CN201772990U - Low-blocking-degree independent six-degree of freedom movement device for captive trajectory experiment system - Google Patents
Low-blocking-degree independent six-degree of freedom movement device for captive trajectory experiment system Download PDFInfo
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- CN201772990U CN201772990U CN2010201759083U CN201020175908U CN201772990U CN 201772990 U CN201772990 U CN 201772990U CN 2010201759083 U CN2010201759083 U CN 2010201759083U CN 201020175908 U CN201020175908 U CN 201020175908U CN 201772990 U CN201772990 U CN 201772990U
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Abstract
The utility model provides a low-blocking-degree independent six-degree of freedom movement device for a captive trajectory experiment system, relates to a six-degree of freedom movement device for captive trajectory wind tunnel experiments, and aims to achieve the purpose that an external store model can move at six degrees of freedom in an captive trajectory wind tunnel experiment; and the device has low blocking degree to airflow. The utility model adopts the technical scheme that the whole device is mounted on the experimental section of a wind tunnel (or the expanding section of the wind tunnel); the device comprises a Z-axis motion mechanism which is vertically arranged, a Y-axis motion mechanism which is arranged in the horizontal direction of the wind tunnel and is perpendicular to the airflow direction, and an X-axis motion mechanism which is arranged horizontally and has the same direction with the airflow direction; as for an X-axis driving device, a Y-axis driving device and a Z-axis driving device, only the Y-axis driving device is arranged at the top of the outer wall of the experimental section of the wind tunnel, or only the Z-axis driving device is arranged on the outer wall of the experimental section of the wind tunnel; and three angular displacement devices are connected to the top end of the x-axis motion mechanism. The utility model is mainly applied to captive trajectory wind tunnel experiment systems in aeronautics and astronautics.
Description
Technical field
The utility model relates to a kind of six-freedom motion device, particularly relates to a kind of independent six-freedom motion device that solves low congestion degree in catching the trajectory tests system.
Technical background
It is indispensable for the plug-in thing input of aircraft trajectory measurement to catch the track wind tunnel test system.
The U.S. has grasped and has caught the track wind-tunnel technique at the seventies in last century, and states such as Britain, France, Israel and China are also in the eighties development with used this experimental technique.
Six-freedom motion mechanism is the core of catching the track wind tunnel test system, is the bracing or strutting arrangement of plug-in object model in the system and the topworks of motion thereof.Six-freedom motion mechanism is by computer control, for plug-in object model provides six-freedom degree (axial X, horizontal Y, vertical Z, pitching α, driftage β and lift-over γ), its canonical form has two kinds: a kind of is that the motion of six-freedom degree keeps separate, the form that is added three slew constrained (realizing three angular displacement campaigns) by three line slideway constraints (realizing three displacement of the lines motions) realizes the six-freedom degree motion, as U.S. AFDC, mechanism in the wind-tunnel such as General Dynamics Corp. and Israel IAI 4 feet, its three angular displacements all are to finish by the motion of the anterior Three Degree Of Freedom device head of installing of device, transverse movement is finished by device head moving on the cross slide way support, and vertical and axially-movable by vertical support (being installed on the rolling bearing guide rail of wind-tunnel top or bottom) along the wind-tunnel vertical to or axial moving finish, when the transverse movement yardstick is big, in order to guarantee the rigidity of horizontal support, the vertical smooth plates that the U.S. and Israel have installed roundel and allowed it be installed along the wind-tunnel both sides in CTS horizontal support both sides moves.
Another kind of then by two motions that six-freedom degree is provided with the slew constrained combination and variation of upper-part, as the CTS mechanism in 9 feet x8 foot high-speed wind tunnels of the 6 feet high-speed wind tunnels of French ONERA and Britain ARA, this class mechanism is not owing to adopt horizontal or vertical line slideway, congestion degree is less relatively, usually be installed on the machine tool bracing or strutting arrangement, do not relate to construction of wind tunnel, be easy to during test install, and can be positioned at test chamber; But this class mechanism requires all very high to rigidity requirement and self mechanism precision of machine tool bracing or strutting arrangement, and its six-freedom degree is not complete independent operating, promptly, the motion of some degree of freedom need be produced by many support arms or multipart aggregate motion, therefore its range of movement is very restricted, the aggregate motion of mechanism also must be eliminated its influence to trial value by revising, and the control difficulty of the plug-in thing of aircraft being thrown in track is big.
The utility model content
The purpose of this utility model provides a kind of in order to solve the separate six-freedom degree motion of in catching track wind tunnel test realization, and this independent six-freedom motion device is low to the congestion degree of air-flow.
