CN208915466U - Landing buffer device - Google Patents
Landing buffer device Download PDFInfo
- Publication number
- CN208915466U CN208915466U CN201821172424.6U CN201821172424U CN208915466U CN 208915466 U CN208915466 U CN 208915466U CN 201821172424 U CN201821172424 U CN 201821172424U CN 208915466 U CN208915466 U CN 208915466U
- Authority
- CN
- China
- Prior art keywords
- landing
- absorbing
- buffer device
- composite material
- outer cylinder
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model provides a kind of landing buffer device, auxiliary landing mechanism including keeping vertical landing for ancillary rocket ontology, and the buffering energy-absorbing mechanism that one end is flexibly connected with auxiliary landing mechanism, buffering energy-absorbing mechanism includes outer cylinder, the power-absorbing being placed in outer cylinder, and one end is flexibly connected with auxiliary landing mechanism and the other end protrudes into the transmission rod supported in outer cylinder with power-absorbing, power-absorbing is the composite material tube made of carbon fiber or glass fibre multi-lay winding.The utility model uses the buffering energy-absorbing mechanism for being built-in with composite material tube, when reurnable booster lands, the composite material tube being accommodated in outer cylinder is crushed by transmission rod, to absorb the kinetic energy generated in reurnable booster landing mission, so that reurnable booster landing mission is more steady, so that the technical issues of light weight, intensity are high, cushion effect is steady and the requirement of good environmental adaptability can not be met simultaneously by efficiently solving landing buffer device.
Description
Technical field
The utility model belongs to the technical field of aerospace equipment, is to be related to a kind of landing buffer dress more specifically
It sets.
Background technique
With the development of aeronautical and space technology, the launch cost of carrier rocket how is reduced into entire aerospace industry
One of main problem faced, reurnable booster are different from general carrier rocket, are discarded after transmitting, being can be multiple
Transmitting, the New Launch reused, therefore, reurnable booster are the effective ways for reducing carrier rocket launch cost
Diameter is worth with high military and civilian.
Reurnable booster returns to landing field by vertical return technique generally after completing carrying duty, in order to guarantee
Reurnable booster reliably and securely lands on landing field, needs to reduce its landing speed and kinetic energy by buffer unit.
Currently, the buffer unit of various countries' research mainly has porous material formula, fluid pressure type, cutting type, thin-wall metal tubular type, tube-expanding type and magnetic
Rheology liquid formula, wherein porous material formula buffer unit mainly has foam metal and metal beehive, and foam metal material is in compression
With the increase of compression travel, cushion effect is also gradually increased, and causes cushion effect in entire buffering course unstable, adhesive type
Metal beehive, since adhesion strength is greatly reduced and leads to the thermal adaptability of cellular material binder when too high or too low for temperature
It is poor, it is impossible to be used in the more severe occasion of environment；Hydraulic buffer device must well solve the sealing of landing buffer device
And Temperature Controlling, design and technique to lander require very high；Processing of the cutting type buffer unit to cutter and metal sleeve
Precision and cooperation required precision are higher, otherwise will lead to cushion effect and larger fluctuation occur；Thin-wall metal tubular type buffer unit has
Simple, the at low cost advantage of high-strength light, manufacturing process, but cushion effect fluctuation is larger；Tube-expanding type buffer unit is due to its knot
Structure feature, maximum cushioning stroke are only integrally-built half, are chiefly used in the crash energy absorption equipment of space flight seat；Magnetorheological fluid formula
It is practical can't to be applied to engineering also in the scientific research stage for buffer unit.
Utility model content
The purpose of this utility model is to provide a kind of landing buffer devices, to solve in the prior art, landing buffer dress
The technical issues of light weight, intensity are high, cushion effect is steady and the requirement of good environmental adaptability can not be met simultaneously by setting.
To achieve the goals above, the technical solution adopted in the utility model is: providing a kind of for recyclable delivery
The landing buffer device of rocket, the reurnable booster include rocket ontology, and the landing buffer device includes can be with institute
State the auxiliary landing mechanism for being used to that the rocket ontology to be assisted to keep vertical landing of rocket ontology flexible connection, and opposite two
The buffering energy-absorbing mechanism that end can be flexibly connected with the rocket ontology and the auxiliary landing mechanism respectively, the buffering energy-absorbing machine
Structure includes the outer cylinder that can be flexibly connected with the rocket ontology, the power-absorbing and one end being placed in the outer cylinder and institute
It states the flexible connection of auxiliary landing mechanism and the other end protrudes into the transmission rod supported in the outer cylinder with the power-absorbing, the suction
Energy element is the composite material tube made of carbon fiber or glass fibre multi-lay winding.
Further, the outer cylinder includes cylinder, is connected on one end of the cylinder and can be hinged with the rocket ontology
First connecting portion, and be covered in the other end of the cylinder and be enclosed the lid of accommodating cavity with the cylinder, it is described
Composite material tube is placed in the accommodating cavity.
Further, the transmission rod includes the body of rod being arranged on the lid, be connected on one end of the body of rod and
With the hinged second connecting portion of the auxiliary landing mechanism, and be connected on the body of rod the other end and with the composite material
The pressure section that pipe is supported, the pressure section are placed in the accommodating cavity.
Further, the spherical shape in the surface of the second connecting portion.
Further, the composite material tube includes main laying of the ratio equal to or more than 60% for accounting for laying total quantity,
The wing flapping of the main laying is ± 10 °.
Further, the auxiliary landing mechanism includes the support rod that one end can be flexibly connected with the rocket ontology, with
And the foot pad being connect respectively with the other end of the support rod and the second connecting portion, the support rod can be with the rocket
One end that ontology is flexibly connected is located at the bottom side of the first connecting portion.
Further, the foot pad and the support rod are hinged, and the foot pad and the second connecting portion are hinged.
Further, the auxiliary landing mechanism includes being mutually inclined and spaced two support rod.
The beneficial effect of landing buffer device provided by the utility model is: using being built-in with the slow of composite material tube
Energy absorber is rushed, since composite material tube light weight, intensity are high and heat-resist, and when reurnable booster lands,
The composite material tube that is accommodated in outer cylinder is crushed by transmission rod, is generated in reurnable booster landing mission to absorb
Kinetic energy, so that reurnable booster landing mission is more steady, so that efficiently solving landing buffer device can not be simultaneously
Meet the technical issues of light weight, intensity are high, cushion effect is steady and the requirement of good environmental adaptability, reduces entire recyclable fortune
The weight for carrying rocket, improves the success rate of reurnable booster safe landing.
Detailed description of the invention
It, below will be to embodiment or the prior art in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
Attached drawing needed in description is briefly described, it should be apparent that, the accompanying drawings in the following description is only that this is practical new
Some embodiments of type for those of ordinary skill in the art without any creative labor, can be with
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is the stereoscopic schematic diagram of reurnable booster provided by the embodiment of the utility model；
Fig. 2 is the stereoscopic schematic diagram of buffering energy-absorbing mechanism in landing buffer device provided by the embodiment of the utility model；
Fig. 3 is the axis diagrammatic cross-section of buffering energy-absorbing mechanism in landing buffer device provided by the embodiment of the utility model；
Fig. 4 is the off-axis coordinate system schematic diagram of composite material provided by the embodiment of the utility model.
Wherein, each appended drawing reference in figure:
1-reurnable booster, 10-rocket ontologies, 20-landing buffer devices, 21-auxiliary landing mechanisms, 22-
Buffering energy-absorbing mechanism, 211-support rods, 212-foot pads, 221-outer cylinders, 222-transmission rods, 223-composite material tubes,
2210-accommodating cavities, 2211-cylinders, 2212-first connecting portions, 2213-lids, the 2221-bodies of rod, the 2222-the second connection
Portion, 2223-pressure sections, θ-wing flapping.
Specific embodiment
In order to which technical problem to be solved in the utility model, technical solution and beneficial effect is more clearly understood, with
Lower combination accompanying drawings and embodiments, the present invention will be further described in detail.It should be appreciated that specific reality described herein
It applies example to be only used to explain the utility model, is not used to limit the utility model.
It should be noted that it can be directly another when element is referred to as " being fixed on " or " being set to " another element
On one element or indirectly on another element.When an element is known as " being connected to " another element, it can
To be directly to another element or be indirectly connected on another element.
It is to be appreciated that term " length ", " width ", "upper", "lower", "front", "rear", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "top", "bottom" "inner", "outside" is that orientation based on the figure or position are closed
System, is merely for convenience of describing the present invention and simplifying the description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as limiting the present invention.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.The meaning of " plurality " is two or two in the description of the present invention,
More than, unless otherwise specifically defined.
It should also be noted that, radially referring in embodiment provided by the utility model perpendicular to structural member center
The direction of axis, and regardless of whether the cross section outer profile of the structural member is round.
It please refers to Fig.1 to Fig.3, now landing buffer device provided by the utility model is illustrated.Recyclable delivery fire
Arrow 1 include rocket ontology 10, this be used for reurnable booster 1 landing buffer device 20 include auxiliary landing mechanism 21 with
And buffering energy-absorbing mechanism 22, wherein auxiliary landing mechanism 21 can be flexibly connected with rocket ontology 10, be used for ancillary rocket ontology 10
Keep vertical landing；The opposite end of buffering energy-absorbing mechanism 22 can connect with rocket ontology 10 and 21 activity of auxiliary landing mechanism respectively
It connects comprising outer cylinder 221, power-absorbing and transmission rod 222, outer cylinder 221 can be flexibly connected with rocket ontology 10, power-absorbing
It is accommodated in outer cylinder 221, one end of transmission rod 222 is flexibly connected with auxiliary landing mechanism 21, and transmission rod 222 is another
End is protruded into outer cylinder 221 and is supported with power-absorbing, and herein, power-absorbing is made of carbon fiber or glass fibre multi-lay winding
Composite material tube 223.
Specifically, one end of composite material tube 223 and the bottom wall of outer cylinder 221 are supported, the other end of composite material tube 223
Supported with one end of drive rod 222, and composite material tube 223 by 3K (3000) carbon fiber wire or 3K glass fiber by
Line is immersed in the material liquid that epoxide-resin glue and curing agent etc. are mixed, and continuous winding is on mold, using solid
Be made after chemical conversion type so that composite material tube 223 have the intensity for being five times in steel, tolerable 2000 DEG C or more of heat resistance,
High impact properties, low thermal coefficient of expansion, 1/5th are in the specific gravity of steel, outstanding corrosion resistance and radiation resistance and very well
Anisotropy.In this way, guaranteeing that the generation when bearing axial compression of composite material tube 223 is circumferential destroys conquassation, and then by certainly
Body is broken to resist axial impact force to absorb kinetic energy when reurnable booster 1 lands, and when operating ambient temperature is higher
When, the reliability for varying widely and reducing buffer system will not occur due to energy absorption performance, and due to composite material specific strength
With specific modulus height, it can be effectively reduced the weight of entire landing buffer device 20, be conducive to light-weight design.
When reurnable booster 1 lands, auxiliary landing mechanism 21 first contacts landing platform, then assists landing mechanism 21
The anti-force of landing platform is oriented to buffering energy-absorbing mechanism 22, at this point, transmission rod 222 continues to protrude under anti-force effect
In outer cylinder 221, and composite material tube 223 is crushed.
Landing buffer device 20 provided by the utility model, compared with prior art, beneficial effect is: using built-in
There is the buffering energy-absorbing mechanism 22 of composite material tube 223, since 223 light weight of composite material tube, intensity are high and heat-resist, and
When reurnable booster 1 lands, the composite material tube 223 being accommodated in outer cylinder 221 is crushed by transmission rod 222, is come
The kinetic energy generated in 1 landing mission of reurnable booster is absorbed, so that 1 landing mission of reurnable booster is more steady,
It can not meet that light weight, intensity are high, cushion effect is steady and environmental suitability simultaneously to efficiently solve landing buffer device
The technical issues of good requirement, the weight of entire reurnable booster is reduced, improves reurnable booster safety
The success rate in land.
Further, Fig. 2 and Fig. 3 are please referred to, a kind of specific reality as landing buffer device provided by the utility model
Mode is applied, above-mentioned outer cylinder 221 includes cylinder 2211, first connecting portion 2212 and lid 2213, wherein first connecting portion 2212
Connect in one end of cylinder 2211, and first connecting portion 2212 can be hinged with above-mentioned rocket ontology 10, lid 2213 is sealed on
The other end of cylinder 2211, and lid 2213 and cylinder 2211 are enclosed accommodating cavity 2210, and above-mentioned composite material tube 223 holds
It sets in accommodating cavity 2210.Specifically, lid 2213 is fastenedly connected with cylinder 2211, and first connecting portion 2212 and cylinder 2211 weld
It connects or is integrally formed, and offer the first mounting hole in first connecting portion 2212, meanwhile, fixation is set on rocket ontology 10
It is equipped with connection lug, the second mounting hole is offered on the connection lug, first connecting portion 2212 is threaded through the first peace by pin shaft
In dress hole and the second mounting hole with connect lug hinged, assist landing mechanism 21 to rotate properly in this way, being conducive to outer cylinder 221 and cooperating
Angle.
Further, Fig. 2 and Fig. 3 are please referred to, a kind of specific reality as landing buffer device provided by the utility model
Mode is applied, above-mentioned transmission rod 222 includes the body of rod 2221, second connecting portion 2222 and pressure section 2223, wherein the body of rod 2221 is worn
Be located on above-mentioned lid 2213, second connecting portion 2222 connects in one end of the body of rod 2221, and second connecting portion 2222 with it is upper
It is hinged to state auxiliary landing mechanism 21, pressure section 2223 connects in the other end of the body of rod 2221, and pressure section 2223 with it is above-mentioned multiple
Condensation material pipe 223 is supported, and pressure section 2223 is accommodated in above-mentioned accommodating cavity 2210.Specifically, it second connecting portion 2222 and compresses
Portion 2223 and the body of rod 2221 are welded or are integrally formed, and the radial width of the body of rod 2221 is less than the radial width of accommodating cavity 2210, are supported
The radial width of splenium 2223 is greater than the radial width of the body of rod 2221 and is equal to or less than the radial width of accommodating cavity 2210, makes
The limit of pressure section 2223 is obtained in accommodating cavity 2210, and can swimmingly be slided along accommodating cavity 2210；Herein, the body of rod 2221 can be
Solid cylindrical member keeps its structural strength higher, or is hollow tubular element, and it is whole can to further decrease buffering energy-absorbing mechanism 22
Weight is determined with demand as the case may be, is not limited uniquely herein.
Preferably as a kind of specific embodiment of landing buffer device provided by the utility model, above-mentioned composite wood
Expects pipe 223 includes the main laying that ratio is not less than 60%, and the wing flapping θ of the main laying is ± 10 °.Specifically, as shown in figure 4, Z
Direction represents filametntary extending direction in main laying, and the direction H represents the direction perpendicular to fiber filament extending direction in main laying,
X-direction represents the extending direction after laying overlapping, and the direction Y represents the direction perpendicular to extending direction after laying overlapping, wing flapping
θ is the angle of Z-direction and X-direction.Experiment shows that the main laying quantity for being ± 10 ° as wing flapping θ accounts for the ratio of laying total quantity
When not less than 60%, composite material tube 223 have stronger bending stiffness, biggish non axial load can be resisted, when pipe fitting compared with
Integrally bending will not occur when long and lose energy-absorbing function, ensure that the energy-absorbing effect of landing buffer device 20.
Further, referring to Fig. 1, a kind of specific embodiment party as landing buffer device provided by the utility model
Formula, above-mentioned auxiliary landing mechanism 21 include support rod 211 and foot pad 212, wherein one end of support rod 211 can be with above-mentioned rocket
Ontology 10 is flexibly connected, and one end that can be flexibly connected with rocket ontology 10 of support rod 211 is located at above-mentioned first connecting portion
2212 bottom side, foot pad 212 are connect with the other end of support rod 211 and above-mentioned second connecting portion 2222 respectively, i.e. support rod
211 intersect at foot pad 212 with above-mentioned transmission rod 222, and support rod 211, above-mentioned buffering energy-absorbing mechanism 22 can be with rocket ontologies 10
It is enclosed a triangular structure, is conducive to the stability for ensureing 22 endergonic process of buffering energy-absorbing mechanism in this way.
Preferably, referring to Fig. 1, a kind of specific embodiment as landing buffer device provided by the utility model,
Above-mentioned foot pad 212 and above-mentioned support rod 211 are hinged, and foot pad 212 and above-mentioned second connecting portion 2222 are hinged.Such foot pad
212 can flexibly swing in support rod 211 and the junction of above-mentioned transmission rod 222, ensure that bottom surface and the landing platform of foot pad 212
Top surface remain fitting in 22 endergonic process of buffering energy-absorbing mechanism, and then ensured reurnable booster 1 land
Stability.
