CN114180074A - Method for adjusting main parameter installation angle of ram parafoil - Google Patents
Method for adjusting main parameter installation angle of ram parafoil Download PDFInfo
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- CN114180074A CN114180074A CN202111590657.4A CN202111590657A CN114180074A CN 114180074 A CN114180074 A CN 114180074A CN 202111590657 A CN202111590657 A CN 202111590657A CN 114180074 A CN114180074 A CN 114180074A
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- parafoil
- umbrella rope
- installation angle
- umbrella
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- IBSREHMXUMOFBB-JFUDTMANSA-N 5u8924t11h Chemical compound O1[C@@H](C)[C@H](O)[C@@H](OC)C[C@@H]1O[C@@H]1[C@@H](OC)C[C@H](O[C@@H]2C(=C/C[C@@H]3C[C@@H](C[C@@]4(O3)C=C[C@H](C)[C@@H](C(C)C)O4)OC(=O)[C@@H]3C=C(C)[C@@H](O)[C@H]4OC\C([C@@]34O)=C/C=C/[C@@H]2C)/C)O[C@H]1C.C1=C[C@H](C)[C@@H]([C@@H](C)CC)O[C@]11O[C@H](C\C=C(C)\[C@@H](O[C@@H]2O[C@@H](C)[C@H](O[C@@H]3O[C@@H](C)[C@H](O)[C@@H](OC)C3)[C@@H](OC)C2)[C@@H](C)\C=C\C=C/2[C@]3([C@H](C(=O)O4)C=C(C)[C@@H](O)[C@H]3OC\2)O)C[C@H]4C1 IBSREHMXUMOFBB-JFUDTMANSA-N 0.000 title claims abstract description 53
- 238000009434 installation Methods 0.000 title claims abstract description 47
- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000012360 testing method Methods 0.000 claims abstract description 28
- 238000011056 performance test Methods 0.000 claims description 7
- 238000010276 construction Methods 0.000 claims 2
- 238000004080 punching Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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Classifications
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The application provides a method for adjusting a main parameter installation angle of a ram parafoil, which comprises the following steps: step 1: before the test work of the model parafoil, when the front edge 1 is rotated counterclockwise from the position a to the position a1 with the aerodynamic center 2 as the origin, the rear edge 3 is rotated from the position b to the position b1 with the aerodynamic center 2 as the origin. The front edge umbrella rope 4 is shortened, the rear edge umbrella rope 5 is lengthened, the disc 6 rotates anticlockwise, and at the moment, the installation angle is changed into beta; step 2: when the mounting angle is adjusted to the position, the front edge umbrella rope 5 and the rear edge umbrella rope 4 are respectively drawn close to the middle clamp and limited by the umbrella rope limiting clamp 7, and are attached to the disc 6 as tightly as possible; and step 3: suspending the disk fixing bolt 8 until the disk fixing bolt is pushed into a groove on the outer side of the disk 6, and fixing the disk 6, wherein the position is the position of the installation angle to be detected of the parafoil; and 4, step 4: after the test in the wind tunnel is finished, the disc fixing bolt 8 is released, the umbrella rope limiting clamp 7 is loosened, and the disc 6 is rotated clockwise or anticlockwise to reach a preset position.
Description
Technical Field
The invention relates to the field of ram parafoil, in particular to a method for adjusting a main parameter installation angle of a ram parafoil.
Background
The ram parachute is a wing type formed by inflating and fully opening the ram air, so the ram parachute is required to be inflated and fully opened through the ram air at a certain installation angle, and meanwhile, the ram parachute has the optimal lift-drag ratio relationship at a certain installation angle, so that the ram parachute has good lift-drag ratio characteristics and gliding performance. The mounting angle refers to the angle between the reference chord line and the horizontal plane when the parafoil stably glides. The existing ram parafoil largely depends on the actual result of the engineering to perform reverse verification in the performance simulation process, and the reference significance is not great when the ram parafoil is designed in the engineering. When the stamping parafoil is actually designed, the main parameter mounting angle is the only parameter which can be adjusted after the canopy is processed. Generally, all the complete parachute line sets need to be processed to complete the adjustment and the test of the installation angle. Therefore, several groups of umbrella ropes need to be processed for testing after testing several installation angles, the number of the umbrella ropes of the common stamping parafoil is large, the number of the small parafoil is dozens of parachute ropes, the number of the large parafoil is hundreds, and if the test is carried out and the replacement is carried out, a large amount of manpower and financial waste are caused.
