CN204096080U - A kind of multi-rotor aerocraft load shock absorption device - Google Patents
A kind of multi-rotor aerocraft load shock absorption device Download PDFInfo
- Publication number
- CN204096080U CN204096080U CN201420465254.6U CN201420465254U CN204096080U CN 204096080 U CN204096080 U CN 204096080U CN 201420465254 U CN201420465254 U CN 201420465254U CN 204096080 U CN204096080 U CN 204096080U
- Authority
- CN
- China
- Prior art keywords
- shock
- adapter plate
- absorbing ball
- damping adapter
- rotor aerocraft
- 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.)
- Expired - Fee Related
Links
- 238000010521 absorption reaction Methods 0.000 title claims abstract description 13
- 230000035939 shock Effects 0.000 title claims abstract description 13
- 238000013016 damping Methods 0.000 claims abstract description 50
- 239000003351 stiffener Substances 0.000 claims abstract description 13
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Abstract
The utility model discloses a kind of multi-rotor aerocraft load shock absorption device, comprise shock-absorbing ball, vibration damper plate pillar stiffener, the first damping adapter plate and the second damping adapter plate, more than one of described shock-absorbing ball, more than one of described vibration damper plate pillar stiffener; Described vibration damper plate pillar stiffener is one by one through being arranged on the first described damping adapter plate and the second damping adapter plate after described shock-absorbing ball, the first described damping adapter plate upper surface and the second damping adapter plate lower surface are all provided with a more than shock-absorbing ball; Multi-rotor aerocraft load is arranged on the shock-absorbing ball of the first described damping adapter plate upper surface, the second described damping adapter plate lower surface is connected with multi-rotor aerocraft body by the shock-absorbing ball on it, thus utilize the inertia of load to offset low-frequency vibration and the filter high-frequency vibrations of multi-rotor aerocraft body, and link by middle shock-absorbing ball and supporting fuselage post the lateral stability ensureing vibration damper plate, reduce the amplitude of dislocation.
Description
Technical field
The utility model belongs to power machine field of components, is specifically related to a kind of multi-rotor aerocraft load shock absorption device, for eight-rotary wing aircraft.
Background technology
Existing cushion technique is simply yielding rubber ball and upper and lower vibration damper plate to be linked, rubber sphere own just has certain elasticity, after load strengthens, during aircraft heeling, the vibration damper plate up and down of rubber sphere link easily misplaces, and causes losing the effect of filtering vibrations.
Utility model content
In order to solve above-mentioned technical matters, of the present invention provide a kind of effectively can offset body low-frequency vibration and the multi-rotor aerocraft load shock absorption device of filter high-frequency vibrations.
The technical scheme that the utility model adopts is: a kind of multi-rotor aerocraft load shock absorption device, it is characterized in that: comprise shock-absorbing ball, vibration damper plate pillar stiffener, the first damping adapter plate and the second damping adapter plate, more than one of described shock-absorbing ball, more than one of described vibration damper plate pillar stiffener; Described vibration damper plate pillar stiffener is one by one through being arranged on the first described damping adapter plate and the second damping adapter plate after described shock-absorbing ball, the first described damping adapter plate upper surface and the second damping adapter plate lower surface are all provided with a more than shock-absorbing ball; Multi-rotor aerocraft load is arranged on the shock-absorbing ball of the first described damping adapter plate upper surface, the second described damping adapter plate lower surface is connected with multi-rotor aerocraft body by the shock-absorbing ball on it, thus utilizes the inertia of load to offset low-frequency vibration and the filter high-frequency vibrations of multi-rotor aerocraft body.
As preferably, the first described damping adapter plate and the second damping adapter plate are provided with shock-absorbing ball mounting hole, for installing described shock-absorbing ball.
As preferably, the first described damping adapter plate and the second damping adapter plate are the fine plate of carbon.
As preferably, described shock-absorbing ball rubber shock-absorbing ball.
As preferably, described shock-absorbing ball is evenly arranged on the first described damping adapter plate and the second damping adapter plate.
The utility model isolates body and load by shock-absorbing ball, by utilizing the inertia of load thus effective low-frequency vibration and filter high-frequency vibrations of offsetting body.And link by middle shock-absorbing ball and supporting fuselage post the lateral stability ensureing vibration damper plate, reduce the amplitude of dislocation.
figure of description
Fig. 1: the constructional drawing of the utility model embodiment.
Fig. 2: the STRUCTURE DECOMPOSITION figure of the utility model embodiment.
Fig. 3: the shock absorption device of the utility model embodiment and fuselage connection diagram.
Detailed description of the invention
Understand for the ease of those of ordinary skill in the art and implement the utility model, below in conjunction with drawings and Examples, the utility model is described in further detail, should be appreciated that exemplifying embodiment described herein is only for instruction and explanation of the utility model, and be not used in restriction the utility model.
