CN109540452B - Rotary rocket three-degree-of-freedom angular motion simulation test device - Google Patents
Rotary rocket three-degree-of-freedom angular motion simulation test device Download PDFInfo
- Publication number
- CN109540452B CN109540452B CN201811390616.9A CN201811390616A CN109540452B CN 109540452 B CN109540452 B CN 109540452B CN 201811390616 A CN201811390616 A CN 201811390616A CN 109540452 B CN109540452 B CN 109540452B
- Authority
- CN
- China
- Prior art keywords
- main
- model
- stage
- rotating shaft
- test
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a three-degree-of-freedom angular motion simulation test device for a rotary rocket, which comprises a test model, a primary rotating mechanism, a secondary rotating mechanism and a model supporting mechanism, wherein the test model comprises a main rotating mechanism, a secondary rotating mechanism and a model supporting mechanism; the front end of the primary rotating mechanism is a sector capable of rotating, the secondary rotating mechanism is arranged on the sector and can adjust the position on the sector, the extension of a precession angle is realized, the model supporting mechanism is arranged on the secondary rotating mechanism, the test model is arranged on the model supporting mechanism, the test model can freely rotate relative to the model supporting mechanism, and the secondary rotating mechanism drives the model supporting mechanism to rotate. The device has a stable structure, simulates three-self-angle movement of the rotating rocket in a high-speed wind tunnel test, simultaneously measures unsteady aerodynamic force in the movement process, can realize independent movement of the model in three directions, can measure angles in the three directions, and can measure unsteady aerodynamic force of the model.
Description
Technical Field
The invention relates to the technical field of aerodynamic wind tunnel tests, in particular to a three-degree-of-freedom angular motion simulation test device for a rotary rocket.
Background
The angular motion of the rotary rocket in flight takes three forms: the spinning motion around the axis of the projectile body, the rotating motion around a speed vector, namely precession, and the rotating motion around a certain axis in space, namely nutation. In actual flight, the motion can be a single angular motion, or can be a two-degree-of-freedom angular motion combination or a three-degree-of-freedom angular motion composite motion. The method is used for simulating the angular motion of the rotary rocket and measuring the unsteady aerodynamic force in the motion process in the wind tunnel test, and is a main means for researching the dynamic aerodynamic characteristics of the rotary rocket. Therefore, a set of three-degree-of-freedom angular motion simulation test device for the rotary rocket needs to be developed in a wind tunnel test, so that the unsteady aerodynamic force measurement of the rotary rocket is realized.
Disclosure of Invention
The invention provides a three-degree-of-freedom angular motion simulation test device for a rotary rocket, which aims at solving the problem that the three-degree-of-freedom angular motion of the rotary rocket cannot be simulated under the technical capability of the existing wind tunnel test.
The technical scheme of the invention is as follows: a three-degree-of-freedom angular motion simulation test device for a rotary rocket comprises a test model, a primary rotating mechanism, a secondary rotating mechanism and a model supporting mechanism; the front end of the primary rotating mechanism is a sector capable of rotating, the secondary rotating mechanism is arranged on the sector and can adjust the position on the sector, the extension of a precession angle is realized, the model supporting mechanism is arranged on the secondary rotating mechanism, the test model is arranged on the model supporting mechanism, the test model can freely rotate relative to the model supporting mechanism, and the secondary rotating mechanism drives the model supporting mechanism to rotate.
The invention also has the following technical characteristics:
1. the main-level rotating mechanism comprises a wind tunnel middle support, a main-level supporting sleeve, a main-level motor, a main-level speed reducer, a main-level coupler, a main-level encoder, a main-level conductive sliding ring, a main-level bearing, a main rotating shaft and a sector, wherein the main-level supporting sleeve is fixedly connected with the wind tunnel middle support, the main-level motor is installed on the main-level supporting sleeve, the main-level motor drives the main rotating shaft to continuously rotate sequentially through the main-level speed reducer and the main-level coupler, the main rotating shaft is connected with the sector, the main rotating shaft is installed in the main-level supporting sleeve through the main rotating shaft, the main-level encoder measures the roll angle of the main rotating shaft in real time.
