CN107380431A - A kind of unpowered spin rotor deceleration device - Google Patents
A kind of unpowered spin rotor deceleration device Download PDFInfo
- Publication number
- CN107380431A CN107380431A CN201710794259.1A CN201710794259A CN107380431A CN 107380431 A CN107380431 A CN 107380431A CN 201710794259 A CN201710794259 A CN 201710794259A CN 107380431 A CN107380431 A CN 107380431A
- Authority
- CN
- China
- Prior art keywords
- rotor
- blade
- connecting bracket
- rotor seat
- seat
- 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.)
- Pending
Links
- 210000004907 gland Anatomy 0.000 claims abstract description 10
- 229910000838 Al alloy Inorganic materials 0.000 claims description 11
- 230000005484 gravity Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 7
- 238000005457 optimization Methods 0.000 description 5
- 230000033001 locomotion Effects 0.000 description 3
- 230000004083 survival effect Effects 0.000 description 2
- 239000003643 water by type Substances 0.000 description 2
- -1 aluminium Gold Chemical compound 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
-
- 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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of unpowered spin rotor deceleration device, including rotor holder assembly, connecting bracket, upper end cover, wherein：The rotor holder assembly includes blade, rotor seat, rotor seat gland, bearing, bearing pin, the blade upper end is provided with through hole, the blade connects rotor seat by the bearing pin through through hole, the bearing is located in rotor seat, rotor seat gland is connected on the rotor seat, the bearing pin is provided with blade device for opening；Described connecting bracket one end and the brearing bore of rotor holder assembly coordinate, the external cylinder for being used to suspend of the other end；The upper end cover end face is connected with connecting bracket, and other end is used for external lampshade and illuminator.Because the air force of blade itself constructs, blade can adjust out cabin posture after opening and drive rotor seat to rotate the present invention under airflow function, play deceleration, pose adjustment effect, and package unit meets mark bullet to center of gravity, deceleration, the requirement of pose adjustment.
Description
Technical field
The present invention relates to navigation light technical field, and in particular to a kind of unpowered spin rotor deceleration device.
Background technology
With the needs of the task of search and rescue, it is badly in need of launching positioning mark bullet at a kind of supporting night, (is thrown with meeting that high-altitude is launched
Put 2000~5000m of height) mission requirements.Existing mark bullet is mainly equipped with parachute deceleration and realizes dispensing positioning, this kind of mode
It is primarily adapted for use in low latitude and launches (release altitude 500m), there is after dispensing that positioning runout degree is big, parachute is difficult to open influences to throw
Phenomena such as putting survival rate.Launched for this reason, it may be necessary to redesign a kind of ways of deceleration with meeting that mark plays night waters high ejection
Demand, disclosure satisfy that positioning runout degree requirement after dispensing, should possess after dispensing from posture function after rotor deceleration and adjustment dispensing.
The content of the invention
It is an object of the invention to：For above-mentioned deceleration device positioning runout degree it is big, be difficult to open and influence to launch survival rate
The problem of, present invention offer is a kind of to be met positioning runout degree, possesses the unpowered spin rotor that posture is adjusted from rotor reductor
Deceleration device.
The technical solution adopted by the present invention is as follows：
A kind of unpowered spin rotor deceleration device, including rotor holder assembly, connecting bracket, upper end cover, wherein：
The rotor holder assembly includes blade, rotor seat, rotor seat gland, bearing, bearing pin, and the blade upper end is provided with logical
Hole, the blade connect rotor seat by the bearing pin through through hole, and the bearing is located in rotor seat, connected on the rotor seat
Rotor seat gland is connect, the bearing pin is provided with blade device for opening；
Described connecting bracket one end and the brearing bore of rotor holder assembly coordinate, the external cylinder for being used to suspend of the other end；
The upper end cover end face is connected with connecting bracket, and other end is used for external lampshade and illuminator.
Further, the blade device for opening includes the torsion spring and torsion spring stop collar on bearing pin, the torsion spring one
End is touched with blade contact, the other end and rotor seated connection, and described torsion spring stop collar one end contacts with torsion spring, the other end and rotor seated connection
Touch.
Further, the connecting bracket uses hollow pyramidal structure, and the connecting bracket is closed using 2A12-T4 aluminium
Gold.