Ask for an interview Fig. 1, Fig. 2 and Fig. 3, the technical scheme that the utility model adopts is: a kind of multi-rotor aerocraft load shock absorption device, comprise shock-absorbing ball 1, vibration damper plate pillar stiffener 2, first damping adapter plate 3 and the second damping adapter plate 4, more than one of shock-absorbing ball 1, more than one of vibration damper plate pillar stiffener 2; First damping adapter plate 3 and the second damping adapter plate 4 are the fine plate of carbon; Shock-absorbing ball 1 rubber shock-absorbing ball; First damping adapter plate 3 and the second damping adapter plate 4 are provided with shock-absorbing ball mounting hole, for installing shock-absorbing ball 1; Vibration damper plate pillar stiffener 2 is one by one through being evenly arranged on the first damping adapter plate 3 and the second damping adapter plate 4 after shock-absorbing ball 1, the first damping adapter plate 3 upper surface and the second damping adapter plate 4 lower surface are evenly provided with a more than shock-absorbing ball 1; Multi-rotor aerocraft load is arranged on the shock-absorbing ball 1 of the first damping adapter plate 3 upper surface, second damping adapter plate 4 lower surface is connected with multi-rotor aerocraft body by the shock-absorbing ball 1 on it, thus utilizes the inertia of load to offset low-frequency vibration and the filter high-frequency vibrations of multi-rotor aerocraft body.
Although this specification sheets more employs the terms such as shock-absorbing ball 1, vibration damper plate pillar stiffener 2, first damping adapter plate 3 and the second damping adapter plate 4, do not get rid of the possibility using other terms.Use these terms to be only used to describe essence of the present utility model more easily, the restriction that they are construed to any one additional is all contrary with the utility model spirit.
Should be understood that, the part that this specification sheets does not elaborate all belongs to prior art.
Should be understood that; the above-mentioned description for preferred embodiment is comparatively detailed; therefore the restriction to the utility model scope of patent protection can not be thought; those of ordinary skill in the art is under enlightenment of the present utility model; do not departing under the ambit that the utility model claim protects; can also make and replacing or distortion, all fall within protection domain of the present utility model, request protection domain of the present utility model should be as the criterion with claims.
Claims (5)
1. a multi-rotor aerocraft load shock absorption device, it is characterized in that: comprise shock-absorbing ball (1), vibration damper plate pillar stiffener (2), the first damping adapter plate (3) and the second damping adapter plate (4), more than one of described shock-absorbing ball (1), more than one of described vibration damper plate pillar stiffener (2); Described vibration damper plate pillar stiffener (2) is one by one through being arranged on the first described damping adapter plate (3) and the second damping adapter plate (4) after described shock-absorbing ball (1), the first described damping adapter plate (3) upper surface and the second damping adapter plate (4) lower surface are all provided with a more than shock-absorbing ball (1); Multi-rotor aerocraft load is arranged on the shock-absorbing ball (1) of the first described damping adapter plate (3) upper surface, the second described damping adapter plate (4) lower surface is connected with multi-rotor aerocraft body by the shock-absorbing ball (1) on it, thus utilizes the inertia of load to offset low-frequency vibration and the filter high-frequency vibrations of multi-rotor aerocraft body.
2. multi-rotor aerocraft load shock absorption device according to claim 1, is characterized in that: the first described damping adapter plate (3) and the second damping adapter plate (4) are provided with shock-absorbing ball mounting hole, for installing described shock-absorbing ball (1).
3. multi-rotor aerocraft load shock absorption device according to claim 1 and 2, is characterized in that: the first described damping adapter plate (3) and the second damping adapter plate (4) are the fine plate of carbon.
4. multi-rotor aerocraft load shock absorption device according to claim 1 and 2, is characterized in that: described shock-absorbing ball (1) rubber shock-absorbing ball.
5. multi-rotor aerocraft load shock absorption device according to claim 1, is characterized in that: described shock-absorbing ball (1) is evenly arranged on the first described damping adapter plate (3) and the second damping adapter plate (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420465254.6U CN204096080U (en) | 2014-08-18 | 2014-08-18 | A kind of multi-rotor aerocraft load shock absorption device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420465254.6U CN204096080U (en) | 2014-08-18 | 2014-08-18 | A kind of multi-rotor aerocraft load shock absorption device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204096080U true CN204096080U (en) | 2015-01-14 |
Family
ID=52264526
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420465254.6U Expired - Fee Related CN204096080U (en) | 2014-08-18 | 2014-08-18 | A kind of multi-rotor aerocraft load shock absorption device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204096080U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104875881A (en) * | 2015-05-26 | 2015-09-02 | 苏州绿农航空植保科技有限公司 | Central plate structure of multi-rotor craft |
| CN106697304A (en) * | 2017-02-28 | 2017-05-24 | 天峋（常州）智能科技有限公司 | High-reliability aircraft engine mounting mechanism |
| CN107025822A (en) * | 2017-06-09 | 2017-08-08 | 安徽安凯汽车股份有限公司 | A kind of passenger train gear box teaching training apparatus |
-
2014
- 2014-08-18 CN CN201420465254.6U patent/CN204096080U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104875881A (en) * | 2015-05-26 | 2015-09-02 | 苏州绿农航空植保科技有限公司 | Central plate structure of multi-rotor craft |
| CN106697304A (en) * | 2017-02-28 | 2017-05-24 | 天峋（常州）智能科技有限公司 | High-reliability aircraft engine mounting mechanism |
| CN107025822A (en) * | 2017-06-09 | 2017-08-08 | 安徽安凯汽车股份有限公司 | A kind of passenger train gear box teaching training apparatus |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150114 Termination date: 20190818 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |