CN105806411A - Detection device and method for folding and unfolding of rotary folding wing of airplane - Google Patents
Detection device and method for folding and unfolding of rotary folding wing of airplane Download PDFInfo
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- CN105806411A CN105806411A CN201610224321.9A CN201610224321A CN105806411A CN 105806411 A CN105806411 A CN 105806411A CN 201610224321 A CN201610224321 A CN 201610224321A CN 105806411 A CN105806411 A CN 105806411A
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- folding
- wing
- detection
- outer wing
- unfolding
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention discloses a detection device and method for folding and unfolding of a rotary folding wing of an airplane.The detection device and method are used for solving the technical problem of poor practicability of an existing detection device for folding and unfolding of a rotary folding wing of an airplane.According to the technical scheme, the detection device comprises a movable working ladder, a wingtip folding in-place detection table, a central wing false part, a laser tracker, double guide rails and three-coordinate posture adjusting POGO columns.The central wing false part comprises a middle-outer wing false part, a central wing false part upper connector and a central wing false part bracket.By means of the detection device and method, a planned folding path can be detected, the folding and unfolding properties of the folding wing can be accurately acquired, reliable data can be provided for design of a folding mechanism to serve as a practical design basis, and practicability is high, wherein the folding and unfolding properties include the wing surface appearance accuracy and jump in the unfolded state of the folding wing, the folding and unfolding stability, the multi-intersection point insertion and connection robustness, the wingtip in-place condition in the folded state and the like.
Description
Technical field
The present invention relates to a kind of aircraft rotary folding wing folding and unfolding detecting device, further relate to a kind of aircraft rotary folding wing folding and unfolding detection method.
Background technology
Rotary folding wing aircraft takes up room little owing to parking, and is widely used in carrier arming.Owing to the folding and unfolding number of times of wing-folding is frequent, the requirement of strength at folding position is high, simultaneously folding and unfolding limited space, therefore, carries out detecting to the properties in wing-folding path, folding and retraction process and verifies very necessary.Folding wings is divided into outer wing and middle outer wing, and middle outer wing is connected fixing with central wing, and outer wing can rotate folding by particular organization.
Document 1 Chinese invention patent of CN104309797A " application publication number be " discloses a kind of light aerocraft single-blade list shaft foldable scheme, this folding scheme is by calculating folding wings rotating shaft locus in whole rotary course, and constantly adjust structure parting surface position with prevent interfere, finally give rational folding scheme.But the program can not obtain the folding scheme of the fixed wing of structure parting surface.Meanwhile, still not for the detecting device of various performance parameter tests in aircraft folding wings folding and unfolding process in existing patent.
Document 2 " the design analysis (paper) of a kind of high mounted wing list shaft foldable organization plan " is when a kind of aircraft folding wings of design, first, pass through theory analysis, the method adopting front and rear edge segmentation cutting, the vertical plane cutting of leading edge of a wing rotating shaft, rear end adopts tangential vertical plane to cut, and obtains internal and external section two parts of wing；And then use DMU module in CATIA to carry out the motion simulation of fold mechanism, confirm that structure is without interference.But emulation experiment can not replace actually detected completely, reality there are many factor emulation experiments do not account for；It addition, this emulation experiment is also without considering whether wing interference and wing with ground folds and put in place.Therefore various performance parameters can not be provided for manufacturing and designing of folding wings.
Summary of the invention
In order to overcome the deficiency of existing aircraft rotary folding wing folding and unfolding detecting device poor practicability, the present invention provides a kind of aircraft rotary folding wing folding and unfolding detecting device and method.Detecting device includes active operation ladder, wingtip folding put in place monitor station, central wing bogusware, laser tracker, biserial guide rail and three coordinate posture adjustment POGO posts.Described central wing bogusware includes middle outer wing bogusware, central wing bogusware upper connector and central wing bogusware bracket.The present invention can carry out planning folding path detection and accurately obtain folding wings folding and unfolding characteristic, insert and be connected under robustness and collapsed state wingtip and put in place situation etc. such as the aerofoil profile accuracy under folding wings deployed condition and jump, folding and retraction stability, many intersection points, design for fold mechanism provides infallible data as actual design foundation, practical.
