CN105416594A - Aerodynamic decelerator - Google Patents
Aerodynamic decelerator Download PDFInfo
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- CN105416594A CN105416594A CN201510884877.6A CN201510884877A CN105416594A CN 105416594 A CN105416594 A CN 105416594A CN 201510884877 A CN201510884877 A CN 201510884877A CN 105416594 A CN105416594 A CN 105416594A
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- aerofoil
- elastic component
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- momentum
- aerodynamic
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- 230000000694 effects Effects 0.000 claims description 9
- 230000000712 assembly Effects 0.000 abstract 2
- 238000000429 assembly Methods 0.000 abstract 2
- 238000005516 engineering process Methods 0.000 description 6
- 230000003042 antagnostic effect Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 2
- 235000017491 Bambusa tulda Nutrition 0.000 description 2
- 241001330002 Bambuseae Species 0.000 description 2
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 239000011425 bamboo Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 241000555922 Potamogeton crispus Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
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
- B64D17/00—Parachutes
- B64D17/02—Canopy arrangement or construction
- B64D17/14—Canopy arrangement or construction with skirt or air-deflecting panels
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to an aerodynamic decelerator which comprises a canopy and a plurality of dense momentum adjusting assemblies. The canopy comprises a top face and a side face. The dense momentum adjusting assemblies are evenly distributed on the top face and the side face of the canopy and comprise return locks, first wind plates, second wind plates, first elastic pieces, second elastic pieces and wind plate clamps. The design scheme of the aerodynamic decelerator capable of automatically adjusting the dense momentum is creatively provided. Compared with the prior art, the aerodynamic decelerator is based on the hydromechanical basic principle, and the aerodynamic decelerator has the automatic adjusting function on the dense momentum by means of the design of one-way air channels, the wind plates, the wind plate clamps, the return locks and the elastic pieces. A pair of acting force and counter acting force is formed by aerodynamic force formed by the wind plates and elastic force, provided by the elastic pieces, of the return locks, and the aerodynamic decelerator achieves the automatic adjusting function on the dense momentum by changing the included angle between the wind plates and the canopy.
Description
Technical field
The present invention relates to aerospace, extreme sport security fields, is a kind of aerodynamic decel erator automatically regulated close momentum specifically.
Background technology
Aerodynamic decel erator refers to parachute.Parachute, as typical aerodynamic decel erator, is applied very extensive in extreme sport and aerospace field.From literature record, first uses the people of aerodynamic decel erator (bamboo hat) to be Shun.With Galileo carry out on the leaning tower of Piza falling body experiment unlike, never Chinese go to think deeply the reason that Shun does not fall to death.Fortunately, maximum in the world at present Shenzhou spacecraft parachute is still made in China." as gunpowder, parachute also spreads out of from China " saying has card can be target-seeking.
Although existing parachute varies on morphosis, could not break away from a problem all the time: canopy is larger, it is larger that canopy collapses brokenly risk.On earth, in order to carry larger load, the array mode of deceleration parachute+main chute is widely used.And for only having the Mars of earth atmosphere density 1%, existing input weight can not more than 1.5 tons of landing technology (guaranteeing to throw in instrument and equipment safety), just govern the mars exploration task requiring to throw in about 500 tons of goods and materials, need new landing concept.Although invented space parachute, when it is tested first, retarder is torn into this fact of fragment and shows that many problems have to be solved in addition.In addition, space shuttle as one of Space Science and Technology mile stone is abandoned, its essence is also how to solve lower density hyprsonic problem, and the high temperature due to high-speed flight causes the infringement of most of instrument to make single emission excess budget nearly ten times (expense of single emission is about 4.5 hundred million dollars).From momentum theorem, on unit area, the density of gas and speed determine the size of the aerodynamic force of retarder.So-called lower density hyprsonic, just refers to the close momentum on unit area.Close momentum on the windward side of object is defined as: (wherein, ρ is density of air to ρ s ν; S is the windward side area of object; ν is the speed of relative movement of object and air).
2020 Mars programs from we more and more close to, lower density supersonic deceleration device decides the implementation process of this grand engineering.Past in several thousand, the bamboo hat that Shun crosses except changing on material and form, and its basic function does not change.Therefore, design aerodynamic decel erator, making it have multistage automatic regulation function to close momentum is a gordian technique urgently broken through.Along with the development of extreme sport, aeronautical and space technology, how to design that to have to close momentum the aerodynamic decel erator automatically regulated be the key of dealing with problems.
