CN202083541U - Follow-up loading structure for airplane flap test - Google Patents

Follow-up loading structure for airplane flap test Download PDF

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Publication number
CN202083541U
CN202083541U CN2011200009296U CN201120000929U CN202083541U CN 202083541 U CN202083541 U CN 202083541U CN 2011200009296 U CN2011200009296 U CN 2011200009296U CN 201120000929 U CN201120000929 U CN 201120000929U CN 202083541 U CN202083541 U CN 202083541U
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CN
China
Prior art keywords
loading
actuator
coaster
guide rail
load
Prior art date
Application number
CN2011200009296U
Other languages
Chinese (zh)
Inventor
郑牧
薛伟松
佟强
董巍
王剑峰
赵春兰
李威
Original Assignee
哈尔滨飞机工业集团有限责任公司
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Publication date
Application filed by 哈尔滨飞机工业集团有限责任公司 filed Critical 哈尔滨飞机工业集团有限责任公司
Priority to CN2011200009296U priority Critical patent/CN202083541U/en
Application granted granted Critical
Publication of CN202083541U publication Critical patent/CN202083541U/en

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Abstract

The utility model relates to a loading structure, particularly to an airplane flap follow-up loading structure. The follow-up loading structure adopts a loading actuator dual-end double-pulley design, comprising a loading tool, a guide track, pulleys, a loading actuator, and a position-adjusting actuator, wherein the position-adjusting actuator is used for driving pulleys to move along the guide track, thereby changing the position of the loading actuator to make the loading actuator cooperatively move with the flap; and the loading tool is used for conveying the output force of the loading actuator to the flap, thus to realize the loading to the flap. The follow-up loading structure can be applied to the airplane flap test of fixed loading and fixed loading position, and can also be applied to the airplane flap test having complicated moving track which requires the change of loading and loading position.

Description

A kind of aircraft flap test servo-actuated loading structure
Technical field
The utility model relates to a kind of loading structure, particularly relates to a kind of aircraft flap servo-actuated loading structure.
Background technology
At present, domesticly carry out loading structure that aircraft flap test uses and only do separately and retreat or load when rotatablely moving, or put down, load when being retracted into special angle at wing flap at wing flap.This loading structure can not also will carry out servo-actuated, loading in real time to the wing flap with compound movement track of a LRO Lateral Runout simultaneously to retreating and rotatablely moving, and can not change the position of load(ing) point in loading procedure with the wing flap motion.
The utility model content
The purpose of this utility model is: a kind of aircraft flap test servo-actuated loading structure is provided, test load size, direction and load(ing) point position are changed with wing flap compound movement track in the wing flap running time on request, guarantee that test load applies accurately, in real time, improves test efficiency simultaneously.
The technical solution of the utility model: the utility model comprises wing flap 2, loading frock 3, guide rail 1, coaster 1, position adjustment actuator 1, loads actuator 7, coaster 28, position adjustment actuator 29, guide rail 2 10, load frock 3 and be suspended on the wing flap 2, load and use loading load thing between frock 3 and the wing flap 2; Draw loading actuator 7 residing positions in the wing flap motion process by the relative position of drawing wing flap 2 movement locus and loaded load; and determine guide rail 1 according to this position; putting highly of guide rail 2 10; direction reaches and loads the angle between the string of a musical instrument face 1; guide rail 1 is fixedlyed connected with loading frock 3; coaster 1 is suspended on the cantilever of guide rail 1; the position is adjusted actuator 1 and is fixed on the guide rail 1; but the position is adjusted the bolt of use free adjustment direction between actuator 1 and the coaster 1 and is connected; the position is adjusted on the actuator 29 and is with the briquetting of monaural to fixedly connected on the side ears joint and guide rail 2 10; position adjustment actuator 29 opposite side ears joints are fixedlyed connected with coaster 28; loading to use between actuator 7 lower ends and the coaster 28 protects bolt to be connected; the use LOAD CELLS is connected between the upper end that loads actuator 7 and the coaster 1; adjust actuator 1 by the position; the position is adjusted actuator 29 and is adjusted coaster 1; coaster 28 positions make loading actuator 7 vertical with loading string of a musical instrument face 1.
Loading frock 3 in the utility model can be suspended on the wing flap 2 by machine made aluminum clamp with hook; Load and to use wooden unit between frock 3 and the wing flap 2 as loading the load thing.
The beneficial effects of the utility model: the utility model is a kind of can the wing flap with compound movement track the loading in real time with the wing flap cooperative motion, and changes the aircraft flap servo-actuated loading structure of load(ing) point position according to the variation of wing flap movement locus.Adopt the fixing mode of aluminum clamp will load frock and be connected, make clamp have overload protection function wing flap with wing flap; Adopt the loading structure that loads the sister block design of actuator two ends to satisfy the loaded load of aircraft flap test and the requirement that the load(ing) point position changes with the wing flap movement locus, realize in the wing flap running time, finishing the purpose of loading, improved test efficiency.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
The 1st, load string of a musical instrument face, the 2nd, wing flap, the 3rd, load frock, the 4th, guide rail one, 10th, guide rail two, 5th, coaster one, 8th, coaster two, 6th, actuator one, 9th is adjusted in the position, and actuator two, 7th is adjusted in the position, loads actuator.
Embodiment
Below with reference to accompanying drawing technical solutions of the utility model are further described.
1) wing flap test servo-actuated loading structure annexation
Mainly actuator 1 is adjusted in frock 3, guide rail 1, guide rail 2 10, coaster 1, coaster 28, loading actuator 7 and position to the servo-actuated loading structure, the position is adjusted actuator 29 and formed by loading.At first will load frock 3 and be suspended on the wing flap 2, and load and use wooden unit between frock 3 and the wing flap 2 as loading the load thing by machine made aluminum clamp with hook.Draw by the relative position of drawing wing flap movement locus and loaded load again and load the residing position of actuator in the wing flap motion process, and according to this position determine guide rail one 4,10 put height, direction and and loading string of a musical instrument face 1 between angle.Use bolt that guide rail 1 is fixedlyed connected with loading frock 3 then; Coaster 1 is suspended on the cantilever of guide rail 1; Using bolt that actuator 1 is adjusted in the position is fixed on the guide rail 1; But the bolt that uses the free adjustment direction is adjusted actuator 1 with the position and is connected with coaster 1, produces to a certain degree malalignment to allow position adjustment actuator 1 and coaster 1 in motion process.Use bolt the position to be adjusted on the actuator 29 briquetting of band monaural is connected on the side ears joint and guide rail 2 10 then; its opposite side ears joint is connected with coaster 28 with bolt; coaster 28 can not deviate from from guide rail 2 10 both sides in motion process, can only deviate from (this effect can protect wing flap not to be subjected to downward pulling force) from guide rail 2 10 tops.The lower end of using a kind of bolt that can rupture automatically under certain shearing action (hereinafter to be referred as the protection bolt) will load actuator 7 at last is connected with coaster 28, and the upper end of using LOAD CELLS will load actuator 7 is connected with coaster 1.Adjust the position that actuator 29 is adjusted coasters 1, coaster 28 by position adjustment actuator 1, position, make loading actuator 7 vertical with loading string of a musical instrument face 1.Before coaster 1, coaster 28 are installed, need to be coated with railway grease with the coaster contact portion at guide rail 1, guide rail 2 10, reduce friction.
2) servo-actuated loading structure principle of work
When wing flap moves, the position is adjusted actuator 1 and is driven coasters 1 and move adjusting the load(ing) point position along guide rail 1 in this servo-actuated loading structure, the position adjust actuator 29 drive coasters 28 along guide rail 2 10 move so that loads actuator 7 and loading string of a musical instrument face 1 vertical remain vertical.Like this, the servo-actuated loading structure reaches purpose accurate, that load in real time with the wing flap cooperative motion.In loading procedure, deform, protect bolt fracture or coaster 28 to be pulled away from phenomenon such as guide rail 2 10 test to occur to stop immediately, avoid destroying wing flap if any being fixed on clamp on the wing flap 2.