Further, the upper end cover takes plate-like hollow structure, and the upper end cover uses 2A12-T4 aluminium alloys.
Further, the blade uses 2A12 aluminium alloys.
Further, the upper end cover, connecting bracket are equipped with the convenient wire through for illuminator connection power supply
Through hole.
Further, the bearing is angular contact ball bearing.
In summary, by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
In rotor holder assembly of the present invention, four pieces of blades are distributed on the outside of rotor seat with symmetrical pattern, by bearing pin blade with
Rotor seat links together, and blade can make 90 ° of rotary motions along bearing pin, and torsion spring applies pretightning force to blade, makes blade in non-work
Make to be bonded with rotor seat circumference under state, when rotor seat is in running order, external force makes blade overcome the pretightning force of torsion spring to beat
Open.Because the air force of blade itself constructs, blade can adjust out cabin posture after opening under airflow function and drive rotation
Wing seat rotates, and plays deceleration, pose adjustment effect, and package unit meets mark bullet to center of gravity, deceleration, the requirement of pose adjustment.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the schematic diagram of the rotor holder assembly of the present invention；
Fig. 3 is the top view of the rotor holder assembly of the present invention；
Fig. 4 is the structure chart of the rotor seat of the present invention；
Fig. 5 is the blade schematic diagram of the present invention；
The torsion spring schematic diagram of Fig. 6 present invention；
Fig. 7 is the rotor seat gland schematic diagram of the present invention；
Fig. 8 is the connecting bracket schematic diagram of the present invention；
Fig. 9 is the upper end cover schematic diagram of the present invention；
Figure 10 is the off working state schematic diagram of the present invention；
Figure 11 is the working state schematic representation of the present invention；
Marked in figure：1- blades, 2- connecting brackets 2,3- rotors seat, 4- upper end covers, 5- illuminators, 6- lampshades, 7- wires,
8- bearing pins, 9- bearings, 11- torsion springs stop collar, 12- torsion springs, 13- cylinders.
Embodiment
With reference to Fig. 1~11 pair, the present invention elaborates.
Embodiment one：
As shown in Fig. 1~11, a kind of unpowered spin rotor deceleration device, including rotor holder assembly, connecting bracket 2, on
End cap 4, wherein：The rotor holder assembly includes blade 1, rotor seat 3, rotor seat gland, bearing 9, bearing pin 8, the blade 1
Upper end is provided with through hole, and the blade connects rotor seat by the bearing pin 8 through through hole, and the bearing 9 is located in rotor seat 3, institute
State connection rotor seat gland, the bearing pin 8 on rotor seat 3 and be provided with blade device for opening；Described one end of connecting bracket 2 and rotor
The inner hole of bearing 9 of holder assembly, the external cylinder 13 for being used to suspend in one end；The end face of upper end cover 4 and connecting bracket 2
Connection, the external lampshade 6 in other end and illuminator 5.
In the present embodiment, four pieces of blades 1 (as shown in Figure 5) are distributed on rotor seat 3 (as shown in Figure 2) outside with symmetrical pattern
Side, blade 1 and rotor seat 3 are linked together by bearing pin 8, blade 1 can make 90 ° of rotary motions along bearing pin 8.Such as Figure 10 and Figure 11
Shown, in off working state, blade 1 is in plumbness；In working condition, blade 1 is opened, in horizontality, blade 1 this
Quarter can rotate under airflow function.
It is supporting (as shown in Figure 1) for actual load from rotor deceleration device that this is unpowered, due to the air force of itself of blade 1
Construction, by the device for opening of blade 1, blade 1 can adjust out cabin posture after opening under airflow function and drive rotor seat 3 to revolve
Turn, play deceleration, pose adjustment effect.The external cylinder 13 for being used to suspend, the external illuminator 5, Ke Yiman in top below device
The mark requirement in sufficient night waters, package unit meet mark bullet to center of gravity, deceleration, the requirement of pose adjustment.
Embodiment two：
As a special case of embodiment one, as shown in figure 3, blade device for opening described in embodiment one includes being located at pin
Torsion spring 12 and torsion spring stop collar 11 on axle 8, described one end of torsion spring 12 contacts with blade 1, the other end contacts with rotor seat 3, institute
State that the one end of torsion spring stop collar 11 contacts with torsion spring 12, the other end contacts with rotor seat 3.
