CN107856867A - A kind of experimental rig for measuring high-speed wind tunnel parachute model parachute-opening characteristic - Google Patents
A kind of experimental rig for measuring high-speed wind tunnel parachute model parachute-opening characteristic Download PDFInfo
- Publication number
- CN107856867A CN107856867A CN201711373694.3A CN201711373694A CN107856867A CN 107856867 A CN107856867 A CN 107856867A CN 201711373694 A CN201711373694 A CN 201711373694A CN 107856867 A CN107856867 A CN 107856867A
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- parachute
- balance
- model
- wind tunnel
- experimental rig
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- 229920000742 Cotton Polymers 0.000 claims description 8
- 230000005611 electricity Effects 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 11
- 238000000034 method Methods 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 description 10
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 238000002474 experimental method Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 229910052742 iron Inorganic materials 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000003721 gunpowder Substances 0.000 description 2
- 238000007664 blowing Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D21/00—Testing of parachutes
-
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of experimental rig for measuring high-speed wind tunnel parachute model parachute-opening characteristic.The experimental rig includes parachute model supporting device, balance, rotor and parachute opener.When the air-flow in high wind tunnel testing section reaches defined flow field condition, the rotating shaft of stepper motor drives screw rod rotation, moved after nut on screw rod and extract umbrella cabin blanking cover, parachute model out of umbrella cabin, parachute model is opened under action of high-speed airflow, in opening process, high-speed wind tunnel data collecting system carries out continuous acquisition to balance measured value.The experimental rig parachute-opening mode safety of the present invention, parachute-opening power is substantially noiseless to balance and will not damage balance；The experimental rig of the present invention employs the beam strain-gauge balance of back taper inner cone as balance, it is therefore prevented that balance departs from parachute model supporting device and damages the generation of balance and high-speed wind tunnel accident.
Description
Technical field
The invention belongs to parachute model high wind tunnel testing technical field, and in particular to one kind measurement high-speed wind tunnel landing
The experimental rig of umbrella model parachute-opening characteristic.
Background technology
Parachute has small volume, light weight, easy to carry and stablizing effect good etc. notable as a kind of deceleration stabilizer
Advantage, had a very wide range of applications in modern aerospace field.As unmanned flight's platform is launched, high speed ejection is rescued
Life, Spacecraft Recovery, extraterrestrial ball detector（Such as Mars probes）The tasks such as landing of slowing down are increasing, more and more flights
Device is at a high speed（More than the 0.3 times velocity of sound）Slowed down under flying condition using parachute, can parachute under high-speed condition just
The parachute-opening characteristics such as normally opened umbrella, opening process resistance coefficient time history are directly connected to above-mentioned task success and implemented.
Due in high-speed wind tunnel measure parachute model parachute-opening characteristic have the test period it is short, obtain test data essence
It is accurate, testing expenses are cheap etc., and remarkable advantage, the domestic high-speed wind tunnel that gradually starts with carry out parachute model high speed parachute-opening characteristic
Experiment.Measure high-speed wind tunnel parachute model parachute-opening characteristic experimental rig mainly include parachute model supporting device, balance,
Parachute opener.Beam strain-gauge balance of the existing high-speed wind tunnel balance frequently with inner cone for positive cone, in the presence of high velocity air,
Parachute model produces the aerodynamic force of direction backward, and balance has the risk departed from high-speed wind tunnel hole wall bracket, can made
Into the accident of damage balance and high-speed wind tunnel, therefore inner cone is the beam strain-gauge balance of positive cone and is not suitable for carrying out independent parachute
Model dynamometer check.Existing high-speed wind tunnel parachute opener relies primarily on gases at high pressure, gunpowder as parachute-opening power.Work as gases at high pressure
During introducing parachute compartment, gases at high pressure can produce to balance measured value to be disturbed and is possible to damage force balance, and gunpowder is present certainly
It is quick-fried to wait unsafe factor.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of examination for measuring high-speed wind tunnel parachute model parachute-opening characteristic
Experiment device.
The experimental rig of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention fills including parachute model support
Put, balance, rotor and parachute opener, the front end of balance are connected with parachute model supporting device, the rear end of balance and rotor
Canned paragraph connects, and the rotation section of parachute model and rotor connects, the canopy top of parachute model and the umbrella cabin of parachute opener
Blanking cover is connected with cotton thread.
Described parachute model supporting device includes high-speed wind tunnel hole wall bracket and the aircraft to slow down using parachute
Model, balance metallic channel is left in the wall bracket of high-speed wind tunnel hole, transmitted for balance signal.
Described balance is the beam strain-gauge balance of back taper inner cone, and balance rear end has what is be connected with the canned paragraph of rotor to insert
Pin-and-hole.