Summary of the invention
Technical matters to be solved by this invention is to provide a kind of aerodynamic decel erator that automatically can regulate close momentum.
In order to solve the problems of the technologies described above, the technical solution used in the present invention is:
A kind of aerodynamic decel erator, comprise canopy and multiple close momentum adjusting part, described canopy comprises end face and side, on the end face that multiple close momentum adjusting part is evenly distributed on canopy and side, described close momentum adjusting part comprises return lock, first aerofoil, second aerofoil, first elastic component, second elastic component and aerofoil card, described return is locked for the curved rectangular hollow box body of end face, the bottom surface of described return lock is fixed on canopy, described first aerofoil is hinged on the relative two sides of return lock with the second aerofoil symmetry, the first jointed shaft that described first aerofoil and return are locked is provided with the first elastic component, the second jointed shaft that described second aerofoil and return are locked is provided with the second elastic component, described canopy offers the first unidirectional air channel and the second unidirectional air channel respectively corresponding to the first aerofoil and the second aerofoil, described first aerofoil inwardly can rotate around the first jointed shaft and close the first unidirectional air channel under the elastic force effect of the first elastic component, described second aerofoil inwardly can rotate around the second jointed shaft and close the second unidirectional air channel under the elastic force effect of the second elastic component, described aerofoil card comprises a transverse slat and is vertically set on two risers be oppositely arranged on transverse slat, described aerofoil cartoon is crossed two risers and is clamped on the first aerofoil and the second aerofoil the first aerofoil and the second aerofoil are parallel to each other.
Beneficial effect of the present invention is: the present invention creatively proposes can to the design plan of the aerodynamic decel erator that close momentum regulates automatically, compared to prior art, the present invention is based on hydromechanical groundwork, by unidirectional air channel, aerofoil, aerofoil card, return locks and the design of elastic component makes aerodynamic decel erator have automatic regulation function to close momentum; The aerodynamic force that aerofoil is formed and the elastic force (being provided by elastic component) that return is locked form a pair application force and antagonistic force, by changing the angle of aerofoil and canopy, make the automatic regulation function of aerodynamic decel erator realization to close momentum.
Accompanying drawing explanation
Figure 1 shows that the assembling schematic diagram of the aerodynamic decel erator of the embodiment of the present invention.
Figure 2 shows that the structural representation of the canopy of the embodiment of the present invention.
Figure 3 shows that the structural representation (aerofoil card drop before) of the close momentum adjusting part of the embodiment of the present invention.
Figure 4 shows that the structural representation (aerofoil card drop after) of the close momentum adjusting part of the embodiment of the present invention.
Figure 5 shows that the front elevation of Fig. 4.
Figure 6 shows that the lateral plan of Fig. 4.
Figure 7 shows that the birds-eye view of Fig. 4.
Figure 8 shows that the structural representation of the return lock of the embodiment of the present invention.
Figure 9 shows that the first aerofoil of the embodiment of the present invention and the structural representation of the second aerofoil.
Figure 10 shows that the first elastic component of the embodiment of the present invention and the structural representation of the second elastic component.
Figure 11 shows that the structural representation of the aerofoil card of the embodiment of the present invention.
Label declaration:
1-canopy; The close momentum adjusting part of 2-; 20-return is locked; The unidirectional air channel of 10-first; The unidirectional air channel of 11-second; 21-first aerofoil; 22-second aerofoil; 23-first elastic component; 24-second elastic component; 25-aerofoil card; 210-first jointed shaft; 220-second jointed shaft; 250-transverse slat; 251-riser.
Detailed description of the invention
By describing technology contents of the present invention in detail, realized object and effect, accompanying drawing is coordinated to be explained below in conjunction with embodiment.
The design of most critical of the present invention is: on canopy, offer multiple unidirectional air channel, each unidirectional air channel is provided with aerofoil, aerofoil is under the interaction of the elastic force of aerodynamic force and elastic component, can rotate relative to canopy and close or open unidirectional air channel and the openings of sizes in the unidirectional air channel of automatic adjustment, thus automatically change the wind area of canopy, make the automatic regulation function of aerodynamic decel erator realization to close momentum.
Concrete, please refer to shown in Fig. 1 to Figure 11, aerodynamic decel erator provided by the invention, comprise canopy 1 and multiple close momentum adjusting part 2, described canopy 1 comprises end face and side, on the end face that multiple close momentum adjusting part 2 is evenly distributed on canopy 1 and side, described close momentum adjusting part 2 comprises return lock 20, first aerofoil 21, second aerofoil 22, first elastic component 23, second elastic component 24 and aerofoil card 25, described return is locked for the curved rectangular hollow box body of end face, the bottom surface of described return lock is fixed on canopy, described first aerofoil 21 and the second aerofoil 22 symmetry are hinged on the relative two sides of return lock 20, the first jointed shaft 210 that described first aerofoil 21 and return lock 20 is provided with the first elastic component 23, the second jointed shaft 220 that described second aerofoil 22 and return lock 20 is provided with the second elastic component 24, described canopy 1 offers the first unidirectional air channel 10 and the second unidirectional air channel 11 respectively corresponding to the first aerofoil 21 and the second aerofoil 22, described first aerofoil 21 inwardly can rotate around the first jointed shaft 210 and close the first unidirectional air channel 10 under the elastic force effect of the first elastic component 23, described second aerofoil 22 inwardly can rotate around the second jointed shaft 220 and close the second unidirectional air channel 11 under the elastic force effect of the second elastic component 24, two risers be oppositely arranged 251 that described aerofoil card 25 comprises a transverse slat 250 and is vertically set on transverse slat 250, described aerofoil card 25 is clamped on the first aerofoil 21 and the second aerofoil 22 by two risers 251 makes the first aerofoil 21 and the second aerofoil 22 be parallel to each other.
Principle of work of the present invention is as follows:
Aerofoil card 25 comes off under Aerodynamic force action, first aerofoil 21 presents the trend that the state to the unidirectional air channel 10 of closedown first is rotated under the elastic force effect of the first elastic component 23, second aerofoil 22 presents the trend that the state to the unidirectional air channel 11 of closedown second is rotated under the elastic force effect of the second elastic component 24, and the first aerofoil 21 and the second aerofoil 22 are subject to the acting in opposition of aerodynamic force simultaneously, the aerodynamic force that aerofoil is formed and the elastic force of elastic component form a pair application force and antagonistic force.If the aerodynamic force that aerofoil is formed is less than the elastic force of elastic component, then aerofoil rotates to the direction (namely inside) closing unidirectional air channel, and the angle of aerofoil and canopy 1 diminishes, the openings get smaller in unidirectional air channel, the area of canopy 1 increases, thus improves the close momentum of aerodynamic decel erator; If the aerodynamic force that aerofoil is formed is greater than the elastic force of elastic component, then aerofoil rotates to the direction (namely outside) of opening unidirectional air channel, and the angle of aerofoil and canopy 1 becomes greatly, and the opening in unidirectional air channel becomes large, the area of canopy 1 reduces, thus reduces the close momentum of aerodynamic decel erator.By the automatic adjustment of the angle of above-mentioned aerofoil and canopy 1, aerodynamic decel erator of the present invention can realize the automatic adjustment to close momentum, and effectively prevents canopy 1 from collapsing brokenly because aerodynamic force is excessive; By designing the shape, size, elastic force etc. in aerofoil, elastic component and unidirectional air channel, the multistage automatic adjustment of the close momentum change of aerodynamic decel erator can be realized.During embody rule, at a low density, by opening unidirectional air channel, reducing Parachute area, realizing high deceleration; Under the low speed, by closing unidirectional air channel, increasing Parachute area, realizing low-range reduction.
From foregoing description, beneficial effect of the present invention is: the present invention creatively proposes can to the design plan of the aerodynamic decel erator that close momentum regulates automatically, compared to prior art, the present invention is based on hydromechanical groundwork, by unidirectional air channel, aerofoil, aerofoil card, return locks and the design of elastic component makes aerodynamic decel erator have automatic regulation function to close momentum; The aerodynamic force that aerofoil is formed and the elastic force (being provided by elastic component) that return is locked form a pair application force and antagonistic force, by changing the angle of aerofoil and canopy, make the automatic regulation function of aerodynamic decel erator realization to close momentum.
