 7 drives hydraulic oil to drive throttle slide valve 5, compression spring 4, and then incites somebody to action
Motion passes to diaphragm 3, and causes P1 and P2 differences to change.Rudder face is passed motion to by connecting rod 2 simultaneously.
Meanwhile rudder face ram compression (P1 and P2 differences) change band dynamic diaphragm 3 under aircraft friction speed, and control surface deflection drive
Connecting rod 2, connecting rod 2 compression spring 4 of diaphragm 3, drive throttle slide valve 5, driving hydraulic oil drives push rod 7, and push rod 7 will with dynamic diaphragm 3
Motion passes to rocking arm 9, and rocking arm 9 passes motion to cam 13, cam 13 is with motion rocker arm with motion rocker arm 10 by roller 15
16, so as to give pilot control force feeling.
Claims (2)
- A kind of 1. airplane hydraulic pressure mechanical load mechanism, it is characterised in that：The hydraulic machinery control feel simulator is by housing (1), connecting rod (2), diaphragm (3), spring A (4), throttle slide valve (5), piston (6), push rod (7), spring B (8), rocking arm A (9), rocking arm B (10), Rocking arm C (11), spring C (12), cam (13), rocking arm D (14), roller (15), housing (17) composition；Wherein, connecting rod (2) and film The connection embedded with spring A (4) of piece (3) bolt connection, diaphragm (3), spring A (4) connections embedded with choke valve (5), rocking arm E (16) Contacted with cam (13) bolt connection, roller (15) with cam (13), roller (15) is installed on rocking arm B (10) by bolt respectively With on rocking arm C (11), the embedded connection of rocking arm C (11) and spring C (12), rocking arm B (10) and rocking arm A (9) bolt connection, rocking arm A (9) connection embedded with spring B (8), rocking arm A (9) contact with push rod (7)；Cam (13), rocking arm A (9), rocking arm B (10), rocking arm C (11), spring B (8), spring C (12) are installed on housing (17).
- A kind of 2. airplane hydraulic pressure mechanical load mechanism according to claim 1, it is characterised in that：The hydraulic machinery load In mechanism, the spring A (4), spring B (8), spring C (12) belong to cylindrical spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817393.9A CN107719642B (en) | 2017-09-12 | 2017-09-12 | A kind of airplane hydraulic pressure mechanical load mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710817393.9A CN107719642B (en) | 2017-09-12 | 2017-09-12 | A kind of airplane hydraulic pressure mechanical load mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107719642A true CN107719642A (en) | 2018-02-23 |
| CN107719642B CN107719642B (en) | 2019-11-15 |
Family
ID=61206061
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710817393.9A Active CN107719642B (en) | 2017-09-12 | 2017-09-12 | A kind of airplane hydraulic pressure mechanical load mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107719642B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268098A (en) * | 2020-03-17 | 2020-06-12 | 景德镇陶瓷大学 | Aircraft hydraulic machinery load mechanism |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201619690U (en) * | 2010-04-09 | 2010-11-03 | 江西洪都航空工业集团有限责任公司 | Dual-spring double-gradient load mechanism |
| CN102001444B (en) * | 2010-11-19 | 2014-06-11 | 陕西飞机工业（集团）有限公司 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
| US20150191241A1 (en) * | 2012-07-09 | 2015-07-09 | Ratier Figeac | Device for combining force among control units, control unit and aircraft |
| CN105270606A (en) * | 2015-10-10 | 2016-01-27 | 中航飞机股份有限公司西安飞机分公司 | Double-set rigid control system for aircraft |
-
2017
- 2017-09-12 CN CN201710817393.9A patent/CN107719642B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201619690U (en) * | 2010-04-09 | 2010-11-03 | 江西洪都航空工业集团有限责任公司 | Dual-spring double-gradient load mechanism |
| CN102001444B (en) * | 2010-11-19 | 2014-06-11 | 陕西飞机工业（集团）有限公司 | Neutral position adjustment device of flight control system and neutral position setting method thereof |
| US20150191241A1 (en) * | 2012-07-09 | 2015-07-09 | Ratier Figeac | Device for combining force among control units, control unit and aircraft |
| CN105270606A (en) * | 2015-10-10 | 2016-01-27 | 中航飞机股份有限公司西安飞机分公司 | Double-set rigid control system for aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268098A (en) * | 2020-03-17 | 2020-06-12 | 景德镇陶瓷大学 | Aircraft hydraulic machinery load mechanism |
| CN111268098B (en) * | 2020-03-17 | 2022-03-11 | 景德镇陶瓷大学 | Aircraft hydraulic machinery load mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107719642B (en) | 2019-11-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103171531A (en) | Active brake pedal travel simulator and control method thereof | |
| CN201950125U (en) | Hydraulic revolving-riveting machine | |
| CN103223729A (en) | Lever push-out type finishing press | |
| CN107719642A (en) | A kind of airplane hydraulic pressure mechanical load mechanism | |
| CN103925404B (en) | A kind of actuating motor directly drives the piston type pneumatic proportional pressure-reducing valve of end cam | |
| CN103277275B (en) | Electric controlled multi-functional compositely proportional axial variable displacement plunger pump | |
| CN105736779B (en) | A kind of metering valve component | |
| CN203784007U (en) | Single piston rod symmetric digital servo hydraulic cylinder | |
| CN106050760B (en) | Four piston air water pressurized cylinders | |
| CN102588369B (en) | Numerical control hydraulic control unit | |
| CN103291575A (en) | Electric proportional variable axial plunger pump | |
| CN103016835B (en) | Forward low-friction unloading gear for reducing valve and reducing valve | |
| CN103195585A (en) | Anti-surge valve | |
| CN202971930U (en) | Mechanical sealing device | |
| CN204553416U (en) | Non-locating formula hydraulic throttle damping mechanism | |
| CN103925399A (en) | Diaphragm-type pneumatic proportional pressure reducing valve of edge cam driven by servo motor directly | |
| CN201471769U (en) | Flywheel brake of press machine | |
| CN104747536B (en) | Non-locating formula hydraulic throttle buffer gear | |
| CN103573616B (en) | The variable cylinder structure of plunger pump | |
| CN203272037U (en) | Electronic control proportional variable axial plunger pump | |
| CN104454787A (en) | Steering engine hydraulic state monitoring system and monitoring method | |
| CN203381222U (en) | Stroke adjusting device of press machine air cushion | |
| CN202250554U (en) | Impact type water turbine spray needle pressureless feedback device | |
| CN108458150B (en) | Electric straight-travel valve actuator | |
| CN2644817Y (en) | Pneumatic rack style actuating element |
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 | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
|
| CP03 | Change of name, title or address |