Disclosure of Invention
The application provides a method for adjusting a main parameter installation angle of a ram parafoil, which is characterized in that a model parafoil wind tunnel test is utilized to continuously test the installation angle within a certain range, so that the requirement of performance test can be met, and a large number of parachute ropes do not need to be processed to be repeatedly disassembled, assembled and replaced.
The technical scheme is as follows: a method for adjusting a main parameter installation angle of a ram parafoil, comprising the following steps of:
step 1: before the test work of the model parafoil, the front edge 1 is at the position a, the rear edge 3 is at the position b, the installation angle is-alpha, and when the front edge 1 is rotated anticlockwise to the position a1 from the position a by taking the aerodynamic center 2 as the origin, the rear edge 3 is rotated to the position b1 from the position b by taking the aerodynamic center 2 as the origin. The front edge umbrella rope 4 is shortened, the rear edge umbrella rope 5 is lengthened, the disc 6 rotates anticlockwise, and at the moment, the installation angle is changed into beta;
step 2: when the mounting angle is adjusted to the position, the front edge umbrella rope 5 and the rear edge umbrella rope 4 are respectively drawn close to the middle clamp and limited by the umbrella rope limiting clamp 7, and are attached to the disc 6 as tightly as possible;
and step 3: suspending the disk fixing bolt 8 until the disk fixing bolt is pushed into a groove on the outer side of the disk 6, and fixing the disk 6, wherein the position is the position of the installation angle to be detected of the parafoil;
and 4, step 4: after the test in the wind tunnel is completed, the disc fixing bolt 8 is released, the umbrella rope limiting clamp 7 is loosened, the disc 6 is rotated clockwise or anticlockwise to reach the preset position, the disc is fixed again and repeatedly, the performance test can be performed on the installation angle of the parafoil within a range until the test is completed, and the optimal performance matching position is found out.
Specifically, ab is the chord line and the mount angle is the angle of the chord line from horizontal.
Specifically, the adjustment range of the installation angle can be adjusted between-15 degrees and 15 degrees.
Specifically, when the umbrella rope at the farthest position on the two sides corresponding to the point o is completely released for the longest time, the umbrella rope at the other side is wound on the disc for the shortest time.
Specifically, the disc 6 is of a coaxial structure, different radiuses can be fixed on the same symmetrical center through shaft pins, and the structure of the disc is arranged according to the corresponding length of the umbrella rope in an equal ratio.
Specifically, the radius of the disc 6 corresponding to each group of the umbrella ropes is respectively equal to the distance between the connecting point of the umbrella ropes and the rotating center.
Specifically, the distance oa to the o point of the umbrella ropes at the front edge and the rear edge is 1 to 3, and the radius of the disc corresponding to the front edge and the rear edge is 1 to 3.
Specifically, when the leading edge moves from the point a to the point a1 and the trailing edge moves from the point b to the position b1, the disk rotates by θ degrees, and the rotation length ratio 2 pi R θ:2 pi R θ of the disk corresponding to the leading edge and the trailing edge is 1: 3.
In summary, the present application provides a method for adjusting a main parameter installation angle of a ram parafoil, wherein after basic parameters of the ram parafoil are determined, a similar model parafoil is designed, and by using a wind tunnel test of the model parafoil, under the constraint of a coaxial disc, each parachute cord group can change within the value range, and the length of each parachute cord enables a main component for ensuring the installation angle of the parafoil, so that when the coaxial disc rotates, the installation direction of each parachute cord group is extended or shortened, the installation angle changes, and the wing surface can be kept flat. The lift-drag coefficient of the wind tunnel test is tested, and the mounting angle corresponding to the optimal lift-drag ratio can be determined quickly. According to the invention, firstly, the model parafoil is used for carrying out the performance test of the large parafoil with the same similarity ratio, so that the complex work required for testing the main performance ratio when the large parafoil is produced can be avoided, for example, a large number of parachute cord groups are produced, the parachute cords are repeatedly installed and disassembled, the test range of the installation angle is discrete, the test method is unchanged, and the like, and the wind tunnel test is utilized for carrying out the performance test verification of the model parafoil variable installation angle, so that the resource is saved, and the practical application value is achieved.
Drawings
The invention is further described with reference to the following figures and examples.
Fig. 1 is a schematic view of a model parafoil mounting angle adjustment test provided in an embodiment of the present invention.