Preferably, referring to Fig. 2, a kind of specific embodiment as landing buffer device provided by the utility model,
The spherical shape in surface of above-mentioned second connecting portion 2222.Specifically, mounting groove is offered in above-mentioned foot pad 212, the mounting groove
It is adapted with second connecting portion 2222, second connecting portion 2222 is accommodated in the mounting groove, and such second connecting portion 2222 can be around
Mounting groove realizes multi-angle rotation, so that transmission rod 222 and the connection of foot pad 212 are more flexible.
Further, referring to Fig. 1, a kind of specific embodiment party as landing buffer device provided by the utility model
Formula, above-mentioned auxiliary landing mechanism 21 include two support rods 211, and two support rods 211 are mutually inclined and are spaced setting.Specifically
Ground, two support rods 211, above-mentioned buffering energy-absorbing mechanism 22 can be enclosed a three-dimensional triangular pyramid knot with above-mentioned rocket ontology 10
Structure, when reurnable booster 1 lands, above-mentioned foot pad 212 first contacts landing platform, and then foot pad 212 is by landing platform
Anti-force is oriented to buffering energy-absorbing mechanism 22, gradually tapers up during 22 energy-absorbing of buffering energy-absorbing mechanism and draws two supports
Bar 211 is swung up, i.e., under the action of two support rods 211 are drawn jointly, limiting transmission rod 222 can only be along above-mentioned outer cylinder
221 extending direction sliding, and then ensured the stability of 22 endergonic process of buffering energy-absorbing mechanism.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, all at this
Made any modifications, equivalent replacements, and improvements etc., should be included in the utility model within the spirit and principle of utility model
Protection scope within.
Claims (8)
1. landing buffer device is used for reurnable booster, the reurnable booster includes rocket ontology, the landing
Buffer unit includes that can be flexibly connected with the rocket ontology for assisting the rocket ontology to keep the auxiliary of vertical landing
The buffering energy-absorbing that landing mechanism and opposite end can be flexibly connected with the rocket ontology and the auxiliary landing mechanism respectively
Mechanism, which is characterized in that the buffering energy-absorbing mechanism includes the outer cylinder that can be flexibly connected with the rocket ontology, is placed in described
Power-absorbing and one end in outer cylinder are flexibly connected with the auxiliary landing mechanism and the other end protrudes into the outer cylinder and institute
The transmission rod that power-absorbing is supported is stated, the power-absorbing is the composite material made of carbon fiber or glass fibre multi-lay winding
Pipe.
2. landing buffer device as described in claim 1, which is characterized in that the outer cylinder includes cylinder, is connected on the cylinder
One end of body and first connecting portion that can be hinged with the rocket ontology, and be covered in the cylinder the other end and with it is described
Cylinder is enclosed the lid of accommodating cavity, and the composite material tube is placed in the accommodating cavity.
3. landing buffer device as claimed in claim 2, which is characterized in that the transmission rod includes being arranged on the lid
The body of rod, be connected on one end of the body of rod and with the hinged second connecting portion of the auxiliary landing mechanism, and be connected on institute
The pressure section stating the other end of the body of rod and supporting with the composite material tube, the pressure section are placed in the accommodating cavity.
4. landing buffer device as claimed in claim 3, which is characterized in that the spherical shape in the surface of the second connecting portion.
5. landing buffer device as described in claim 3 or 4, which is characterized in that the composite material tube is total including accounting for laying
The ratio of quantity is equal to or more than 60% main laying, and the wing flapping of the main laying is ± 10 °.
6. landing buffer device as claimed in claim 5, which is characterized in that the auxiliary landing mechanism includes that one end can be with institute
The support rod of rocket ontology flexible connection is stated, and connect respectively with the other end of the support rod and the second connecting portion
Foot pad, one end that can be flexibly connected with the rocket ontology of the support rod are located at the bottom side of the first connecting portion.
7. landing buffer device as claimed in claim 6, which is characterized in that the foot pad and the support rod are hinged, and institute
It states foot pad and the second connecting portion is hinged.