For achieving the above object, the technical solution adopted in the utility model is: low congestion degree is caught the independent six-freedom motion device of trajectory tests system, integral installation is on test chamber (or wind-tunnel ultra-expanded section), the Z shaft movement mechanism that comprises vertical setting, along the Y-axis motion of wind-tunnel horizontal direction setting be horizontally disposed with and the X-axis motion vertical with the Y-axis motion, described X-axis drive unit, in Y-axis drive unit and the Z axial brake device, perhaps only there is the Z axial brake device to place on the outer wall of test chamber, perhaps only have the Y-axis drive unit to place the top of the outer wall of test chamber, three angular displacement devices are connected the top of X-axis motion.
Described Z shaft movement mechanism is two, lay respectively on the both sides outer wall of test chamber, two Z axial brake device operations of two Z shaft movement mechanisms of driven in synchronism control respectively, the Z shaft movement mechanism is provided with two gravity balance devices that are used to offset experimental provision gravity, the Y-axis motion passes test chamber, its two ends are connected on two Z shaft movement mechanisms, the X-axis motion is connected on the Y-axis motion, wherein two Z shaft movement mechanisms drives of two Z axial brake device driven in synchronism Y-axis motion moves along the Z axle, the Y-axis drive unit drives Y-axis motion drive X-axis motion and moves along the Y axle, and the X-axis drive unit drives three angular displacement devices and moves along X-axis.
On the top exterior walls that is fixed on test chamber (or wind-tunnel ultra-expanded section) of described Y-axis motion, the Z shaft movement mechanism is connected on the Y-axis motion, the X-axis motion is connected on the Z shaft movement mechanism, wherein Y-axis drive unit driving Y-axis motion drive Z shaft movement mechanism moves along Y-axis, the Z axial brake device drives Z shaft movement mechanism drive X-axis motion and moves along the Z axle, and the X-axis drive unit drives three angular displacement devices of X-axis motion drive and moves along X-axis.
The described X-axis motion cross section that facings the wind is the π cavity structure, the X-axis drive unit is arranged at the rear end of X-axis motion, the X-axis winder that is connected with the X-axis drive unit is arranged at and is used to control the operation of X-axis motion in the internal cavities of X-axis motion, is used for the control cable of three angular displacement devices on the automatic deploying and retracting X-axis motion.。
Described Y-axis motion and Y-axis winder are arranged in parallel, and the Y-axis winder is connected with the Y-axis drive unit and is used to control the operation of Y-axis motion.
The cross section that facings the wind of described Z shaft movement mechanism is the version of well word shape.
Described Z shaft movement mechanism is provided with the gravity balance device that is used to offset experimental provision gravity.
From above-mentioned technical characterictic of the present utility model as can be seen, the utility model has the advantages that: (1) is different with traditional X-ray shaft supporting structure form, X-axis motion of the present utility model adopts π cavity structure form, with the X-axis drive arrangement in X-axis motion back, the X-axis winder is placed in the X-axis motion cavity simultaneously, make design of test compacter, reduced the congestion degree of test unit greatly.
(2) the utility model is arranged in parallel within the Y-axis back with Y-axis motion and Y-axis winder, the front face area in same cross section is reduced, thereby reduce congestion degree.
(3) another version of the utility model is that the Cross section Design of facining the wind with the Z shaft supporting structure is the version of well word shape, the front face area in same cross section is reduced, thereby reduce congestion degree.
(4) different with the design of traditional Z shaft movement mechanism, in a kind of therein structure, the utility model adopts the design of left and right sides driven in synchronism and matching mechanism gravity balance device (as balance cylinder), overcomes the Z axle and adopts monolateral driving, makes test unit produce stuck, bad phenomenon such as creep easily; For another version, the utility model adopts single also design of matching mechanism gravity balance device (as balance cylinder) that drives.Z shaft movement mechanism matching mechanism gravity balance device, the bigger breakoff phenomenon that produces of inertia when avoiding mechanism to move downward (as damaging precision ball screw), mechanism's gravity balance device is offset the gravity of test unit simultaneously, can guarantee that also precision lead screw is on active service under the high precision operating mode, guarantee Z axle kinematic accuracy.Show that through test the wind-tunnel congestion degree of the utility model independence six-freedom motion device is lower more than 45% than the system in the middle of the prior art.