In the figure: 1-front edge, 2-pneumatic center, 3-rear edge, 4-rear edge umbrella rope, 5-front edge umbrella rope, 6-disc, 7-umbrella rope limit clamp and 8-disc fixing bolt.
Detailed Description
The application provides a confirm that punching press parafoil best lift-drag ratio correlation parameter mounting angle is convenient timing method, when solving punching press parafoil main parameter mounting angle timing, need produce the umbrella rope that the processing multiunit is different on the one hand, a set of umbrella rope need be changed to a mounting angle of on the other hand test, secondly is that the mounting angle of test is discrete, the inconvenient problem that causes a large amount of wastes of operation. The method is characterized in that a parafoil scaling model parafoil designed in advance is utilized, the pneumatic center of a stamping parafoil is taken as the center, four groups of parachute cords are designed generally at one quarter of the chord direction, concentric discs capable of rotating are designed according to the equal ratio of the distances between the chord direction front parachute cords and the chord direction rear parachute cords and the pneumatic center, the discs are installed at the umbrella cord junction, the parachute cords can be connected to the equal ratio disc parachute cord junction, when the discs rotate integrally, the installation angle of the stamping parafoil can be changed, and the purpose of adjusting the installation angle in real time and rapidly to perform adjustment and calibration tests is achieved.
The technical scheme of the invention is as follows: the large or ultra-large parafoil scheme is initially designed by using a model parachute, the scaled model parachute is designed, the performance test in a common wind tunnel is facilitated due to the small area, the model parafoil is divided into four equal parts according to the chord direction, four groups of parachute ropes are designed according to the maximum value in the adjustment range of the installation angle, the minimum value position is marked, the minimum value position is checked by the mark when the parachute ropes are installed, and all the groups of parachute ropes are designed according to the requirements.
The method is characterized in that coaxial disks with equal ratio are designed at the intersection of umbrella ropes of each group of the stamping parafoil according to the distances between the chord-wise front and rear parachute ropes and the pneumatic center, the parachute ropes at the front and rear of the pneumatic center are wound in the counterclockwise direction and the clockwise direction respectively, and the longest ends of the parachute ropes are fixed on the disks. When rotating clockwise with the axle center disc, two sets of umbrella ropes before the pneumatic center release extension, and two sets of umbrella ropes of rear end twine and shorten to the disc on, utilize interim fixed clamp to carry out spacingly respectively, simultaneously, utilize lower extreme expansion nut to carry out spacingly with the disc. At the moment, four umbrella ropes connected with the lower end of the umbrella coat are kept on the same line.
When the mounting angle needs to be changed, the movable clamp for limiting the umbrella rope is loosened, the telescopic nut releases the disc for limiting, after the mounting angle is changed, the umbrella rope and the disc are respectively limited, and the mounting angle can be finely adjusted repeatedly to perform performance testing.
The present invention will be described in further detail below by way of specific embodiments:
as shown in fig. 1, a working diagram for adjusting the installation angle of a model parafoil provided in the embodiment of the present invention includes:
step 1: before the test work of the model parafoil, the front edge 1 is at the position a, the rear edge 3 is at the position b, the installation angle is-alpha, and when the front edge 1 is rotated anticlockwise to the position a1 from the position a by taking the aerodynamic center 2 as the origin, the rear edge 3 is rotated to the position b1 from the position b by taking the aerodynamic center 2 as the origin. The front edge cord 4 is shortened, the rear edge cord 5 is lengthened, the disc 6 rotates anticlockwise, and at the moment, the mounting angle is changed to beta.
Specifically, ab is the chord line and the mount angle is the angle of the chord line from horizontal.
Note that the front edge cord 5 and the rear edge cord 4 are broken line lengths.
Step 2: when the installation angle is adjusted to the position, the umbrella rope limiting clamp 7 is used for enabling the front edge umbrella rope 5 and the rear edge umbrella rope 4 to respectively draw close to the middle clamp and limit, and the front edge umbrella rope and the rear edge umbrella rope are attached to the disc 6 as tightly as possible.
And step 3: and (3) hanging the disk fixing bolt 8 upwards until the disk fixing bolt is pushed into a groove on the outer side of the disk 6, and fixing the disk 6, wherein the position is the position of the installation angle to be measured of the parafoil.
And 4, step 4: after the test in the wind tunnel is completed, the disc fixing bolt 8 is released, the umbrella rope limiting clamp 7 is loosened, the disc 6 is rotated clockwise or anticlockwise to reach the preset position, the disc is fixed again and repeatedly, the performance test can be performed on the installation angle of the parafoil within a range until the test is completed, and the optimal performance matching position is found out.