Described rotor is divided into canned paragraph, rotation section two parts, and canned paragraph is connected with balance rear end, rotates section and parachute
Model is connected.
Described parachute opener includes umbrella cabin blanking cover, thin wire, nut, screw rod I, bearing, stepper motor, support frame, carefully
One end of iron wire is connected with umbrella cabin blanking cover, and the other end of thin wire is connected by the through hole on nut top with nut, nut installation
On screw rod I, screw rod I is fixed in the rotating shaft of stepper motor by bolt I, and bearing passes through bolt II and the housing of stepper motor
Connection, bearing are connected by bolt III with support frame.
The experimental rig of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention has advantages below：
1. employ the beam strain-gauge balance of back taper inner cone, it is therefore prevented that with parachute model supporting device relative fortune occurs for balance
It is dynamic, avoid the accident that balance departs from parachute model supporting device and damages balance and high-speed wind tunnel and occur；
2. the rotating shaft for employing stepper motor drives screw rod to rotate, is moved after the nut on screw rod and extract umbrella cabin blanking cover, parachute mould
The parachute-opening mode of type, parachute-opening mode safety, parachute-opening power is substantially noiseless to balance and will not damage balance.
The experimental rig of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention can safely carry out parachute
Model high speed parachute-opening attribute testing, parachute-opening power is substantially noiseless to balance and will not damage balance, balance and parachute mould
The connection of type support meanss is firm.
Brief description of the drawings
Fig. 1 is the experimental rig structural representation of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention；
Fig. 2 is the parachute opener in the experimental rig of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention（Do not include
Umbrella cabin blanking cover, thin wire）A to schematic diagram；
Fig. 3 is the rod-type of the back taper inner cone in the experimental rig of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention
Strain balance geometric shape schematic diagram.
In figure, the umbrella cabin blanking cover of 1. parachute model supporting device, 2. balance, 3. rotor, 4. parachute model 5.
6. 12. support frame of thin wire 7. nut, I 8. screw rod, I 9. bolt, I 10. bearing, 11. stepper motor 13. is at a high speed
The high wind tunnel testing section hole wall of III 16. bolt of test chamber tail supporting mechanism 14. bolt, II 15. bolt IV 17.
101. the latch I of 103. umbrella cabin of dummy vehicle 301. that high-speed wind tunnel hole wall bracket 102. is slowed down using parachute
The stepper motor of 304. latch of rotation section, II 401. umbrella connecting rope 1101. of the rotor of canned paragraph 303. of 302. rotors
The housing of the stepper motor of rotating shaft 1102..
Embodiment
The present invention is described in detail below in conjunction with drawings and examples.
It is required in being described below to embodiment in order to illustrate more clearly of the present invention or the technical scheme of prior art
The accompanying drawing used is briefly described, it should be apparent that, drawings in the following description are some embodiments of the present invention, for
For those of ordinary skill in the art, on the premise of not paying creative work, other can also be obtained according to these accompanying drawings
Accompanying drawing.
Embodiment 1
As Figure 1-3, the experimental rig of measurement high-speed wind tunnel parachute model parachute-opening characteristic of the invention includes parachute mould
Type support meanss 1, balance 2, rotor 3 and parachute opener, the front end of balance 2 are connected with parachute model supporting device 1, balance 2
Rear end be connected with the canned paragraph 302 of rotor 3, parachute model 4 is connected with the rotation section 303 of rotor 3, parachute model 4
The umbrella cabin blanking cover 5 of canopy top and parachute opener is connected with cotton thread；
Described parachute model supporting device 1 includes high-speed wind tunnel hole wall bracket 101 and the aircraft to slow down using parachute
Model 102, balance metallic channel is left in the wall bracket of high-speed wind tunnel hole, transmitted for balance signal；
Described balance 2 is the beam strain-gauge balance of back taper inner cone, and the rear end of balance 2 has to be connected with the canned paragraph of rotor 3 302
Pin hole；
Described rotor 3 divides to be connected for canned paragraph 302, rotation two parts of section 303, canned paragraph 302 with the rear end of balance 2, rotates section
303 are connected with parachute model 4；
Described parachute opener includes umbrella cabin blanking cover 5, thin wire 6, nut 7, screw rod I 8, bearing 10, stepper motor 11, support frame
12, one end of thin wire 6 is connected with umbrella cabin blanking cover 5, and the other end of thin wire 6 is connected by the through hole on the top of nut 7 with nut 7
Connect, nut 7 is arranged on screw rod I 8, and screw rod I 8 is fixed in the rotating shaft 1102 of stepper motor 11 by bolt I 9, and bearing 10 is logical
Cross bolt II 14 to be connected with the housing 1101 of stepper motor 11, bearing 10 is connected by bolt III 15 with support frame 12.