Torsion spring 12 applies pretightning force to blade 1, blade 1 is bonded (such as Fig. 2 with the circumference of rotor seat 3 in a non-operative state
It is shown), when rotor seat 3 is in running order, external force makes blade 1 overcome the pretightning force of torsion spring 12 to open.
The pretightning force of torsion spring 12 is adjusted by torsion spring stop collar 11, ensures that blade 1 can be opened normally, is realized to mark bullet
Slow down, the purpose of pose adjustment.
Embodiment three：
For the structure of further optimization rotor holder assembly, connecting bracket 2 described in embodiment one uses hollow cone knot
Structure, the connecting bracket 2 use 2A12-T4 aluminium alloys.
For the technical requirement of quality and overall center of gravity, connecting bracket 2 takes hollow cone structure (such as Fig. 8 institutes
Show), because higher to intensity requirement, therefore use 2A12-T4 aluminium alloys.
Example IV：
For the structure of further optimization rotor holder assembly, upper end cover 4 described in embodiment one takes plate-like hollow structure, institute
State upper end cover 4 and use 2A12-T4 aluminium alloys.
Because the wire of illuminator needs guiding through, therefore upper end cover 4 takes plate-like hollow structure, because higher to intensity requirement, therefore
Using 2A12-T4 aluminium alloys.
Embodiment five：
For the structure of further optimization rotor holder assembly, blade 1 described in embodiment one uses 2A12 aluminium alloys.
Blade 1 bears larger impulsive force when opening, therefore uses 2A12 aluminium alloys to be heat-treated after being molded to improve its machinery
Performance.
Embodiment six：
It is equal to upper end cover 4 described in embodiment five, connecting bracket 2 for the structure of the further optimization present apparatus, embodiment one
Provided with the convenient through hole through the wire 7 that power supply is connected for illuminator 5.By through hole, the wire 7 of illuminator 5 can smoothly lead to
Cross and be connected with power supply.Prevent wire is external from causing to damage, and internal cabling is easy to connect, classification is clear, is easy to assemble.
Embodiment seven：
For the structure of the further optimization present apparatus, embodiment one to bearing 9 described in embodiment five is angular contact ball bearing.
Because rotor holder assembly rotates in working condition around connecting bracket 2, therefore in rotor seat 3 with being connected branch
The bearing that the joint of frame 2 installs additional uses angular contact ball bearing, is fixed on and is chosen in wing seat with rotor seat gland (as shown in Figure 7),
Ensure that the spinning movement after blade opening is flexible.
It is embodiments of the invention as described above.The present invention is not limited to the above-described embodiments, anyone should learn that
The structure change made under the enlightenment of the present invention, the technical schemes that are same or similar to the present invention, each fall within this
Within the protection domain of invention.
Claims (7)
1. a kind of unpowered spin rotor deceleration device, it is characterised in that including rotor holder assembly, connecting bracket (2), upper end cover
(4), wherein：
The rotor holder assembly includes blade (1), rotor seat (3), rotor seat gland, bearing (9), bearing pin (8), the blade
(1) upper end is provided with through hole, and the blade connects rotor seat by the bearing pin (8) through through hole, and the bearing (9) is located at rotor seat
(3) in, rotor seat gland is connected on the rotor seat (3), the bearing pin (8) is provided with blade device for opening；
Described connecting bracket (2) one end and bearing (9) inner hole of rotor holder assembly, the external cylinder for being used to suspend in one end
(13)；
Upper end cover (4) end face is connected with connecting bracket (2), the external lampshade in other end (6) and illuminator (5).
2. the unpowered spin rotor deceleration device of one kind according to claim 1, it is characterised in that the blade opens dress
Put including the torsion spring (12) and torsion spring stop collar (11) on bearing pin (8), described torsion spring (12) one end contacts with blade (1),
The other end contacts with rotor seat (3), and described torsion spring stop collar (11) one end contacts with torsion spring (12), the other end and rotor seat (3)
Contact.
3. the unpowered spin rotor deceleration device of one kind according to claim 1, it is characterised in that the connecting bracket
(2) hollow pyramidal structure is used, the connecting bracket (2) uses 2A12-T4 aluminium alloys.