The technical solution adopted for the present invention to solve the technical problems is: a kind of aircraft rotary folding wing folding and unfolding detecting device, is characterized in: include removable outer wing shape-keeping frame 1, active operation ladder 2, wingtip folding put in place monitor station 3, central wing bogusware, laser tracker 7, biserial guide rail 8 and three coordinate posture adjustment POGO posts 9.Described central wing bogusware includes middle outer wing bogusware 4, central wing bogusware upper connector 5 and central wing bogusware bracket 6.Being furnished with leveling foundation bolt 10 bottom central wing bogusware bracket 6, leveling foundation bolt 10 is as the load-carrying construction of wing；Three coordinate posture adjustment POGO posts 9 are positioned on biserial guide rail 8, and can move along biserial guide rail 8.The folding laser detection head 11 that puts in place of wingtip is installed on folding monitor station 3 upper end that puts in place, is used for detecting whether wing is folding puts in place, and described removable wing shape-keeping frame 1 is for the outer wing 16 of the transport of folded wing.
A kind of aircraft rotary folding wing folding and unfolding detection method, is characterized in comprising the following steps:
Step one, active operation ladder 2, wingtip folding put in place monitor station 3, middle outer wing bogusware 4, central wing bogusware upper connector 5, central wing bogusware bracket 6, laser tracker 7 and three coordinate posture adjustment POGO posts 9 are positioned over appointment position, meanwhile, three coordinate posture adjustment POGO posts 9 and laser tracker 7 self-inspection and calibration.
The outer wing 16 of folding wings is transported and puts in place by step 2, the removable wing shape-keeping frame 1 of use, on outer wing 16 to the three coordinate posture adjustment POGO post 9 of lifting folding wings, the outer wing 16 of folding wings is carried out profile measurement.
Step 3, the target of laser tracker 7 is directed at the outer wing 16 of folding wings, utilizes laser tracker 7 to scan target point, outer wing 16 spatial pose of folding wings is detected in real time, instruct outer wing 16 posture adjustment to folding wings of the three coordinate posture adjustment POGO posts 9.
Step 4, wing-folding position rotary gemel jaw 13 involutory with rotary gemel auricle 12, rotating dog inserts；Four bearing jaws 15 are involutory with four bearing auricles 14 respectively, and double action cylinder is locked.
Step 5, outer wing 16 to folding wings carry out profile measurement, and the outer wing 16 of folding wings carries out stress mornitoring and jump detection with the involutory position of central wing；Stress monitoring system is used rotating shaft stress to be measured in real time and feeds back.
Step 6, active operation ladder 2, three coordinate posture adjustment POGO post 9 are withdrawn, and wing rotates pressurized strut inspection, prepare folding and retraction detection.
Step 7, by path planning unilateral outer wing 16 carried out repeatedly folding and retraction detection；Folding and unfolding process carries out interference checking, stress detect in real time and tachometric survey；Carry out opposite joint and the jump detection of outer wing 16 and middle outer wing docking site in the deployed state；Carry out the detection of wingtip position in a folded configuration.
Step 8, bilateral outer wing is carried out synchronize folding and unfolding detection, equally, inspection record various performance parameters.
Step 9, under wing deployed condition, three coordinate posture adjustment POGO posts 9 and wing shape-keeping frame 1 are in place, open double action cylinder and rotating dog, lift outer wing 16 undercarriage；
Step 10, detection record, analysis, process data, form examining report.
Described folding and retraction detection includes, and carries out repeatedly unilateral outer wing folding and retraction detection by path planning, by means checking path plannings such as stress mornitoring, interference checking, tachometric surveys；The measurement of aerofoil profile accuracy under folding wings deployed condition, jump and established angle；The insertion of the intersection point pin in many intersection points folding and retraction process and connection robustness detection；Under outer wing folded state, wingtip puts in place the detection of situation；Equally, repeatedly bilateral outer wing synchronous folding folding and unfolding detection is carried out.