Description of drawings
The utility model will illustrate by accompanying drawing comparison and mode in conjunction with the embodiments:
Fig. 1 is wherein a kind of synoptic diagram of structure of the utility model,
Fig. 2 is the synoptic diagram of the another kind of structure of the utility model,
Fig. 3 is the utility model X-axis motion π cavity structure synoptic diagram,
Fig. 4 is the utility model Y-axis motion and Y-axis winder structural representation,
Embodiment
The utility model is described further by embodiment below in conjunction with accompanying drawing:
Preferred embodiment
Catch the independent six-freedom motion device of trajectory tests system as Fig. 1-low congestion degree shown in Figure 4, integral installation is on test chamber (or wind-tunnel ultra-expanded section) 1, the Z shaft movement mechanism 4 that comprises vertical setting, along the Y-axis motion 3 of wind-tunnel horizontal direction setting be horizontally disposed with and the X-axis motion 2 vertical with Y-axis motion 3, described X-axis drive unit 5, in Y-axis drive unit 6 and the Z axial brake device 7, perhaps only there is Z axial brake device 7 to place on the outer wall of test chamber (or wind-tunnel ultra-expanded section) 1, perhaps only have Y-axis drive unit 6 to place the top of the outer wall of test chamber (or wind-tunnel ultra-expanded section) 1, three angular displacement devices 8 are connected the top of X-axis motion 2.The set-up mode of this programme has significantly been simplified the inner structure of device, plays an important role for reducing congestion degree, in addition, three angular displacement devices 8 simple in structure, volume is little, and is in light weight, easy for installation, the reliability height can be good at satisfying the requirement of congestion degree, and the load-bearing capacity that realizes is big.
As shown in Figure 1, on the basis of such scheme, described Z shaft movement mechanism 4 is two, lay respectively on the both sides outer wall of test chamber (or wind-tunnel ultra-expanded section) 1, two Z axial brake device 7 operations of two Z shaft movement mechanisms 4 of driven in synchronism control respectively, Z shaft movement mechanism 4 is provided with two gravity balance devices 9 that are used to offset experimental provision gravity, Y-axis motion 3 passes test chamber 1, its two ends are connected on two Z shaft movement mechanisms 4, X-axis motion 2 is connected on the Y-axis motion 3, wherein two Z shaft movement mechanisms of two Z axial brake device 7 driven in synchronism 4 drive Y-axis motion 3 and move along the Z axle, Y-axis drive unit 6 drives Y-axis motions 3 and drives X-axis motion 2 and move along Y-axis, and X-axis drive unit 5 drives three angular displacement devices 8 and moves along X-axis.In this programme, with Z shaft movement mechanism 4 overall fixed on the left and right sides outer wall of test chamber (or wind-tunnel ultra-expanded section) 1, to increase the rigidity of whole device, Z shaft movement mechanism and other drive unit are arranged in the outside of test chamber (or wind-tunnel ultra-expanded section), to greatest extent expansion instrument range of operation and reduce its congestion degree in wind-tunnel; The two ends of Y-axis motion 3 are connected on the Z shaft movement mechanism 4 to increase rigidity and intensity in addition, X-axis motion 2 is a cantilever beam structure, be installed on the Y-axis motion 3, three angular displacement devices 8 are installed in the top of X-axis motion 2, realize the angular displacement of Three Degree Of Freedom.
In the such scheme, described X-axis motion 2 is the π cavity structure, X-axis drive unit 5 is arranged at the rear end of X-axis motion 2, and the X-axis winder 10 that is connected with X-axis drive unit 5 is arranged at and is used to control 2 operations of X-axis motion in the internal cavities of X-axis motion 2.Because X-axis motion 2 (axial along wind-tunnel) is a cantilever beam structure, and in wind-tunnel, must bear very big aerodynamic loading, in order to increase the bending strength of X-axis motion 2, weight reduction simultaneously, the X-axis motion adopts the π cavity structure, with the machine-shaping of high-strength alloy structural steel, with the X-axis drive arrangement in X-axis, simultaneously the X-axis winder is caused in X-axis motion cavity, make design of test compacter, reduced the congestion degree of test unit greatly.
In such scheme, described Y-axis motion 3 is arranged in parallel with Y-axis winder 11, and Y-axis winder 11 is connected with Y-axis drive unit 6 and is used to control 3 operations of Y-axis motion.In this programme, Y-axis motion (along the wind-tunnel horizontal direction) adopts the fixed installation in two ends, to increase rigidity and intensity.Y-axis motion and Y-axis winder are arranged in parallel, and the Y-axis winder places Y-axis motion back, the front face area in same cross section is reduced, thereby reduce congestion degree.