2. The secondary rotating mechanism comprises a pre-biased sliding block, a secondary supporting sleeve, a secondary motor, a secondary speed reducer, a secondary shaft coupling, a secondary angle encoder, a secondary conductive sliding ring, a secondary bearing and a secondary rotating shaft, the secondary rotating shaft is installed in the secondary supporting sleeve, the secondary bearing is arranged between the secondary rotating shaft and the secondary supporting sleeve, the secondary supporting sleeve is connected with the sector through the pre-biased sliding block, the secondary rotating motor is connected with the secondary rotating shaft through the secondary speed reducer and the secondary shaft coupling in sequence, the secondary angle encoder measures the rotating angle of the secondary rotating shaft in real time, the secondary conductive sliding ring realizes electric signal transmission, and the extension of the precession angle is realized by adjusting the position of the pre-biased sliding block on the.
3. Model supporting mechanism include model branch, tertiary encoder, two tertiary bearings, five fractional balance and test model, the front end and the test model fixed connection of five fractional balance, the end and the model branch fixed connection of five fractional balance, the five fractional balance passes through the interior wall connection of the tertiary bearing of second and test model, model branch links to each other with test model afterbody inner wall through first tertiary bearing, can make the free rotation of test model around self axis, install tertiary encoder between test model and the test model, the roll angle of tertiary encoder real-time measurement test model around self axis, the one end of model branch is inflection shape, can realize the simulation of test model nutation angle.
4. The main-stage rotating mechanism further comprises a balancing weight, and the balancing weight is installed on the extension of the sector surface.
The three-stage motion tandem device is overall in structural layout and stable in structure, three-degree-of-freedom angular motion of the rotating rocket is simulated in a high-speed wind tunnel test, unsteady aerodynamic force in the motion process is measured at the same time, independent motion of the model in three directions can be achieved, angles in the three directions can be measured, and unsteady aerodynamic force of the model can be measured. The invention can completely simulate the combination of three motions of precession, nutation and spin motion of a rocket model in a high-speed wind tunnel, and can independently realize any two motions or one motion.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic view of the primary rotary mechanism of the present invention.
Fig. 3 is a schematic diagram of a secondary rotary mechanism and spinning mechanism of the present invention.
Detailed Description
The invention is further illustrated by way of example in the accompanying drawings of the specification:
example 1
As shown in fig. 1, the three-degree-of-freedom angular motion simulation test device for the rotary rocket comprises a test model 29, a primary rotary mechanism 1, a secondary rotary mechanism 2 and a model supporting mechanism 3; the front end of the primary rotating mechanism 1 is a sector capable of rotating, the secondary rotating mechanism 2 is arranged on the sector and can adjust the position on the sector, the extension of a precession angle is realized, the model supporting mechanism 3 is arranged on the secondary rotating mechanism 2, the test model 29 is arranged on the model supporting mechanism, the test model 29 can freely rotate relative to the model supporting mechanism 3, and the secondary rotating mechanism 2 drives the model supporting mechanism 3 to rotate.
The main-stage rotating mechanism 1 comprises a wind tunnel middle support 4, a main-stage supporting sleeve 5, a main-stage motor 6, a main-stage speed reducer 7, a main-stage coupling 8, a main-stage encoder 9, a main-stage conductive sliding ring 10, a main-stage bearing 11, a main rotating shaft 12 and a sector 13, wherein the main-stage supporting sleeve 5 is fixedly connected with the wind tunnel middle support 4, the main-stage motor 6 is installed on the main-stage supporting sleeve 5, the main-stage motor 6 drives the main rotating shaft 12 to rotate continuously through the main-stage speed reducer 7 and the main-stage coupling 8 in sequence, the main rotating shaft 12 is connected with the sector 13, the main rotating shaft 12 is installed in the main-stage supporting sleeve 5 through the main rotating shaft 12, the main-stage encoder 9 measures the roll angle of the main rotating shaft 12 in real time. The main stage rotating mechanism 1 as described above further includes a weight 14, and the weight 14 is mounted on the extension of the sector 13. The weight 14 serves to balance the rotational centrifugal force, contributing to smooth rotation.