It should be noted that the parafoil installation angle is determined by adjusting the length of the parachute cord below the chord line, in fig. 1, ab is the chord line, the installation angle is the included angle between the chord line and the horizontal line, and the performance of the parafoil installation angle can be optimized by adjusting the installation angle of the parafoil.
Specifically, the adjustment range of the installation angle can be adjusted between-15 degrees and 15 degrees.
The parachute cords of the parafoil can continuously change and adjust the installation angle of the parafoil, and the designed initial size of each group of parachute cords can meet the size requirement in the installation angle adjustment range.
Specifically, when the umbrella rope at the farthest position on the two sides corresponding to the point o is completely released for the longest time, the umbrella rope at the other side is wound on the disc for the shortest time.
Specifically, the disc 6 is of a coaxial structure, different radiuses can be fixed on the same symmetrical center through shaft pins, and the structure of the disc is arranged according to the corresponding length of the umbrella rope in an equal ratio.
Specifically, the radius of the disc 6 corresponding to each group of the umbrella ropes is respectively equal to the distance between the connecting point of the umbrella ropes and the rotating center.
During initial installation, the shortest front edge umbrella rope and the longest rear edge umbrella rope can be respectively connected and fixed at corresponding positions on the disc; at this time, the longest dimension of the front edge umbrella rope is subtracted by the shortest dimension, namely the winding length of the front edge umbrella rope on the disc is needed, and other grouped umbrella ropes are shortened in the same way. At each corresponding mounting angle position, all the groups of umbrella ropes are in a tight state.
For example, if the distance oa to ob of the umbrella ropes of the front edge and the rear edge is 1 to 3 corresponding to the point o, the radius of the disc corresponding to the front edge and the rear edge is also 1 to 3, and if the front edge moves from the point a to the point a1, the rear edge moves from the point b to the position b1, at this time, the disc rotates by theta degrees, and the rotating length ratio of the disc corresponding to the front edge and the rear edge is 2 pi R theta to 1 to 3. When the disk fixing bolt rotates to the position, the disk fixing bolt is suspended upwards, the disk is tightly propped to limit the rotation of the disk, the performance of the parafoil under the installation angle can be tested, the installation angle is continuously changed according to the method after the test is finished, and the measurement is continuously carried out until the installation angle position with the best performance is found out.
Claims (8)
1. The method for adjusting the main parameter installation angle of the ram parafoil is characterized by comprising the following steps:
step 1: before the test work of the model parafoil, the front edge (1) is at the position a, the rear edge (3) is at the position b, the installation angle is-alpha, and when the front edge (1) rotates anticlockwise to the position a1 from the position a by using the aerodynamic center (2), the rear edge (3) rotates to the position b1 by using the aerodynamic center (2) as an origin. The front edge umbrella rope (4) is shortened, the rear edge umbrella rope (5) is lengthened, the disc (6) rotates anticlockwise, and at the moment, the mounting angle is changed into beta;
step 2: when the mounting angle is adjusted to the position, the front edge umbrella rope (5) and the rear edge umbrella rope (4) are respectively drawn close to the middle clamp and limited by the umbrella rope limiting clamp (7), and are attached to the compact disc (6) as much as possible;
and step 3: suspending the disc fixing bolt (8) until the disc fixing bolt is jacked into a groove on the outer side of the disc (6), and fixing the disc (6), wherein the position is the position of the installation angle to be measured of the parafoil;
and 4, step 4: after the test in the wind tunnel is completed, the disc fixing bolt (8) is released, the umbrella rope limiting clamp (7) is loosened, when the disc (6) rotates clockwise or anticlockwise to reach the preset position, the disc is fixed again and repeatedly, the performance test can be carried out on the installation angle of the parafoil within a range until the test is completed, and the optimal performance matching position is found out.
2. The method of claim 1 wherein ab is chord line and the setting angle is the angle of the chord line from horizontal.
3. A method according to claim 1, characterized in that the adjustment range of the setting angle is adjustable between-15 ° and 15 °.
4. The method of claim 1, wherein when the umbrella strings at one side are all released the longest corresponding to the farthest umbrella strings at both sides of the o-point, the umbrella strings at the other side are wound on the disc to be the shortest.
5. Method according to claim 1, characterized in that the disks (6) are of coaxial construction, the different radii being fixable using pins in the same symmetrical centre, the construction being such that the lengths of the cords are equal.