Another version of the present utility model as shown in Figure 2, the two ends of described Y-axis motion 3 are connected on the top exterior walls of test chamber (or wind-tunnel ultra-expanded section) 1, Z shaft movement mechanism 4 is connected on the Y-axis motion 3, X-axis motion 2 is connected on the Z shaft movement mechanism 4, wherein Y-axis drive unit 6 drives Y-axis motions 3 and drives Z shaft movement mechanism 4 and move along Y-axis, Z axial brake device 7 drives Z shaft movement mechanisms 4 and drives X-axis motion 2 and move along the Z axle, and X-axis drive unit 5 drives X-axis motions 2 and drives three angular displacement devices 8 and move along X-axis.
In such scheme, the cross section that facings the wind of described Z shaft movement mechanism 4 is the version of well word shape.The utility model is the form of well word shape with the Cross section Design of facining the wind of Z shaft supporting structure, the front face area in same cross section is reduced, thereby reduce congestion degree.
Device of the present utility model in such scheme, described Z shaft movement mechanism 4 is provided with the gravity balance device 9 that is used to offset experimental provision gravity.In this programme, adopt single also design of matching mechanism gravity balance device 9 (as balance cylinder) that drives.Z shaft movement mechanism 4 matching mechanism gravity balance devices 9, the bigger breakoff phenomenon that produces of inertia when avoiding mechanism to move downward (as damaging precision ball screw), mechanism's gravity balance device 9 is offset the gravity of test unit simultaneously, can guarantee that also precision lead screw is on active service under the high precision operating mode, guarantee Z shaft movement mechanism kinematic accuracy.
Disclosed all features in this instructions except mutually exclusive feature, all can make up by any way.
Disclosed arbitrary feature in this instructions (comprising any accessory claim, summary and accompanying drawing) is unless special narration all can be replaced by other equivalences or the alternative features with similar purpose.That is, unless special narration, each feature is an example in a series of equivalences or the similar characteristics.
Claims (7)
1. low congestion degree is caught the independent six-freedom motion device of trajectory tests system, integral installation is on test chamber (1), the Z shaft movement mechanism (4) that comprises vertical setting, the Y-axis motion (3) that is provided with along the wind-tunnel horizontal direction be horizontally disposed with and the X-axis motion (2) vertical with Y-axis motion (3), it is characterized in that described X-axis drive unit (5), in Y-axis drive unit (6) and the Z axial brake device (7), perhaps only there is Z axial brake device (7) to place on the outer wall of test chamber (1), perhaps only have Y-axis drive unit (6) to place the top exterior walls of test chamber (1), three angular displacement devices (8) are connected the top of X-axis motion (2).
2. low congestion degree according to claim 1 is caught the independent six-freedom motion device of trajectory tests system, it is characterized in that described Z shaft movement mechanism (4) is two, lay respectively on the both sides outer wall of test chamber (1), two Z axial brake devices (7) are the operation of driven in synchronism two Z shaft movement mechanisms of control (4) respectively, Z shaft movement mechanism (4) is provided with two gravity balance devices (9) that are used to offset experimental provision gravity, Y-axis motion (3) passes test chamber (1), its two ends are connected on two Z shaft movement mechanisms (4), X-axis motion (2) is connected on the Y-axis motion (3), wherein two Z axial brake devices (7), two Z shaft movement mechanisms of driven in synchronism (4) drive Y-axis motions (3) move along the Z axle, Y-axis drive unit (6) drives Y-axis motion (3) drive X-axis motion (2) and moves along Y-axis, and X-axis drive unit (5) drives three angular displacement devices (8) and moves along X-axis.
3. low congestion degree according to claim 1 is caught the independent six-freedom motion device of trajectory tests system, the two ends that it is characterized in that described Y-axis motion (3) are connected on the top of test chamber (1) outer wall, Z shaft movement mechanism (4) is connected on the Y-axis motion (3), X-axis motion (2) is connected on the Z shaft movement mechanism (4), wherein Y-axis drive unit (6) driving Y-axis motion (3) drive Z shaft movement mechanism (4) moves along Y-axis, Z axial brake device (7) drives Z shaft movement mechanism (4) drive X-axis motion (2) and moves along the Z axle, and X-axis drive unit (5) drives X-axis motion (2) three angular displacement devices of drive (8) and moves along X-axis.
4. low congestion degree according to claim 2 is caught the independent six-freedom motion device of trajectory tests system, it is characterized in that described X-axis motion (2) is that the π cavity structure is to reduce the congestion degree to air-flow, X-axis drive unit (5) is arranged at the rear end of X-axis motion (2), the X-axis winder (10) that is connected with X-axis drive unit (5) is arranged in the internal cavities of X-axis motion (2), is used for the control cable of last three the angular displacement devices of automatic deploying and retracting X-axis motion (2) (8).