Further, described first elastic component 23 and the second elastic component 24 are torsion spring.
Further, described first aerofoil 21 and the second aerofoil 22 semicircular in shape or arc.
Further, described first elastic component 23 and the second elastic component 24 are positioned at return lock 20.
Embodiment:
The explanation of technical terms that the present invention relates to is in table 1:
Table 1 technical term
Speed is that 1.2-5 Mach is defined as supersonic flight.Aircraft is slowed down by space parachute under this speed, and the mission of space parachute is under velocity of sound aircraft down.Aircraft speed is faster, generally in the thinner environment of air.As the density of air apart from earth surface 50 km is approximately 1/1000 of earth surface, if with 5 times of sonic flights, relatively can bear 100 meters/conventional main chute per second, speed is fast 17 times.At this moment resistance can increase several thousand times.Due to rarefaction of air, ignore the factors such as sonic boom, canopy is designed to the structure being covered with unidirectional air channel, make umbrella cover wind area reduce several times, the size in unidirectional air channel is classification, thus realizes supersonic flight deceleration.
The present embodiment with shown in Fig. 1 to Figure 11 by canopy, unidirectional air channel, aerofoil, aerofoil card, return lock and the device such as elastic component, complete the design of hyprsonic parachute, the close momentum illustrated described in the present embodiment regulates the step included by aerodynamic decel erator method of designing automatically.
(1) function of setting device: the function needs being met aerodynamic decel erator by canopy, unidirectional air channel, aerofoil, aerofoil card, return lock and retainer spring design;
(2) aerodynamic decel erator: as required, design canopy, unidirectional air channel, aerofoil, aerofoil card, return lock and elastic component; Aerofoil comes off under being stuck in Aerodynamic force action, makes unidirectional air channel have the function automatically adjusted to close momentum; The elastic force of the elastic component of return lock makes aerofoil move to closed condition; The elastic force that aerofoil formation aerodynamic force and return are locked forms a pair application force and antagonistic force, and by changing aerofoil angle, aerodynamic decel erator realizes the automatic adjustment to close momentum; The design in the unidirectional air channel of multiple function difference, the aerodynamic braking realizing close momentum change regulates automatically;
(3) simulation analysis: according to the function needs of aerodynamic decel erator, carry out simulation analysis of computer to aerodynamic decel erator, to determine the Potamogeton crispus that retarder is final.
During lower density supersonic flight, air resistance is multiplied.Air resistance can be reduced by reducing wind area at double.The unidirectional air channel that grading design is made up of aerofoil, aerofoil card, return lock and elastic component, the unidirectional air channel of different stage is covered with canopy, and several times reduce wind area, avoid canopy to burst apart, and realize lower density supersonic flight and slow down.
In sum, aerodynamic decel erator provided by the invention, creatively proposing can to the design plan of the aerodynamic decel erator that close momentum regulates automatically, compared to prior art, the present invention is based on hydromechanical groundwork, by unidirectional air channel, aerofoil, aerofoil card, return locks and the design of elastic component makes aerodynamic decel erator have automatic regulation function to close momentum; The aerodynamic force that aerofoil is formed and the elastic force (being provided by elastic component) that return is locked form a pair application force and antagonistic force, by changing the angle of aerofoil and canopy, make the automatic regulation function of aerodynamic decel erator realization to close momentum.
The foregoing is only embodiments of the invention; not thereby the scope of the claims of the present invention is limited; every equivalents utilizing specification sheets of the present invention and accompanying drawing content to do, or be directly or indirectly used in relevant technical field, be all in like manner included in scope of patent protection of the present invention.
