CN107719642B - A kind of airplane hydraulic pressure mechanical load mechanism - Google Patents
A kind of airplane hydraulic pressure mechanical load mechanism Download PDFInfo
- Publication number
- CN107719642B CN107719642B CN201710817393.9A CN201710817393A CN107719642B CN 107719642 B CN107719642 B CN 107719642B CN 201710817393 A CN201710817393 A CN 201710817393A CN 107719642 B CN107719642 B CN 107719642B
- Authority
- CN
- China
- Prior art keywords
- rocker arm
- spring
- cam
- shell
- 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.)
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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
Abstract
The invention belongs to aircrafts to be mechanically operated by field, especially a kind of airplane hydraulic pressure mechanical load mechanism.The hydraulic machinery control feel simulator is made of shell 1, restraint rocker arm 2, diaphragm 3, spring 4, throttle slide valve 5, piston 6, mandril 7, spring 8, rocker arm 9, rocker arm 10, rocker arm 11, spring 12, cam 13, rocker arm 14, idler wheel 15, shell 17.Overcoming conventional hydraulic machines control feel simulator cannot change with flying speed the shortcomings that change steering force, and can overcome high to each component processing required precision, complicated, the shortcomings that easy clamping stagnation of mechanism etc. easily causes flight safety is coordinated in installation.
Description
Technical field
The invention belongs to be mechanically operated by field, a kind of especially airplane hydraulic pressure mechanical load mechanism.
Background technique
Conventional hydraulic machines control feel simulator be spring rod-pulling type mechanism, the aesthesia provided 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
Cooperation precision has high requirements between the linearity of spring, surface quality and spring and spring base, guide rod.These factors are equal
It will affect steering force.Biggish fit clearance will lead to that work is unstable, and too small gap can generate very big frictional force, and
Easily lead to mechanism clamping stagnation, causes flight safety.
Summary of the invention
Mechanism of the invention overcomes conventional springs rod-pulling type hydraulic machinery control feel simulator, cannot with flying speed change and
The shortcomings that changing steering force, and, installation coordination complexity high to each component processing required precision can be overcome, easy clamping stagnation of mechanism etc. is easy
The shortcomings that causing flight safety.
Technical problems to be solved:
Hydraulic machinery control feel simulator of the invention overcomes conventional whip formula hydraulic machinery control feel simulator, cannot be with 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 causes the shortcomings that flight safety.
Flight control power can be reached to change with flying speed, while solving, installation high to parts machining required precision
Coordinate complicated, the problems such as mechanism easy clamping stagnation, is effectively improved flight quality.
Technical solution:
A kind of airplane hydraulic pressure mechanical load mechanism, comprising: shell (1), restraint rocker arm (2), diaphragm (3), spring A (4), section
It is fluent valve (5), piston (6), mandril (7), spring B (8), rocker arm A (9), rocker arm B (10), rocker arm C (11), spring C (12), convex
Take turns (13), rocker arm D (14), idler wheel (15), shell (17) composition；Wherein, connecting rod (2) and diaphragm (3) be bolted, diaphragm (3)
It is connected with spring A (4) insertion connection, spring A (4) and throttle valve (5) insertion, (13 are bolted, roll for rocker arm E (16) and cam
(15) contact wheel with cam (13), idler wheel (15) is installed on rocker arm B (10) by bolt respectively, on rocker arm C (11), rocker arm C
(11) it is bolted with spring C (12) insertion connection, rocker arm B (10) with rocker arm A (9), rocker arm A (9) and spring B (8) insertion connect
It connects, rocker arm A (9) is contacted with mandril (7).Cam (13), rocker arm A (9), rocker arm B (10), rocker arm C (11), spring B (8), spring C
(12) it is installed on shell (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 cannot
The shortcomings that changing with flying speed and changing steering force, and can overcome to each component processing required precision height, installation is coordinated multiple
It is miscellaneous, easy clamping stagnation of mechanism etc. easily cause flight safety the shortcomings that.
, it is effectively improved flight quality.