The invention has the beneficial effects as follows: detecting device includes active operation ladder, wingtip folding put in place monitor station, central wing bogusware, laser tracker, biserial guide rail and three coordinate posture adjustment POGO posts.Described central wing bogusware includes middle outer wing bogusware, central wing bogusware upper connector and central wing bogusware bracket.The present invention can carry out planning folding path detection and accurately obtain folding wings folding and unfolding characteristic, insert and be connected under robustness and collapsed state wingtip and put in place situation etc. such as the aerofoil profile accuracy under folding wings deployed condition and jump, folding and retraction stability, many intersection points, practical.
The present invention adopts the apparatus and method simulating true folded wing folding and unfolding, it is possible to the effective measurement folding wings each characterisitic parameter in folding and unfolding process, including the measurement of the aerofoil profile accuracy under folding wings deployed condition, jump and established angle；Speed relation over time is launched/packed up to folding wings folding angles, folding wings；Investigate after folding wings folding and unfolding puts in place and can normally lock；The constructive interference of fold domain, fold mechanism fatigue properties；Can comprehensively simulating folding wings folding and unfolding process thus optimizing folding and unfolding scheme, the design for fold mechanism provides infallible data as actual design foundation.
The present invention is described in detail below in conjunction with drawings and Examples.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft rotary folding wing folding and unfolding detecting device of the present invention.
Fig. 2 is the overall enlarged drawing of central wing bogusware part in Fig. 1.
Fig. 3 is the enlarged drawing of removable wing shape-keeping frame in Fig. 1.
Fig. 4 is the enlarged drawing that in Fig. 1, wingtip folds into a monitor station.
Fig. 5 is that in Fig. 1, cut sth. askew the overall enlarged drawing of rib fork ear portions in folding position.
Fig. 6 is that in Fig. 1, three coordinate posture adjustment POGO posts carry out supported at three point posture adjustment enlarged diagram.
Fig. 7 is the design sketch that mono-/bis-side wing is folding on monitor station.
In figure, 1-may move wing shape-keeping frame, 2-active operation ladder, the folding monitor station that puts in place of 3-wingtip, outer wing bogusware in 4-, 5-central wing bogusware upper connector, 6-central wing bogusware bracket, 7-laser tracker, 8-biserial guide rail, 9-tri-coordinate posture adjustment POGO post, 10-leveling foundation bolt, the folding laser detection head that puts in place of 11-, 12-rotary gemel auricle, 13-rotary gemel jaw, 14-bearing auricle, 15-bearing jaw, 16-outer wing.
Detailed description of the invention
With reference to Fig. 1-7.Aircraft rotary folding wing folding and unfolding detecting device of the present invention includes removable outer wing shape-keeping frame 1, active operation ladder 2, wingtip folding put in place monitor station 3, central wing bogusware, laser tracker 7, biserial guide rail 8 and three coordinate posture adjustment POGO posts 9.Described central wing bogusware includes middle outer wing bogusware 4, central wing bogusware upper connector 5 and central wing bogusware bracket 6.Leveling foundation bolt 10 it is furnished with bottom central wing bogusware bracket 6, the central wing box of simulation, middle outer wing and fuselage spatial attitude, and as the main load-carrying construction of wing；Three coordinate posture adjustment POGO posts 9 are positioned on biserial guide rail 8, for supporting outer wing in transport and posture adjustment process；And for transporting the removable wing shape-keeping frame 1 with conformal effect；The folding laser detection head 11 that puts in place of wingtip is installed on folding monitor station 3 upper end that puts in place, is used for detecting whether wing is folding puts in place.
Above-mentioned folding and unfolding detecting device also includes the biserial guide rail 8 for placing three coordinate posture adjustment POGO posts 9, and the base of three coordinate posture adjustment POGO posts 9 is connected with biserial guide rail 8, and accurately can move along biserial guide rail 8.
Specifically comprising the following steps that of a kind of aircraft rotary folding wing folding and unfolding detection method
Step one, active operation ladder 2, wingtip folding put in place monitor station 3, middle outer wing bogusware 4, central wing bogusware upper connector 5, central wing bogusware bracket 6, laser tracker 7 and three coordinate posture adjustment POGO posts 9 are positioned over appointment position, meanwhile, three coordinate posture adjustment POGO posts 9 and laser tracker 7 self-inspection and calibration.