The secondary rotating mechanism 2 comprises a pre-biased slider 15, a secondary supporting sleeve 16, a secondary motor 17, a secondary speed reducer 18, a secondary coupling 19, a secondary angle encoder 20, a secondary conductive sliding ring 21, a secondary bearing 23 and a secondary rotating shaft 22, wherein the secondary rotating shaft 22 is installed in the secondary supporting sleeve 16, the secondary bearing 23 is arranged between the secondary rotating shaft 22 and the secondary supporting sleeve 16, the secondary supporting sleeve 16 is connected with the sector 13 through the pre-biased slider 15, the secondary rotating motor 17 is connected with the secondary rotating shaft 22 through the secondary speed reducer 18 and the secondary coupling 19 in sequence, the secondary angle encoder 20 measures the rotating angle of the secondary rotating shaft 22 in real time, and the secondary conductive sliding ring 21 realizes the electric signal transmission of a balance, the secondary motor and the angle encoder, by adjusting the position of the pre-biased slide 15 on the sector 13, an extension of the precession angle is achieved.
The model supporting mechanism 3 is composed of a model supporting rod 24, a three-level encoder 25, a three-level bearing 26, a five-component balance 26 and a test model 27. The front end of the five-component balance 26 is designed into an elongated connecting section, and the section is connected with the test model 27 through the three-stage bearing 26, so that the test model can freely rotate around the axis of the test model. The three-stage encoder 25 measures the roll angle of the test model 27 around its own axis in real time.
The precession angle of this embodiment varies from 5 to 30 deg., and the nutation angle varies from 0 to 5 deg..
The working process and principle of the invention are as follows:
precession and nutation of a rotating projectile may be described in terms of the projectile's rotation about an axis with a velocity vector. For this purpose, a series combination of two sub-mechanisms is adopted. Wherein, the main-level rotating mechanism provides the rotating motion of the projectile body around the velocity vector, namely the precession of the test model is realized; the rotary motion of the projectile about an axis is provided by a secondary rotary mechanism, i.e. nutation of the figure is achieved. In addition, the projectile spinning motion is realized by the model supporting mechanism. The primary and secondary rotational movements are at a given rotational rate and the free rotational movement is induced by aerodynamic torque. The included angle between the rotating main shaft and the axis of the secondary sleeve is a precession angle, and the included angle between the axis of the model projectile body and the axis of the secondary support sleeve is a nutation angle. The precession angle is realized by adjusting the installation position of the secondary support sleeve on the sector, and the nutation angle is realized by replacing balance support rods with different pre-deflection angles.
Claims (4)
1. A three-degree-of-freedom angular motion simulation test device for a rotary rocket comprises a test model (29), a primary rotating mechanism (1), a secondary rotating mechanism (2) and a model supporting mechanism (3); the front end of the main-stage rotating mechanism (1) is a sector which can rotate, the secondary rotating mechanism (2) is arranged on the sector and can adjust the position on the sector, the extension of a precession angle is realized, the model supporting mechanism (3) is arranged on the secondary rotating mechanism (2), the test model (29) is arranged on the model supporting mechanism, the test model (29) can freely rotate relative to the model supporting mechanism (3), and the secondary rotating mechanism (2) drives the model supporting mechanism (3) to rotate; the method is characterized in that: the main-stage rotating mechanism (1) comprises a wind tunnel middle support (4), a main-stage supporting sleeve (5), a main-stage motor (6), a main-stage speed reducer (7), a main-stage coupler (8), a main-stage encoder (9), a main-stage conductive slip ring (10), a main-stage bearing (11), a main rotating shaft (12) and a sector (13), wherein the main-stage supporting sleeve (5) is fixedly connected with the wind tunnel middle support (4), the main-stage motor (6) is installed on the main-stage supporting sleeve (5), the main-stage motor (6) drives the main rotating shaft (12) to continuously rotate through the main-stage speed reducer (7) and the main-stage coupler (8) in sequence, the main rotating shaft (12) is connected with the sector (13), the main rotating shaft (12) is installed in the main-stage supporting sleeve (5) through the main rotating shaft (12), and the main-stage encoder (9) measures the roll angle of the main rotating, the main-stage conductive slip ring (10) realizes electric signal transmission.