Claims (3)

1. an aircraft flap is tested the servo-actuated loading structure, comprise wing flap (2), loading frock (3), guide rail one (4), coaster one (5), position adjustment actuator one (6), load actuator (7), coaster two (8), position adjustment actuator two (9), guide rail two (10), load frock (3) and be suspended on the wing flap (2), load and use loading load thing between frock (3) and the wing flap (2); Draw by the relative position of drawing wing flap (2) movement locus and loaded load and to load the residing position of actuator (7) in the wing flap motion process; and determine guide rail one (4) according to this position; putting highly of guide rail two (10); direction reaches and loads the angle between the string of a musical instrument face (1); guide rail one (4) is fixedlyed connected with loading frock (3); coaster one (5) is suspended on the cantilever of guide rail one (4); the position is adjusted actuator one (6) and is fixed on the guide rail one (4); the position adjust actuator one (6) with coaster one (5) but between the bolt of use free adjustment direction be connected; the position is adjusted actuator two (9) last side ears joints and upward is with the briquetting of monaural to fixedly connected with guide rail two (10); position adjustment actuator two (9) opposite side ears joints are fixedlyed connected with coaster two (8); loading to use between actuator (7) lower end and the coaster two (8) protects bolt to be connected; the use LOAD CELLS is connected between the upper end that loads actuator (7) and the coaster one (5); adjust actuator one (6) by the position; the position is adjusted actuator two (9) and is adjusted coaster one (5); coaster two (8) positions make loading actuator (7) vertical with loading string of a musical instrument face (1).
2. aircraft flap test servo-actuated loading structure according to claim 1 is characterized in that loading frock (3) and is suspended on the wing flap (2) by machine made aluminum clamp with hook.
3. aircraft flap test servo-actuated loading structure according to claim 1 and 2 is characterized in that loading and uses wooden unit as loading the load thing between frock (3) and the wing flap (2).
CN2011200009296U 2011-01-05 2011-01-05 Follow-up loading structure for airplane flap test CN202083541U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN2011200009296U CN202083541U (en) 2011-01-05 2011-01-05 Follow-up loading structure for airplane flap test