5. catch the independent six-freedom motion device of trajectory tests system according to claim 2 or 4 described low congestion degrees, it is characterized in that described Y-axis motion (3) and Y-axis winder (11) are arranged in parallel, Y-axis winder (11) is connected with Y-axis drive unit (6) and is used to control Y-axis motion (3) operation.
6. low congestion degree according to claim 3 is caught the independent six-freedom motion device of trajectory tests system, it is characterized in that the cross section that facings the wind of described Z shaft movement mechanism (4) is the version of well word shape, to reduce the congestion degree to air-flow.
7. low congestion degree according to claim 6 is caught the independent six-freedom motion device of trajectory tests system, it is characterized in that described Z shaft movement mechanism (4) is provided with the gravity balance device (9) that is used to offset experimental provision gravity.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102607795A (en) * | 2012-03-19 | 2012-07-25 | 西北工业大学 | Three-dimensional movement test device for wind tunnel |
| CN104458194A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Hydraulic drive device and mode for axial movement of wind tunnel super expansion segment |
| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
| CN105258907A (en) * | 2015-11-13 | 2016-01-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Three-turn angle head applied to wind tunnel test |
| CN105784316A (en) * | 2016-05-11 | 2016-07-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-rigidness embedded device for multi-body separation test of hypersonic wind tunnel |
| CN106124157A (en) * | 2016-05-11 | 2016-11-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of space mechanism in six degree of freedom for the test of hypersonic wind tunnel Multi-bodies Separation |
| CN106768815A (en) * | 2016-12-12 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of real-time multi-axis synchronized control measuring system |
| CN108088647A (en) * | 2017-12-04 | 2018-05-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of five degree of freedom boundary layer measuring system for wind tunnel test |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN109269758A (en) * | 2018-10-30 | 2019-01-25 | 北京航天益森风洞工程技术有限公司 | A kind of wind-tunnel Three Degree Of Freedom model interposer control system and method |
| CN112326190A (en) * | 2020-10-30 | 2021-02-05 | 北京航空航天大学 | Insect flapping wing model experiment platform based on towing water tank |
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2010
- 2010-04-29 CN CN2010201759083U patent/CN201772990U/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102607795A (en) * | 2012-03-19 | 2012-07-25 | 西北工业大学 | Three-dimensional movement test device for wind tunnel |
| CN104458194A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Hydraulic drive device and mode for axial movement of wind tunnel super expansion segment |
| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
| CN104931222B (en) * | 2015-05-04 | 2018-04-10 | 中国航天空气动力技术研究院 | Machine bullet separated track captive test system |
| CN105258907A (en) * | 2015-11-13 | 2016-01-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Three-turn angle head applied to wind tunnel test |
| CN105784316B (en) * | 2016-05-11 | 2018-06-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of high rigidity embedded equipment for the experiment of hypersonic wind tunnel Multi-bodies Separation |
| CN105784316A (en) * | 2016-05-11 | 2016-07-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-rigidness embedded device for multi-body separation test of hypersonic wind tunnel |
| CN106124157A (en) * | 2016-05-11 | 2016-11-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of space mechanism in six degree of freedom for the test of hypersonic wind tunnel Multi-bodies Separation |
| CN106124157B (en) * | 2016-05-11 | 2018-11-06 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of space mechanism in six degree of freedom for the experiment of hypersonic wind tunnel Multi-bodies Separation |
| CN106768815A (en) * | 2016-12-12 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of real-time multi-axis synchronized control measuring system |
| CN108088647A (en) * | 2017-12-04 | 2018-05-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of five degree of freedom boundary layer measuring system for wind tunnel test |
| CN108088647B (en) * | 2017-12-04 | 2020-03-10 | 中国航空工业集团公司哈尔滨空气动力研究所 | Five-degree-of-freedom boundary layer measuring system for wind tunnel test |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN109269758A (en) * | 2018-10-30 | 2019-01-25 | 北京航天益森风洞工程技术有限公司 | A kind of wind-tunnel Three Degree Of Freedom model interposer control system and method |
| CN112326190A (en) * | 2020-10-30 | 2021-02-05 | 北京航空航天大学 | Insect flapping wing model experiment platform based on towing water tank |
| CN112326190B (en) * | 2020-10-30 | 2022-02-22 | 北京航空航天大学 | Insect flapping wing model experiment platform based on towing water tank |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110323 Termination date: 20130429 |