2. The three-degree-of-freedom angular motion simulation test device for the rotary projectile according to claim 1, wherein: the secondary rotating mechanism (2) comprises a pre-deflection slider (15), a secondary supporting sleeve (16), a secondary motor (17), a secondary speed reducer (18), a secondary coupling (19), a secondary angle encoder (20), a secondary conductive slip ring (21), a secondary bearing (23) and a secondary rotating shaft (22), wherein the secondary rotating shaft (22) is installed in the secondary supporting sleeve (16), the secondary bearing (23) is arranged between the secondary rotating shaft (22) and the secondary supporting sleeve (16), the secondary supporting sleeve (16) is connected with the sector (13) through the pre-deflection slider (15), the secondary rotating motor (17) is connected with the secondary rotating shaft (22) through the secondary speed reducer (18) and the secondary coupling (19) in sequence, the secondary angle encoder (20) measures the rotating angle of the secondary rotating shaft (22) in real time, and the secondary conductive slip ring (21) realizes electric signal transmission, by adjusting the position of the pre-biased sliding block (15) on the sector (13), the extension of the precession angle is realized.
3. The three-degree-of-freedom angular motion simulation test device for the rotary rocket according to claim 1 or 2, wherein: the model supporting mechanism (3) comprises a model supporting rod (24), a three-level encoder (25), two three-level bearings (26, 27), a five-component balance (28) and a test model (29), the front end of the five-component balance (28) is fixedly connected with the test model (29), the tail end of the five-component balance (28) is fixedly connected with the model supporting rod (24), the five-component balance (28) is connected with the inner wall of the test model (29) through a second three-level bearing (27), the model supporting rod (24) is connected with the inner wall of the tail of the test model (29) through a first three-level bearing (26), the test model (29) can freely rotate around the axis of the model, the three-level encoder (25) is installed between the test model (29) and the test model (29), the three-level encoder (25) measures the roll angle of the test model (29) around the axis of the test model in real time, one end of the model supporting rod (24) is in, simulation of the nutation angle of the test model (29) can be achieved.
4. The three-degree-of-freedom angular motion simulation test device for the rotary projectile according to claim 1, wherein: the fan-shaped fan further comprises a balancing weight (14), and the balancing weight (14) is.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811390616.9A CN109540452B (en) | 2018-11-21 | 2018-11-21 | Rotary rocket three-degree-of-freedom angular motion simulation test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811390616.9A CN109540452B (en) | 2018-11-21 | 2018-11-21 | Rotary rocket three-degree-of-freedom angular motion simulation test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109540452A CN109540452A (en) | 2019-03-29 |
| CN109540452B true CN109540452B (en) | 2020-05-22 |
Family
ID=65849100
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811390616.9A Active CN109540452B (en) | 2018-11-21 | 2018-11-21 | Rotary rocket three-degree-of-freedom angular motion simulation test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109540452B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179608B (en) * | 2020-09-28 | 2021-07-09 | 厦门大学 | Supporting device and testing system for wind tunnel dynamic test of rotary rocket model |
| CN112649171B (en) * | 2020-12-17 | 2022-10-14 | 中国航天空气动力技术研究院 | Trajectory capture system for simultaneous separation simulation of machine bombs |
| CN112904898B (en) * | 2021-01-28 | 2022-11-29 | 上海机电工程研究所 | Method and system for evaluating unsteady pneumatic response characteristic of rotary rocket |
| CN113494989B (en) * | 2021-06-28 | 2024-05-31 | 中国航天空气动力技术研究院 | Double-rotating-shaft device for wind tunnel provided with balancing mechanism and balancing method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592099A (en) * | 2013-11-28 | 2014-02-19 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring equipment for wind tunnel free-rolling vibration test and measuring method thereof |
| CN205642791U (en) * | 2015-12-29 | 2016-10-12 | 中国航天空气动力技术研究院 | Wind -tunnel is with toper motion simulation device of rotatory guided missile |