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN2011200009296U CN202083541U (en) 2011-01-05 2011-01-05 Follow-up loading structure for airplane flap test

Publications (1)

Publication Number Publication Date
CN202083541U true CN202083541U (en) 2011-12-21

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CN2011200009296U CN202083541U (en) 2011-01-05 2011-01-05 Follow-up loading structure for airplane flap test

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Country Link
CN (1) CN202083541U (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103018028A (en) * 2012-12-10 2013-04-03 沈阳中之杰流体控制系统有限公司 Follow-up loading system
CN103033378A (en) * 2012-12-10 2013-04-10 中国飞机强度研究所 Moving-follow constraint device
CN104048874A (en) * 2014-06-24 2014-09-17 西北工业大学 Load follow-up loading system for plane flap reliability test
CN104139868A (en) * 2013-05-10 2014-11-12 中国飞机强度研究所 Path contact protection device for intensity test for movable control surface of airplane structure
CN104697761A (en) * 2013-12-06 2015-06-10 中国飞机强度研究所 Follow-up loading method of movable airfoil
CN104697762A (en) * 2013-12-06 2015-06-10 中国飞机强度研究所 Airplane vertical tail dynamic load following loading test device
CN104925270A (en) * 2015-05-13 2015-09-23 中国飞机强度研究所 Method, torsion load testing system, pressure load testing system and adjustment assembly
CN105021414A (en) * 2014-04-29 2015-11-04 中国飞机强度研究所 Movable wing surface servo loading device
CN105758629A (en) * 2014-12-19 2016-07-13 成都飞机设计研究所 Servo loading method in aircraft strength test
CN107010245A (en) * 2016-01-28 2017-08-04 陕西飞机工业(集团)有限公司 A kind of flap-type rudder surface servo load maintainer
CN107264836A (en) * 2017-07-28 2017-10-20 中国航空工业集团公司西安飞机设计研究所 The a wide range of following loading experimental rig of hatch door and test method
CN108827682A (en) * 2018-06-25 2018-11-16 杭州邦威机电控制工程有限公司 A kind of anti-load(ing) point unstability device of structural test
CN109019397A (en) * 2018-08-20 2018-12-18 中国飞机强度研究所 load support system

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103018028A (en) * 2012-12-10 2013-04-03 沈阳中之杰流体控制系统有限公司 Follow-up loading system
CN103033378A (en) * 2012-12-10 2013-04-10 中国飞机强度研究所 Moving-follow constraint device
CN103033378B (en) * 2012-12-10 2015-10-28 中国飞机强度研究所 A kind of Moving-follow constraint device
CN103018028B (en) * 2012-12-10 2015-07-01 沈阳中之杰流体控制系统有限公司 Follow-up loading system
CN104139868A (en) * 2013-05-10 2014-11-12 中国飞机强度研究所 Path contact protection device for intensity test for movable control surface of airplane structure
CN104139868B (en) * 2013-05-10 2016-04-20 中国飞机强度研究所 A kind of via-contacts fender guard for the movable rudder face strength test of aircaft configuration
CN104697761A (en) * 2013-12-06 2015-06-10 中国飞机强度研究所 Follow-up loading method of movable airfoil
CN104697762A (en) * 2013-12-06 2015-06-10 中国飞机强度研究所 Airplane vertical tail dynamic load following loading test device
CN104697762B (en) * 2013-12-06 2017-09-29 中国飞机强度研究所 Aircraft vertical fin dynamic load following loading experimental rig
CN105021414A (en) * 2014-04-29 2015-11-04 中国飞机强度研究所 Movable wing surface servo loading device
CN104048874A (en) * 2014-06-24 2014-09-17 西北工业大学 Load follow-up loading system for plane flap reliability test
CN105758629A (en) * 2014-12-19 2016-07-13 成都飞机设计研究所 Servo loading method in aircraft strength test
CN105758629B (en) * 2014-12-19 2018-04-03 成都飞机设计研究所 A kind of following loading method in aircraft strength test
CN104925270A (en) * 2015-05-13 2015-09-23 中国飞机强度研究所 Method, torsion load testing system, pressure load testing system and adjustment assembly
CN107010245A (en) * 2016-01-28 2017-08-04 陕西飞机工业(集团)有限公司 A kind of flap-type rudder surface servo load maintainer
CN107264836A (en) * 2017-07-28 2017-10-20 中国航空工业集团公司西安飞机设计研究所 The a wide range of following loading experimental rig of hatch door and test method
CN107264836B (en) * 2017-07-28 2020-04-14 中国航空工业集团公司西安飞机设计研究所 Cabin door large-range follow-up loading test device and test method
CN108827682A (en) * 2018-06-25 2018-11-16 杭州邦威机电控制工程有限公司 A kind of anti-load(ing) point unstability device of structural test
CN109019397A (en) * 2018-08-20 2018-12-18 中国飞机强度研究所 load support system

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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: 20111221

Termination date: 20160105