8. landing buffer device as claimed in claim 7, which is characterized in that the auxiliary landing mechanism include be mutually inclined and
Spaced two support rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821172424.6U CN208915466U (en) | 2018-07-23 | 2018-07-23 | Landing buffer device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821172424.6U CN208915466U (en) | 2018-07-23 | 2018-07-23 | Landing buffer device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208915466U true CN208915466U (en) | 2019-05-31 |
Family
ID=66694604
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821172424.6U Active CN208915466U (en) | 2018-07-23 | 2018-07-23 | Landing buffer device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208915466U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017269A (en) * | 2019-11-22 | 2020-04-17 | 北京宇航系统工程研究所 | Large-span foldable reusable rocket landing buffer structure |
| CN111038743A (en) * | 2019-12-09 | 2020-04-21 | 北京翎客航天科技有限公司 | Telescopic and foldable rocket landing system and application thereof |
| CN114426108A (en) * | 2021-12-08 | 2022-05-03 | 兰州空间技术物理研究所 | Specific-angle folding and unfolding mechanism for instrument panel of novel manned spacecraft |
-
2018
- 2018-07-23 CN CN201821172424.6U patent/CN208915466U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017269A (en) * | 2019-11-22 | 2020-04-17 | 北京宇航系统工程研究所 | Large-span foldable reusable rocket landing buffer structure |
| CN111017269B (en) * | 2019-11-22 | 2021-07-13 | 北京宇航系统工程研究所 | Large-span foldable reusable rocket landing buffer structure |
| CN111038743A (en) * | 2019-12-09 | 2020-04-21 | 北京翎客航天科技有限公司 | Telescopic and foldable rocket landing system and application thereof |
| CN114426108A (en) * | 2021-12-08 | 2022-05-03 | 兰州空间技术物理研究所 | Specific-angle folding and unfolding mechanism for instrument panel of novel manned spacecraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN208915466U (en) | Landing buffer device | |
| US5035307A (en) | Energy absorbing device | |
| CN106884919B (en) | Embedded multistage high-efficient energy-absorbing device | |
| EP1357016B1 (en) | Side member for use in vehicle frame and method of manufacturing the same | |
| CN106123710B (en) | The closed spherical anti-explosion container of foam metal sandwich | |
| US4740100A (en) | Attachment lug adapted to be fixed to an end of a cylindrical body, such as a power cylinder, and assembly | |
| CN109911246A (en) | Spacecraft composite structure is connected suitable for point type | |
| CN203528805U (en) | Plane anti-collision energy-absorbing structure unit | |
| CN115009363B (en) | Frame, slide chassis and electric automobile | |
| CN206416791U (en) | Bushing, automobile front under controlling arm and automobile | |
| CN206797692U (en) | Can handling goods aircraft fuselage loading cabin | |
| JP6103239B2 (en) | Reinforced beam material | |
| CN105173054A (en) | Telescopic tail pipe of unmanned helicopter and application of telescopic tail pipe | |
| CN108674635A (en) | A kind of undercarriage pendant hits energy absorption device | |
| US4807522A (en) | Piston and attaching apparatus for piston-and-cylinder arrangements | |
| EP3696431B1 (en) | Composite shock strut cylinder with integral metallic lower bearing carrier and sleeve | |
| JPS5992255A (en) | Impact absorptive steering shaft | |
| CN208069682U (en) | Composite material anti-climbing energy-absorbing device | |
| CN213261517U (en) | Dynamic energy-absorbing 3D composite material | |
| JPS5992256A (en) | Impact absorptive steering shaft | |
| CN210122192U (en) | Undercarriage buffer and undercarriage | |
| CN217170685U (en) | Guiding energy absorption device and railway vehicle | |
| CN107672548A (en) | A kind of bumper and automobile | |
| CN213566446U (en) | 70 kg unmanned helicopter landing frame device | |
| CN117231584B (en) | Carbon fiber hydraulic cylinder body, forming process of cylinder body and hydraulic cylinder |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 518000 innovation building 101, seven star creative workshop, 336, Baotian first road, fenghuanggang community, Xixiang street, Bao'an District, Shenzhen City, Guangdong Province Patentee after: Shenzhen qianxingda New Material Technology Co., Ltd Address before: 518000, Shenzhen District, Guangdong, Baoan District, Nanpu Road, No. 531, 7 floor, C District Patentee before: SHENZHEN QIANXING AVIATION SPACEFLIGHT MATERIAL Co.,Ltd. |