Described cotton thread is the thin cotton thread of commercially available sewing；Described thin wire is commercially available iron wire, and iron wire diameter is about 2
Millimeter.
The course of work of the experimental rig of the measurement high-speed wind tunnel parachute model parachute-opening characteristic of the present invention is as follows：
A. the mode being connected by screw bolts, parachute model supporting device 1 is installed on high wind tunnel testing section hole wall 17；
B. it is connected using the back taper cavity in the dummy vehicle 102 of parachute deceleration and the back taper of the front end of balance 2, balance
2 are fixed in the dummy vehicle 102 to be slowed down using parachute of parachute model supporting device 1, wire and the high speed of balance 2
Wind tunnel data acquisition system connects；
C. the canned paragraph 302 of rotor 3 is connected by latch I 301 with balance rear end, and the rotation section 303 of rotor 3 passes through latch II
304 are connected with the umbrella connecting rope 401 of parachute model 4, after parachute model canopy top is connected with umbrella cabin blanking cover 5 with cotton thread,
Umbrella cabin blanking cover 5 blocks parachute model 4 in umbrella cabin 103；
D. bearing 10 is connected by bolt II 14 with the housing 1101 of stepper motor 11, and bearing 10 passes through bolt III 15 and support frame
12 connections, support frame 12 are arranged on high wind tunnel testing section tail supporting mechanism 13 by bolt IV 16, and nut 7 is arranged on screw rod
On I 8, screw rod I 8 is fixed in the rotating shaft 1102 of stepper motor 11 by bolt I 9；
E. the direction of rotation of the rotating shaft 1102 of stepper motor 11 is determined so that during the rotation of the rotating shaft 1102 of stepper motor 11, spiral shell
Moved after mother 7, when stepper motor 11 works, the rotating shaft 1102 of stepper motor 11 drives screw rod I 8 to rotate, 7, nut on screw rod I 8
Divide in the groove of bearing 10, nut 7 can not rotate, and nut 7 can only move forward and backward；
F. connected between nut 7 and umbrella cabin blanking cover 5 with thin wire 6；
G. when the air-flow in high wind tunnel testing section reaches defined flow field condition, stepper motor 11 works, and moves and incites somebody to action after nut 7
Umbrella cabin blanking cover 5 and parachute model 4 are extracted out of umbrella cabin 103, and parachute model 4 is opened under action of high-speed airflow, in parachute-opening
During, high-speed wind tunnel number carries out continuous acquisition according to acquisition system to the measured value of balance 2, in parachute model 4 out of umbrella cabin 103
After extraction, because the movement velocity of umbrella cabin blanking cover 5 is faster than parachute model 4, canopy top and the connection cotton thread of umbrella cabin blanking cover 5 are rapid
It is pulled off, compared with the aerodynamic loading of parachute model 4, load that the connection cotton thread of canopy top and umbrella cabin blanking cover 5 can be born
Very little, the influence to the aerodynamics force measurement result of parachute model 4 can be ignored；
H. high-speed wind tunnel blowing terminates, and experiment is completed, and the parachute-opening characteristic of parachute model 4 is obtained by the measured value result of balance 2.
Claims (1)
- A kind of 1. experimental rig for measuring high-speed wind tunnel parachute model parachute-opening characteristic, it is characterised in that described experimental rig Including parachute model supporting device（1）, balance（2）, rotor（3）And parachute opener, balance（2）Front end and parachute model Support meanss（1）Connection, balance（2）Rear end and rotor（3）Canned paragraph（302）Connection, parachute model（4）With rotor （3）Rotation section（303）Connection, parachute model（4）Canopy top and parachute opener umbrella cabin blanking cover（5）Connected with cotton thread Connect；Described balance（2）For the beam strain-gauge balance of back taper inner cone, balance（2）Rear end has and rotor（3）Canned paragraph （302）Connected pin hole；Described rotor（3）It is divided into canned paragraph（302）, rotation section（303）Two parts, canned paragraph（302）With balance（2）Rear end phase Even, section is rotated（303）With parachute model（4）It is connected；Described parachute opener includes umbrella cabin blanking cover（5）, thin wire（6）, nut（7）, screw rod I（8）, bearing（10）, stepping electricity Machine（11）, support frame（12）, thin wire（6）One end and umbrella cabin blanking cover（5）Connection, thin wire（6）The other end pass through nut （7）The through hole and nut on top（7）Connection, nut（7）Installed in screw rod I（8）On, screw rod I（8）Pass through bolt I（9）It is fixed on Stepper motor（11）Rotating shaft（1102）On, bearing（10）Pass through bolt II（14）With stepper motor（11）Housing（1101）Even Connect, bearing（10）Pass through bolt III（15）With support frame（12）Connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711373694.3A CN107856867B (en) | 2017-12-19 | 2017-12-19 | A kind of experimental rig measuring high-speed wind tunnel parachute model parachute-opening characteristic |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711373694.3A CN107856867B (en) | 2017-12-19 | 2017-12-19 | A kind of experimental rig measuring high-speed wind tunnel parachute model parachute-opening characteristic |