Claims (4)
1. an aerodynamic decel erator, it is characterized in that: comprise canopy and multiple close momentum adjusting part, described canopy comprises end face and side, on the end face that multiple close momentum adjusting part is evenly distributed on canopy and side, described close momentum adjusting part comprises return lock, first aerofoil, second aerofoil, first elastic component, second elastic component and aerofoil card, described return is locked for the curved rectangular hollow box body of end face, the bottom surface of described return lock is fixed on canopy, described first aerofoil is hinged on the relative two sides of return lock with the second aerofoil symmetry, the first jointed shaft that described first aerofoil and return are locked is provided with the first elastic component, the second jointed shaft that described second aerofoil and return are locked is provided with the second elastic component, described canopy offers the first unidirectional air channel and the second unidirectional air channel respectively corresponding to the first aerofoil and the second aerofoil, described first aerofoil inwardly can rotate around the first jointed shaft and close the first unidirectional air channel under the elastic force effect of the first elastic component, described second aerofoil inwardly can rotate around the second jointed shaft and close the second unidirectional air channel under the elastic force effect of the second elastic component, described aerofoil card comprises a transverse slat and is vertically set on two risers be oppositely arranged on transverse slat, described aerofoil cartoon is crossed two risers and is clamped on the first aerofoil and the second aerofoil the first aerofoil and the second aerofoil are parallel to each other.
2. aerodynamic decel erator according to claim 1, is characterized in that: described first elastic component and the second elastic component are torsion spring.
3. aerodynamic decel erator according to claim 1, is characterized in that: described first aerofoil and the second aerofoil semicircular in shape or arc.
4. aerodynamic decel erator according to claim 1, is characterized in that: described first elastic component and the second elastic component are positioned at return lock.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510884877.6A CN105416594B (en) | 2015-12-04 | 2015-12-04 | A kind of aerodynamic decel erator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510884877.6A CN105416594B (en) | 2015-12-04 | 2015-12-04 | A kind of aerodynamic decel erator |
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| Publication Number | Publication Date |
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| CN105416594A true CN105416594A (en) | 2016-03-23 |
| CN105416594B CN105416594B (en) | 2017-09-19 |
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| CN201510884877.6A Active CN105416594B (en) | 2015-12-04 | 2015-12-04 | A kind of aerodynamic decel erator |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108170878A (en) * | 2016-12-08 | 2018-06-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of supersonic vehicle sonic boom Forecasting Methodology |
| CN108466698A (en) * | 2018-04-17 | 2018-08-31 | 大连理工大学 | Inhibit control device, parachute and the control method of parachute spin |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0911995A (en) * | 1995-03-24 | 1997-01-14 | Nobuo Okazaki | Canopy of paraglider |
| CN2288138Y (en) * | 1996-06-14 | 1998-08-19 | 任义军 | Parachute for astronautic re-entry spacecraft |
| CN200946699Y (en) * | 2006-06-23 | 2007-09-12 | 晋江秉信阀业有限公司 | Improved structure of valve sheet pressing device |
| US20080191098A1 (en) * | 2007-01-25 | 2008-08-14 | Milan Babovka | Life parachute especially for ultra-lightweight aircrafts |
| CN202140632U (en) * | 2011-07-01 | 2012-02-08 | 苏州纽威阀门股份有限公司 | Pair-clamp and double-flap check valve |
-
2015
- 2015-12-04 CN CN201510884877.6A patent/CN105416594B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0911995A (en) * | 1995-03-24 | 1997-01-14 | Nobuo Okazaki | Canopy of paraglider |
| CN2288138Y (en) * | 1996-06-14 | 1998-08-19 | 任义军 | Parachute for astronautic re-entry spacecraft |
| CN200946699Y (en) * | 2006-06-23 | 2007-09-12 | 晋江秉信阀业有限公司 | Improved structure of valve sheet pressing device |
| US20080191098A1 (en) * | 2007-01-25 | 2008-08-14 | Milan Babovka | Life parachute especially for ultra-lightweight aircrafts |
| CN202140632U (en) * | 2011-07-01 | 2012-02-08 | 苏州纽威阀门股份有限公司 | Pair-clamp and double-flap check valve |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108170878A (en) * | 2016-12-08 | 2018-06-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of supersonic vehicle sonic boom Forecasting Methodology |
| CN108170878B (en) * | 2016-12-08 | 2021-03-26 | 中国航空工业集团公司沈阳空气动力研究所 | Supersonic aircraft sonic boom prediction method |
| CN108466698A (en) * | 2018-04-17 | 2018-08-31 | 大连理工大学 | Inhibit control device, parachute and the control method of parachute spin |
| CN108466698B (en) * | 2018-04-17 | 2021-03-19 | 大连理工大学 | Control device for inhibiting parachute spinning, parachute and control method |
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| Publication number | Publication date |
|---|---|
| CN105416594B (en) | 2017-09-19 |
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