4. the unpowered spin rotor deceleration device of one kind according to claim 1, it is characterised in that the upper end cover (4)
Plate-like hollow structure is taken, the upper end cover (4) uses 2A12-T4 aluminium alloys.
5. the unpowered spin rotor deceleration device of one kind according to claim 1, it is characterised in that the blade (1) is adopted
With 2A12 aluminium alloys.
6. according to a kind of any described unpowered spin rotor deceleration device of Claims 1 to 5, it is characterised in that on described
End cap (4), connecting bracket (2) are equipped with the through hole of the convenient wire (7) through for illuminator (5) connection power supply.
7. according to a kind of any described unpowered spin rotor deceleration device of Claims 1 to 5, it is characterised in that the axle
It is angular contact ball bearing to hold (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710794259.1A CN107380431A (en) | 2017-09-06 | 2017-09-06 | A kind of unpowered spin rotor deceleration device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710794259.1A CN107380431A (en) | 2017-09-06 | 2017-09-06 | A kind of unpowered spin rotor deceleration device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107380431A true CN107380431A (en) | 2017-11-24 |
Family
ID=60351733
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710794259.1A Pending CN107380431A (en) | 2017-09-06 | 2017-09-06 | A kind of unpowered spin rotor deceleration device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107380431A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112224386A (en) * | 2020-10-20 | 2021-01-15 | 南京航空航天大学 | Single-wing self-rotating landing device |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2706097A (en) * | 1954-03-15 | 1955-04-12 | Edward B Johnson | Apparatus and method of lowering bodies into space |
| US2917255A (en) * | 1958-08-01 | 1959-12-15 | William Hunter A Boyd | Self-regulating rotochute |
| US3265136A (en) * | 1964-03-02 | 1966-08-09 | Hoffman Electronics Corp | Descent mechanism |
| US3978790A (en) * | 1975-10-23 | 1976-09-07 | The Boeing Company | High altitude sonobuoy |
| US4890554A (en) * | 1987-03-20 | 1990-01-02 | Schleimann Jensen Lars J | System for guiding a flying object towards a target |
| US5947419A (en) * | 1998-01-21 | 1999-09-07 | Warren; Charles M. | Aerial cargo container |
| FR2900469A1 (en) * | 2006-04-28 | 2007-11-02 | Saint Louis Inst | RECOGNITION DEVICE. |
| CN101421157A (en) * | 2004-04-14 | 2009-04-29 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| CN207129145U (en) * | 2017-09-06 | 2018-03-23 | 郑州郑飞机电技术有限责任公司 | A kind of unpowered spin rotor deceleration device |
-
2017
- 2017-09-06 CN CN201710794259.1A patent/CN107380431A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2706097A (en) * | 1954-03-15 | 1955-04-12 | Edward B Johnson | Apparatus and method of lowering bodies into space |
| US2917255A (en) * | 1958-08-01 | 1959-12-15 | William Hunter A Boyd | Self-regulating rotochute |
| US3265136A (en) * | 1964-03-02 | 1966-08-09 | Hoffman Electronics Corp | Descent mechanism |
| US3978790A (en) * | 1975-10-23 | 1976-09-07 | The Boeing Company | High altitude sonobuoy |
| US4890554A (en) * | 1987-03-20 | 1990-01-02 | Schleimann Jensen Lars J | System for guiding a flying object towards a target |
| US5947419A (en) * | 1998-01-21 | 1999-09-07 | Warren; Charles M. | Aerial cargo container |
| CN101421157A (en) * | 2004-04-14 | 2009-04-29 | 保罗·E·阿尔托恩 | Rotary wing vehicle |
| FR2900469A1 (en) * | 2006-04-28 | 2007-11-02 | Saint Louis Inst | RECOGNITION DEVICE. |
| CN207129145U (en) * | 2017-09-06 | 2018-03-23 | 郑州郑飞机电技术有限责任公司 | A kind of unpowered spin rotor deceleration device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112224386A (en) * | 2020-10-20 | 2021-01-15 | 南京航空航天大学 | Single-wing self-rotating landing device |
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| 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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171124 |
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| RJ01 | Rejection of invention patent application after publication |