The outer wing 16 of folding wings is transported and puts in place by step 2, the removable wing shape-keeping frame 1 of use, on outer wing 16 to the three coordinate posture adjustment POGO post 9 of lifting folding wings, the outer wing 16 of folding wings is carried out profile measurement.
Step 3, the target of laser tracker 7 is directed at the outer wing 16 of folding wings, utilizes laser tracker 7 to scan target point, outer wing 16 spatial pose of folding wings is detected in real time, instruct outer wing 16 posture adjustment to folding wings of the three coordinate posture adjustment POGO posts 9.
Step 4, wing-folding position rotary gemel jaw 13 involutory with rotary gemel auricle 12, rotating dog inserts；Four bearing jaws 15 are involutory with four bearing auricles 14 respectively, and double action cylinder is locked.
Step 5, outer wing 16 to folding wings carry out profile measurement, and the outer wing 16 of folding wings carries out stress mornitoring and jump detection with the involutory position of central wing；Stress monitoring system is used rotating shaft stress to be measured in real time and feeds back.
Step 6, active operation ladder 2, three coordinate posture adjustment POGO post 9 are withdrawn, and wing rotates pressurized strut inspection, prepare folding and retraction detection.
Step 7, by path planning unilateral outer wing 16 carried out repeatedly folding and retraction detection；Folding and unfolding process carries out interference checking, stress detect in real time and tachometric survey；Carry out opposite joint and the jump detection of outer wing 16 and middle outer wing docking site in the deployed state；Carry out the detection of wingtip position in a folded configuration.
Step 8, bilateral outer wing is carried out synchronize folding and unfolding detection, equally, inspection record various performance parameters.
Step 9, under wing deployed condition, three coordinate posture adjustment POGO posts 9 and wing shape-keeping frame 1 are in place, open double action cylinder and rotating dog, lift outer wing 16 undercarriage；
Step 10, detection record, analysis, process data, form examining report.
Described folding and retraction detection includes, and carries out repeatedly unilateral outer wing folding and retraction detection by path planning, by means checking path plannings such as stress mornitoring, interference checking, tachometric surveys；The measurement of aerofoil profile accuracy under folding wings deployed condition, jump and established angle；The insertion of the intersection point pin in many intersection points folding and retraction process and connection robustness detection；Under outer wing folded state, wingtip puts in place the detection of situation；Equally, repeatedly bilateral outer wing synchronous folding folding and unfolding detection is carried out.
Claims (3)
1. an aircraft rotary folding wing folding and unfolding detecting device, it is characterised in that: include removable outer wing shape-keeping frame (1), active operation ladder (2), wingtip folding put in place monitor station (3), central wing bogusware, laser tracker (7), biserial guide rail (8) and three coordinates posture adjustment POGO post (9)；Described central wing bogusware includes middle outer wing bogusware (4), central wing bogusware upper connector (5) and central wing bogusware bracket (6)；Central wing bogusware bracket (6) bottom is furnished with leveling foundation bolt (10), and leveling foundation bolt (10) is as the load-carrying construction of wing；Three coordinates posture adjustment POGO post (9) are positioned on biserial guide rail (8), and can be mobile along biserial guide rail (8)；The folding laser detection head (11) that puts in place of wingtip is installed on folding monitor station (3) upper end that puts in place, for detecting, whether wing is folding puts in place, and described removable wing shape-keeping frame (1) is for the outer wing (16) of the transport of folded wing.