| CN106441779A (en) * | 2015-08-06 | 2017-02-22 | 无锡市羲和科技有限公司 | Apparatus for measuring three-degree-of-freedom dynamic stability parameters of aircraft in high-speed wind tunnel |
| CN106768816A (en) * | 2016-12-22 | 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 pitching dynamic derivative experimental provision of tail vibration |
| CN107290123A (en) * | 2017-06-07 | 2017-10-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
| CN109506878A (en) * | 2018-10-29 | 2019-03-22 | 中国航天空气动力技术研究院 | A kind of multiple-degree-of-freedom mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11131598B2 (en) * | 2016-08-04 | 2021-09-28 | Ahmad D. Vakili | Technology to control a model and balance support system's dynamics and isolate the balance as needed to increase test facilities productivity |
-
2018
- 2018-11-21 CN CN201811390616.9A patent/CN109540452B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592099A (en) * | 2013-11-28 | 2014-02-19 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring equipment for wind tunnel free-rolling vibration test and measuring method thereof |
| CN106441779A (en) * | 2015-08-06 | 2017-02-22 | 无锡市羲和科技有限公司 | Apparatus for measuring three-degree-of-freedom dynamic stability parameters of aircraft in high-speed wind tunnel |
| CN205642791U (en) * | 2015-12-29 | 2016-10-12 | 中国航天空气动力技术研究院 | Wind -tunnel is with toper motion simulation device of rotatory guided missile |
| CN106768816A (en) * | 2016-12-22 | 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 pitching dynamic derivative experimental provision of tail vibration |
| CN107290123A (en) * | 2017-06-07 | 2017-10-24 | 中国航天空气动力技术研究院 | The big angle of attack device of multiple degrees of freedom wind-tunnel |
| CN109506878A (en) * | 2018-10-29 | 2019-03-22 | 中国航天空气动力技术研究院 | A kind of multiple-degree-of-freedom mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109540452A (en) | 2019-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109540452B (en) | Rotary rocket three-degree-of-freedom angular motion simulation test device | |
| CN205642791U (en) | Wind -tunnel is with toper motion simulation device of rotatory guided missile | |
| CN102175420B (en) | Two-degrees-of-freedom supporting system for wind tunnel test of airplane | |
| CN106441779B (en) | The device of aircraft three-freedom moving steadiness parameter is measured in a kind of high-speed wind tunnel | |
| CN105527068A (en) | Wind tunnel dynamic force measurement test device for canard configuration rotating missile | |
| CN110160730B (en) | Device and method for testing separation performance of aircraft plug-in high-speed wind tunnel | |
| CN102095567B (en) | Forced yawing-free rolling wind tunnel test device | |
| CN102494865A (en) | Simulation apparatus of pitching/jawing/rolling over three-freedom degree forced movement of aircraft | |
| CN111623951B (en) | Wind tunnel model multi-attitude coupling real-time force measuring device and test method | |
| CN112179608B (en) | Supporting device and testing system for wind tunnel dynamic test of rotary rocket model | |
| CN211347313U (en) | Two-degree-of-freedom dynamic test supporting device for open wind tunnel | |
| CN109506877B (en) | Sub-span super wind tunnel 90-degree large attack angle coupling 360-degree rolling device | |
| CN104326368A (en) | Gravity compensation device for solar wing low temperature unfolding experiment | |
| CN108344553A (en) | Model in wind tunnel parallel institution support device for aircraft formation flight | |
| CN110683074A (en) | High-dynamic centrifugal overload simulation test device | |
| CN109506878B (en) | Multi-degree-of-freedom mechanism | |
| CN210555640U (en) | High-dynamic centrifugal overload simulation test device | |
| CN110004046B (en) | Variable gravity cell experimental device based on three-dimensional rotation | |
| CN102778333A (en) | Method for performing dynamic balance test on large rotating part | |
| Araujo-Estrada et al. | Wind tunnel manoeuvre rig: a multi-DOF test platform for model aircraft | |
| Acree Jr et al. | Development and initial testing of the tiltrotor test rig | |
| CN110606222B (en) | Pneumatic characteristic testing device for single rotor system of suspended Mars aircraft | |
| CN114166496B (en) | Tilt rotor wing test device | |
| CN110001328B (en) | Spacecraft simulation device | |
| CN112345195B (en) | Test device for high-speed wind tunnel ultra-large attack angle multi-frequency compound motion |
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 |