6. Method according to claim 1, characterized in that the radius of the disc (6) corresponding to each group of cords is in equal proportion to the distance between the connection point of the cords and the centre of rotation.
7. The method of claim 1, wherein the distance oa to ob of the o point of the umbrella ropes of the front edge and the rear edge is 1:3, and the radius of the disc corresponding to the front edge and the rear edge is 1: 3.
8. The method of claim 7, wherein if the leading edge moves from point a to a1 and the trailing edge moves from b to b1, the disk rotates by θ degrees, and the leading edge and the trailing edge each correspond to a disk rotation length ratio of 2 π R θ:2 π R θ ═ 1: 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111590657.4A CN114180074B (en) | 2021-12-23 | 2021-12-23 | Method for adjusting main parameter installation angle of punching parafoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111590657.4A CN114180074B (en) | 2021-12-23 | 2021-12-23 | Method for adjusting main parameter installation angle of punching parafoil |
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| CN114180074A true CN114180074A (en) | 2022-03-15 |
| CN114180074B CN114180074B (en) | 2023-10-20 |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5303883A (en) * | 1993-07-16 | 1994-04-19 | The United States Of America As Represented By The Secretary Of The Army | Gliding decelerator including an assembly for improving the lift to drag ratio associated therewith |
| CN2193322Y (en) * | 1994-04-15 | 1995-03-29 | 王嘉謇 | Aerated winged parachute |
| CN105109681A (en) * | 2015-09-16 | 2015-12-02 | 航宇救生装备有限公司 | Unmanned power parafoil with adjustable mounting angle |
| CN106092497A (en) * | 2016-06-21 | 2016-11-09 | 西北工业大学 | A kind of erecting device of flex-wing |
| RU2655713C1 (en) * | 2017-07-06 | 2018-05-29 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for the gliding parachute aerodynamic characteristics measuring in wind tunnel, gliding parachute model for tests in wind tunnel, method of gliding parachute aerodynamic characteristics measuring in wind tunnel |
| CN109292110A (en) * | 2018-08-23 | 2019-02-01 | 淮阴工学院 | A kind of parafoil longitudinal direction Aerodynamic Coefficient estimating system and its evaluation method |
| RU2714529C1 (en) * | 2019-04-08 | 2020-02-18 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for determining aerodynamic characteristics of a gliding parachute in a wind tunnel |
| CN111947905A (en) * | 2020-08-07 | 2020-11-17 | 南京航空航天大学 | Parachute cord operating force adjusting and measuring device |
| CN112254919A (en) * | 2020-10-16 | 2021-01-22 | 航宇救生装备有限公司 | Wind tunnel test device for aerodynamic characteristics and manipulation characteristics of flexible parafoil |
-
2021
- 2021-12-23 CN CN202111590657.4A patent/CN114180074B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5303883A (en) * | 1993-07-16 | 1994-04-19 | The United States Of America As Represented By The Secretary Of The Army | Gliding decelerator including an assembly for improving the lift to drag ratio associated therewith |
| CN2193322Y (en) * | 1994-04-15 | 1995-03-29 | 王嘉謇 | Aerated winged parachute |
| CN105109681A (en) * | 2015-09-16 | 2015-12-02 | 航宇救生装备有限公司 | Unmanned power parafoil with adjustable mounting angle |
| CN106092497A (en) * | 2016-06-21 | 2016-11-09 | 西北工业大学 | A kind of erecting device of flex-wing |
| RU2655713C1 (en) * | 2017-07-06 | 2018-05-29 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for the gliding parachute aerodynamic characteristics measuring in wind tunnel, gliding parachute model for tests in wind tunnel, method of gliding parachute aerodynamic characteristics measuring in wind tunnel |
| CN109292110A (en) * | 2018-08-23 | 2019-02-01 | 淮阴工学院 | A kind of parafoil longitudinal direction Aerodynamic Coefficient estimating system and its evaluation method |
| RU2714529C1 (en) * | 2019-04-08 | 2020-02-18 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for determining aerodynamic characteristics of a gliding parachute in a wind tunnel |
| CN111947905A (en) * | 2020-08-07 | 2020-11-17 | 南京航空航天大学 | Parachute cord operating force adjusting and measuring device |
| CN112254919A (en) * | 2020-10-16 | 2021-01-22 | 航宇救生装备有限公司 | Wind tunnel test device for aerodynamic characteristics and manipulation characteristics of flexible parafoil |
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