2. aircraft rotary folding wing folding and unfolding detection method described in a claim 1, it is characterised in that comprise the following steps:
Step one, active operation ladder (2), wingtip folding put in place monitor station (3), middle outer wing bogusware (4), central wing bogusware upper connector (5), central wing bogusware bracket (6), laser tracker (7) and three coordinates posture adjustment POGO post (9) are positioned over appointment position, meanwhile, three coordinates posture adjustment POGO post (9) and laser tracker (7) self-inspection and calibration；
The outer wing (16) of folding wings is transported and puts in place by step 2, the removable wing shape-keeping frame (1) of use, the outer wing (16) of folding wings, to three coordinates posture adjustment POGO post (9), is carried out profile measurement by the outer wing (16) of lifting folding wings；
Step 3, the target of laser tracker (7) is directed at the outer wing (16) of folding wings, utilize laser tracker (7) scanning target point, outer wing (16) spatial pose of folding wings is detected in real time, instructs outer wing (16) posture adjustment to folding wings of three coordinates posture adjustment POGO post (9)；
Step 4, wing-folding position rotary gemel jaw (13) and rotary gemel auricle (12) involutory, rotating dog inserts；Four bearing jaws (15) are involutory with four bearing auricles (14) respectively, and double action cylinder is locked；
Step 5, outer wing (16) to folding wings carry out profile measurement, and the outer wing (16) of folding wings carries out stress mornitoring and jump detection with the involutory position of central wing；Stress monitoring system is used rotating shaft stress to be measured in real time and feeds back；
Step 6, active operation ladder (2), three coordinates posture adjustment POGO post (9) are withdrawn, and wing rotates pressurized strut inspection, prepare folding and retraction detection；
Step 7, by path planning, unilateral outer wing (16) is carried out repeatedly folding and retraction detection；Folding and unfolding process carries out interference checking, stress detect in real time and tachometric survey；Carry out opposite joint and the jump detection of outer wing (16) and middle outer wing docking site in the deployed state；Carry out the detection of wingtip position in a folded configuration；
Step 8, bilateral outer wing is carried out synchronize folding and unfolding detection, equally, inspection record various performance parameters；
Step 9, under wing deployed condition, three coordinates posture adjustment POGO post (9) and wing shape-keeping frame (1) are in place, open double action cylinder and rotating dog, lift outer wing (16) undercarriage；
Step 10, detection record, analysis, process data, form examining report.
3. aircraft rotary folding wing folding and unfolding detection method according to claim 2, it is characterized in that: described folding and retraction detection includes, unilateral outer wing folding and retraction detection is carried out repeatedly, by stress mornitoring, interference checking, tachometric survey checking path planning by path planning；The measurement of aerofoil profile accuracy under folding wings deployed condition, jump and established angle；The insertion of the intersection point pin in many intersection points folding and retraction process and connection robustness detection；Under outer wing folded state, wingtip puts in place the detection of situation；Equally, repeatedly bilateral outer wing synchronous folding folding and unfolding detection is carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610224321.9A CN105806411B (en) | 2016-04-12 | 2016-04-12 | Aircraft rotary folding wing folding and unfolding detection device and method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610224321.9A CN105806411B (en) | 2016-04-12 | 2016-04-12 | Aircraft rotary folding wing folding and unfolding detection device and method |
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| Publication Number | Publication Date |
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| CN105806411A true CN105806411A (en) | 2016-07-27 |
| CN105806411B CN105806411B (en) | 2018-04-20 |
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| CN201610224321.9A Expired - Fee Related CN105806411B (en) | 2016-04-12 | 2016-04-12 | Aircraft rotary folding wing folding and unfolding detection device and method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107702931A (en) * | 2017-09-18 | 2018-02-16 | 上海航天精密机械研究所 | A kind of Multifunctional pneumatic power deploys separation test device |
| CN109163677A (en) * | 2018-10-15 | 2019-01-08 | 北京航星机器制造有限公司 | A kind of method that three-dimensional laser scanning system carries out the horizontal measurement of product airfoil structure |
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Patent Citations (5)
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| EP1818646A1 (en) * | 2006-02-10 | 2007-08-15 | LFK-Lenkflugkörpersysteme GmbH | Wrap-around fin for a missile |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107702931A (en) * | 2017-09-18 | 2018-02-16 | 上海航天精密机械研究所 | A kind of Multifunctional pneumatic power deploys separation test device |
| CN109163677A (en) * | 2018-10-15 | 2019-01-08 | 北京航星机器制造有限公司 | A kind of method that three-dimensional laser scanning system carries out the horizontal measurement of product airfoil structure |
| CN109163677B (en) * | 2018-10-15 | 2020-12-08 | 北京航星机器制造有限公司 | Method for horizontally measuring product airfoil structure by three-dimensional laser scanning system |
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| CN105806411B (en) | 2018-04-20 |
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