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| Publication Number | Publication Date |
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| CN107856867A true CN107856867A (en) | 2018-03-30 |
| CN107856867B CN107856867B (en) | 2019-11-08 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109141805A (en) * | 2018-09-20 | 2019-01-04 | 北京空间机电研究所 | A kind of parachute aerodynamic coefficient and torque coefficient calculation method and system |
| CN109186931A (en) * | 2018-09-12 | 2019-01-11 | 温州大学瓯江学院 | It is a kind of for testing the test method of umbrella stand umbrella frame wind loading rating |
| CN109186930A (en) * | 2018-09-12 | 2019-01-11 | 温州大学瓯江学院 | It is a kind of for testing the device of umbrella stand mobile jib wind loading rating |
| CN109238629A (en) * | 2018-09-12 | 2019-01-18 | 温州大学瓯江学院 | It is a kind of for testing the test method of umbrella stand mobile jib wind loading rating |
| CN109238628A (en) * | 2018-09-12 | 2019-01-18 | 温州大学瓯江学院 | It is a kind of for testing the device of umbrella stand umbrella frame wind loading rating |
| CN112098037A (en) * | 2020-08-11 | 2020-12-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Self-adaptive variable-resistance stabilizing umbrella resistance characteristic and deformation measurement test device and method |
| CN116659804A (en) * | 2023-07-21 | 2023-08-29 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel speed-reducing umbrella force-measuring balance |
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| JPH0848300A (en) * | 1994-08-08 | 1996-02-20 | Mitsubishi Heavy Ind Ltd | Parachute tester |
| CN105222979A (en) * | 2015-10-13 | 2016-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of device for the protection of parachute performance supersonic wind tunnel test parachute body |
| CN207607655U (en) * | 2017-12-19 | 2018-07-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of experimental rig measuring high-speed wind tunnel parachute model parachute-opening characteristic |
-
2017
- 2017-12-19 CN CN201711373694.3A patent/CN107856867B/en not_active Expired - Fee Related
Patent Citations (3)
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|---|---|---|---|---|
| JPH0848300A (en) * | 1994-08-08 | 1996-02-20 | Mitsubishi Heavy Ind Ltd | Parachute tester |
| CN105222979A (en) * | 2015-10-13 | 2016-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of device for the protection of parachute performance supersonic wind tunnel test parachute body |
| CN207607655U (en) * | 2017-12-19 | 2018-07-13 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of experimental rig measuring high-speed wind tunnel parachute model parachute-opening characteristic |
Non-Patent Citations (1)
| Title |
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| 杨贤文等: "阻力伞及气囊气动特性风洞试验技术研究", 《实验流体力学》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109186931A (en) * | 2018-09-12 | 2019-01-11 | 温州大学瓯江学院 | It is a kind of for testing the test method of umbrella stand umbrella frame wind loading rating |
| CN109186930A (en) * | 2018-09-12 | 2019-01-11 | 温州大学瓯江学院 | It is a kind of for testing the device of umbrella stand mobile jib wind loading rating |
| CN109238629A (en) * | 2018-09-12 | 2019-01-18 | 温州大学瓯江学院 | It is a kind of for testing the test method of umbrella stand mobile jib wind loading rating |
| CN109238628A (en) * | 2018-09-12 | 2019-01-18 | 温州大学瓯江学院 | It is a kind of for testing the device of umbrella stand umbrella frame wind loading rating |
| CN109141805A (en) * | 2018-09-20 | 2019-01-04 | 北京空间机电研究所 | A kind of parachute aerodynamic coefficient and torque coefficient calculation method and system |
| CN109141805B (en) * | 2018-09-20 | 2020-10-23 | 北京空间机电研究所 | Parachute aerodynamic coefficient and moment coefficient calculation method and system |
| CN112098037A (en) * | 2020-08-11 | 2020-12-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Self-adaptive variable-resistance stabilizing umbrella resistance characteristic and deformation measurement test device and method |
| CN112098037B (en) * | 2020-08-11 | 2022-05-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Self-adaptive variable-resistance stabilizing umbrella resistance characteristic and deformation measurement test device and method |
| CN116659804A (en) * | 2023-07-21 | 2023-08-29 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel speed-reducing umbrella force-measuring balance |
| CN116659804B (en) * | 2023-07-21 | 2023-10-10 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel speed-reducing umbrella force-measuring balance |
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Granted publication date: 20191108 Termination date: 20211219 |