Detailed description of the invention
Fig. 1 is hydraulic machinery control feel simulator front view
1 shell, 2 connecting rod, 3 diaphragm, 4 spring A, 5 throttle slide valve, 6 piston, 7 mandril
8 spring B, 9 rocker arm A, 10 rocker arm B, 11 rocker arm C, 12 spring C
13 cam, 14 rocker arm D, 15 idler wheel, 16 rocker arm E, 17 shell
Fig. 2 is hydraulic machinery control feel simulator left view
Fig. 3 is hydraulic machinery control feel simulator top view
Specific embodiment
Present invention is further described in detail with specific embodiment with reference to the accompanying drawing: a kind of airplane hydraulic pressure machinery load
Lotus mechanism, comprising: shell (1), connecting rod (2), diaphragm (3), spring A (4), throttle slide valve (5), piston (6), mandril (7), spring
B (8), rocker arm A (9), rocker arm B (10), rocker arm C (11), spring C (12), cam (13), rocker arm D (14), idler wheel (15), shell
(17) it forms；Wherein, connecting rod (2) and diaphragm (3) are bolted, diaphragm (3) and spring A (4) are embedded in connection, spring A (4) and section
(13 are bolted, idler wheel (15) is contacted with cam (13), idler wheel (15) divides for stream valve (5) insertion connection, rocker arm E (16) and cam
Be not installed on rocker arm B (10) by bolt, on rocker arm C (11), rocker arm C (11) and spring C (12) insertion connection, rocker arm B (10)
It is bolted with rocker arm A (9), rocker arm A (9) is contacted with spring B (8) insertion connection, rocker arm A (9) with mandril (7).Cam (13),
Rocker arm A (9), rocker arm B (10), rocker arm C (11), spring B (8), spring C (12) are installed on shell (17).
Pilot passes motion to idler wheel 15 with moving cam 13 by stepping on rocker arm 16, and rotation rocker arm 10 transmits movement
To rocker arm 9, rocker arm 9 passes motion to mandril 7, and mandril 7 drives hydraulic oil to drive throttle slide valve 5, compressed spring 4, and then incites somebody to action
Movement passes to diaphragm 3, and P1 and P2 difference is caused to change.Rudder face is passed motion to by connecting rod 2 simultaneously.
Meanwhile rudder face ram compression (P1 and P2 difference) variation band dynamic diaphragm 3 and control surface deflection drive under aircraft friction speed
Connecting rod 2, connecting rod 2 drive throttle slide valve 5 with dynamic diaphragm 3,3 compressed spring 4 of diaphragm, and driving hydraulic oil drives mandril 7, and mandril 7 will
Movement passes to rocker arm 9, and rocker arm 9 drives rocker arm 10, passes motion to cam 13 by idler wheel 15, cam 13 drives rocker arm
16, to give pilot control force feeling.
Claims (2)
1. a kind of airplane hydraulic pressure mechanical load mechanism, it is characterised in that: the hydraulic machinery control feel simulator is by shell (1), connecting rod
(2), diaphragm (3), spring A (4), throttle slide valve (5), piston (6), mandril (7), spring B (8), rocker arm A (9), rocker arm B (10),
Rocker arm C (11), spring C (12), cam (13), rocker arm D (14), idler wheel (15), shell (17) composition；Wherein, connecting rod (2) and film
Piece (3) is bolted, diaphragm (3) and spring A (4) are embedded in connection, spring A (4) and throttle slide valve (5) insertion connection, rocker arm E
(16) it is bolted with cam (13), idler wheel (15) is contacted with cam (13), idler wheel (15) is installed on rocker arm B by bolt respectively
(10) and on rocker arm C (11), rocker arm C (11) and spring C (12) insertion connection, rocker arm B (10) and rocker arm A (9) be bolted, shake
Arm A (9) is contacted with spring B (8) insertion connection, rocker arm A (9) with mandril (7)；Cam (13), rocker arm B (10), shakes rocker arm A (9)
Arm C (11), spring B (8), spring C (12) are installed on shell (17).
2. a kind of 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 CN107719642A (en) | 2018-02-23 |
| CN107719642B true 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) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268098B (en) * | 2020-03-17 | 2022-03-11 | 景德镇陶瓷大学 | Aircraft hydraulic machinery load mechanism |
Citations (3)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2993065B1 (en) * | 2012-07-09 | 2014-08-29 | Ratier Figeac Soc | DEVICE FOR CONJUGATION OF EFFORT BETWEEN CONTROL UNITS, STEERING BODY AND AIRCRAFT |
-
2017
- 2017-09-12 CN CN201710817393.9A patent/CN107719642B/en active Active
Patent Citations (3)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107719642A (en) | 2018-02-23 |
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| 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. |
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| CP03 | Change of name, title or address |